EP3999721A1 - Turbine casing comprising a low-stress connection flange, and exhaust-gas turbine having such a turbine casing - Google Patents

Turbine casing comprising a low-stress connection flange, and exhaust-gas turbine having such a turbine casing

Info

Publication number
EP3999721A1
EP3999721A1 EP20733442.6A EP20733442A EP3999721A1 EP 3999721 A1 EP3999721 A1 EP 3999721A1 EP 20733442 A EP20733442 A EP 20733442A EP 3999721 A1 EP3999721 A1 EP 3999721A1
Authority
EP
European Patent Office
Prior art keywords
housing
turbine
turbine housing
bores
clamping edge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP20733442.6A
Other languages
German (de)
French (fr)
Inventor
Matthias Richner
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Turbo Systems Switzerland Ltd
Original Assignee
Turbo Systems Switzerland Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Turbo Systems Switzerland Ltd filed Critical Turbo Systems Switzerland Ltd
Publication of EP3999721A1 publication Critical patent/EP3999721A1/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/39—Retaining components in desired mutual position by a V-shaped ring to join the flanges of two cylindrical sections, e.g. casing sections of a turbocharger
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/97—Reducing windage losses
    • F05D2260/972—Reducing windage losses in radial flow machines

Definitions

  • Turbine housing with a low-stress connecting flange and exhaust gas turbine with such a turbine housing
  • the invention relates to a turbine housing with a low-stress connecting flange and an exhaust gas turbine with such a turbine housing.
  • the exhaust gas turbine can be, for example, a turbocharger turbine for a turbocharger or a utility turbine.
  • a one-piece exhaust system of a gas turbine is known from US 2015/0143814 A1.
  • This exhaust system has a turbine outlet housing and a turbine exhaust manifold, the turbine outlet housing being connected to the turbine exhaust manifold at outwardly directed interface flanges. This makes it possible, if necessary, to detach the turbine exhaust manifold by simply decoupling it from the turbine outlet housing and to replace it with a new component.
  • a gas turbine is known from EP 3 103 972 A1, in which a high-pressure turbine housing is connected to a diffuser housing on outwardly directed flanges.
  • a typical turbocharger has a turbine housing, a bearing housing and a compressor housing, the turbine housing being connected to the bearing housing and the bearing housing also being connected to the compressor housing.
  • the connection between the turbine housing and the bearing housing must meet several requirements. These requirements include ensuring gas tightness, preventing twisting between the two housings due to external forces and ensuring that the two housings are held together even in the event of a burst.
  • the connection between the turbine housing and the bearing housing must in particular be designed in such a way that it can cope with large temperature differences between the turbine housing and the bearing housing and high forces in the event of a burst.
  • a reliable safety enclosure - called "containment" in English - is a very important and therefore structurally very demanding requirement for an exhaust gas turbine in such a burst.
  • FIG. 1 shows a first sectional view to illustrate a turbine housing according to the prior art.
  • This turbine housing has a connecting flange 2, via which the turbine housing 1 is connected to the bearing housing 14 of a turbocharger.
  • This connection is implemented using connecting elements screwed into the housing connecting bores of the connecting flange, which press clamping lugs 16 onto the connecting flange 2 of the turbine housing 1 and onto the bearing housing 14 by means of nuts 17, whereby the bearing housing 14 is also pressed against the turbine housing.
  • the mentioned housing connection bores are spaced from one another (that is to say spatially apart from one another) and are arranged in the circumferential direction along a circle.
  • the clamping lugs are also arranged along a circle in the circumferential direction of the turbine housing.
  • FIG. 2 shows a second sectional view to illustrate a turbine housing according to the prior art.
  • This second sectional illustration illustrates the turbine housing at an interface at which a connecting element 15 is screwed into a housing connecting bore 3 of the connecting flange 2 of the turbine housing.
  • a clamping lug 16 is pressed both onto the turbine housing 2 and onto the bearing housing 14, which is implemented using a nut 17 and a washer 18.
  • the object of the invention is to provide a turbine housing and an exhaust gas turbine in which the disadvantages mentioned above with reference to a turbocharger are reduced.
  • a turbine housing of this type has a connecting flange for connection on the bearing housing side to a bearing housing, in which housing connecting bores spaced apart from one another in the circumferential direction are provided, with material recesses in the connecting flange being provided between adjacent housing connecting bores radially inwardly towards a longitudinal center axis of the turbine housing.
  • the turbine housing can also be in several parts.
  • a heat shield or a nozzle ring can be arranged between the turbine housing and the bearing housing.
  • drilling is to be interpreted functionally and not, due to manufacturing reasons, to mechanical processing using a drilling machine or milling machine.
  • the spaced apart housing connecting bores in the connecting flange are arranged along at least one circle.
  • the turbine housing has a clamping edge which is arranged adjacent to the housing connecting bores in the radial direction.
  • annular recess is provided in the clamping edge, which has a recess base, the adjacent housing connection bores being made in the recess base and the material recesses provided between two adjacent housing connection bores being provided in the recess base.
  • the clamping edge in the area between two adjacent housing connecting bores each has a clamping edge recess that widens the annular recess.
  • the depth of the clamping edge recess corresponds to the sum of the depth of the annular recess and the depth of the material recesses provided in the annular recess.
  • the turbine housing is constructed in several pieces.
  • the clamping edge forms a separate part of the turbine housing.
  • a heat shield or a nozzle ring forms a separate part of the turbine housing.
  • the clamping edge is part of the heat shield or the nozzle ring.
  • an exhaust gas turbine has a turbine housing with the features according to the invention.
  • an exhaust gas turbine has a bearing housing connected to the turbine housing, the turbine housing being connected to the bearing housing by means of connecting elements.
  • an exhaust gas turbine has clamping elements, each of which is formed by a connecting element or by several Connecting elements are pressed to the connecting flange of the turbine housing and to the bearing housing.
  • the clamping elements of the exhaust gas turbine are pressed against the clamping edge.
  • the connecting elements are screws or threaded pins.
  • the advantages of the invention are in particular that the material recesses provided between the housing connecting bores enable the connecting flange area to be heated more quickly and more evenly during operation of the respective exhaust gas turbine. Due to these material cutouts, there is also a reduced rigidity of the turbine housing in the area of the connecting flange. As a result, lower thermal transient stresses occur when the exhaust gas turbine is in operation. This in turn leads to an extension of the service life of the turbine housing and thus also to an extension of the service life of the entire exhaust gas turbine.
  • Figure 1 is a first sectional view to illustrate a
  • Figure 2 is a second sectional view to illustrate a
  • Figure 3 is a sketch to illustrate an inventive
  • Figure 4 is a sectional view in the radial direction to illustrate a
  • FIG. 5 shows a sectional illustration according to the section line C-C shown in FIG. 4
  • FIG. 6 shows a sketch to illustrate another embodiment of FIG
  • FIG. 7 shows a sectional illustration in the direction of the section line AA shown in FIG. 6,
  • Figure 8 is a sketch to illustrate a further embodiment of the
  • FIG. 9 shows a sectional illustration in the direction of the cutting line shown in FIG.
  • FIG. 3 shows a sketch to illustrate a turbine housing according to the invention, only a partial area of this turbine housing being shown in FIG.
  • the turbine housing has a connecting flange 2 which is arranged coaxially to a longitudinal center axis of the turbine housing and which is equipped with a clamping edge 7.
  • connecting webs 19 extending inward in the radial direction 8 are provided, in which housing connecting bores 3 are made.
  • Said connecting webs 19 and thus also the housing connecting bores 3 introduced into them are spaced apart from one another in the circumferential direction 9 of the turbine housing. They are arranged in the connection flange in the circumferential direction 9 along one or more circles.
  • material recesses 4 which are open radially inward are provided in the clamping edge 7 of the connecting flange 2.
  • These material recesses 4 can be introduced into the clamping edge of the connecting flange by material removal or, if a shaping manufacturing process is used, they can be modeled directly.
  • the geometry of the material recesses can be selected differently.
  • the material recesses can be made semicircular, elliptical, bell-shaped or rectangular.
  • a connection of the turbine housing to a bearing housing of a turbocharger takes place in the same way as was explained above in connection with FIG. 2 using connecting elements which are each introduced into a housing connecting bore 3 of the connecting flange 2, Furthermore, clamping elements arranged along a circle in the circumferential direction of the turbine housing, which in one embodiment are clamping lugs, are pressed onto both the turbine housing and the bearing housing, which is implemented using a nut and a washer.
  • the material recesses 4 provided in contrast to the prior art bring about faster and more uniform heating of the connecting flange 2 of the turbine housing when the turbocharger is in operation. Furthermore, due to the material cutouts 4 made in the connecting flange 2, there is a reduced rigidity of the turbine housing in the area of the connecting flange 2. This in turn has the consequence that in the area of the connecting flange 2, reduced thermal transient stresses occur in comparison with the prior art. This reduction in thermal transient stresses in the area of the connecting flange extends the service life of the turbine housing and thus also the service life of the entire turbocharger.
  • FIG. 4 shows a sectional illustration in the radial direction to illustrate an embodiment of the invention.
  • the connection flange 2 of the turbine housing and the bearing housing 14 connected to the connection flange 2 and thus to the turbine housing 14 are shown.
  • the connection of the turbine housing to the bearing housing is realized using a clamping bracket 16 in the sectional plane shown.
  • This clamping lug 16 is pressed onto the connecting flange 2 of the turbine housing and onto the bearing housing 14.
  • This pressing is implemented using a nut 17 and a washer 18 arranged between the nut 17 and the clamping bracket 16.
  • FIG. 4 shows a sectional illustration in the radial direction to illustrate an embodiment of the invention.
  • the connection flange 2 of the turbine housing and the bearing housing 14 connected to the connection flange 2 and thus to the turbine housing 14 are shown.
  • the connection of the turbine housing to the bearing housing is realized using a clamping bracket 16 in the sectional plane shown.
  • This clamping lug 16 is pressed onto the connecting flange 2 of the turbine housing
  • FIG. 5 shows a sectional view according to the section line C-C shown in FIG. From this illustration it can be seen in particular that between each two housing connection bores 3 spaced apart from one another in the circumferential direction 9, in which connection elements 15 are introduced, material recesses 4 are provided in the clamping edge 7 of the connection flange 2 of the turbine housing, which in the sectional plane shown are in the radial direction 8 outside the Bearing housing 14 are located and are open radially inward.
  • FIG. 6 shows a sketch to illustrate another embodiment of the invention.
  • an annular recess 5 is provided in the radially inner edge area of the clamping edge 7 of the connecting flange 2 of the turbine housing, which extends in the circumferential direction 9 over the entire circumference of the turbine housing.
  • This annular recess 5 has a recess bottom 6.
  • the housing connecting bores 3, which are spaced apart from one another in the circumferential direction 9, are introduced into the recess bottom 6 of the annular recess 5.
  • Material recesses 4 also made in the recess bottom 6 of the annular recess 5. These material recesses 4 extend in the radial direction 8 over the entire recess base 6.
  • FIG. 7 shows a sectional illustration in the direction of the section line AA shown in FIG. 6.
  • the depth of the housing connecting bores 3 made in the recess base 6 is designated by the reference number 12.
  • the depth of the material recesses 4 corresponds to the depth 12 of the housing connecting bores 3 made in the recess base 6.
  • the depth of the material recesses 4 can also differ from the depth of the housing connecting bores 3.
  • the depth of the annular recess 5 is denoted by the reference number 11.
  • the sum of the depth 1 1 of the annular recess and the depth 12 of the housing connecting bores made in the recess base is denoted by the reference number 20.
  • FIG. 8 shows a sketch to illustrate a further embodiment of the invention.
  • an annular recess 5 is again provided in the radially inner edge region of the clamping edge 7 of the connecting flange 2 of the turbine housing, which extends in the circumferential direction 9 over the entire circumference of the turbine housing.
  • Housing connection bores 3 spaced apart from one another in the circumferential direction 9, between which the material recesses 4 are located, are again made in the recess bottom 6 of the annular recess 5.
  • These recesses 4 are open inward in the radial direction 8 and extend into the area of the clamping edge 7. Consequently, in this development, the clamping edge 7 has clamping edge recesses 10, which are each provided between two adjacent housing connection bores 3. In the exemplary embodiment shown, these clamping edge recesses 10 extend in the radial direction 8 through the entire clamping edge 7.
  • FIG. 9 shows a sectional illustration in the direction of the section line BB shown in FIG. 8.
  • the clamping edge recess 10 provided in the clamping edge 7 has a first depth 20.
  • the annular recess 5 has a second depth 11.
  • the housing connection bores 3 made in the recess bottom 6 have a third depth 12.
  • the first depth 20 of the clamping edge recess 10 agrees with the embodiment shown Sum of the second depth 1 1 of the annular recess 5 and the third depth 12 of the housing connecting bore 3 provided in the annular recess 5.
  • the depths 20, 11 and 12 each extend in the axial direction 13 of the turbine housing.
  • the flange thickness 19 of the connecting flange 2 is reduced, so that the thermal transient stresses occurring in the connecting flange 2 are reduced compared to the prior art, which leads to an extended service life of the turbine housing and thus of the entire turbocharger.
  • This turbocharger has a turbine housing, as has been explained above.
  • this turbocharger has a bearing housing connected to the turbine housing, the turbine housing being connected to the bearing housing by means of connecting elements 15 introduced into the housing connection bores 3 of the turbine housing, which are for example screws or threaded pins.
  • the turbocharger has clamping elements implemented as clamping lugs 16, which are each pressed by one or more connecting elements onto the connecting flange 2 of the turbine housing and onto the bearing housing 14.
  • the clamping elements are pressed against a clamping edge of the connecting flange.
  • clamping disks or clamping rings can also be used, for example.
  • the clamping elements are preferably designed to be at least slightly elastic in order to be able to yield at least slightly when the nuts are tightened.
  • the spaced apart are spaced apart
  • Housing connection bores 3 arranged in the connection flange 2 in the circumferential direction along at least one circle, preferably at most three or at most two (concentric to each other and / or to the turbine axis) and extend along the entire at least one circle, preferably distributed over the entire circumference at regular intervals.
  • the number of housing connection holes required depends on the strength requirements in the event of damage (containment) and the tightness requirements.
  • Housing connection bores 3 in the connection flange 2 can also be arranged in the circumferential direction along two or more circles, with, for example, every second housing connection bore 3 being arranged along a first circle and each housing connection bore 3 lying in between being arranged along a second circle.
  • the flange has at least five housing connection bores 3 and / or at least two, preferably at least four, particularly preferably at least five of the material recesses 4 between adjacent housing connection bores 3.
  • 3 material recesses 4 are provided between all housing connecting bores.
  • the material recesses 4 are open radially inward.
  • the material recesses 4 are preferably closed in the axial direction by a (e.g., ring-shaped) rear side of the connecting flange, so they are not continuous in the axial direction.
  • material recesses 4 cannot be provided between all the housing connecting bores 3, but only where the influence on the service life is relevant, for example in the area of the entry into the spiral.
  • the flange is arranged coaxially to the longitudinal center axis of the turbine housing.
  • the flange is oriented towards a bearing housing of the exhaust gas turbine or is arranged for the connection of the turbine housing to the bearing housing (optionally with part of a heat shield and / or a diffuser ring between the flange and the corresponding part of the bearing housing).
  • the recess 4 has an arc length in the circumferential direction of more than half the distance between the centers of the two housing connection bores 3.
  • the connecting flange 2 has connecting webs 19 which directly surround the housing connecting bores 3 at least in sections and which are arranged in the circumferential direction between the adjacent housing connecting bores 3 and the material recess 4 lying between them.
  • connection flange 2 has a clamping edge 7 which is arranged adjacent to the housing connection bores 3 in the radial direction 8.
  • the connecting webs 19 run radially inward, starting from the clamping edge 7.
  • the clamping edge can be provided as a separate part of the turbine housing or be provided in one piece with the rest of the turbine housing or connecting flange.
  • the turbine housing can be designed in several pieces.
  • a heat shield or a nozzle ring can form a separate part of the turbine housing.
  • the clamping edge of the turbine housing can be part of the heat shield or the nozzle ring, ie it can be integrated into the heat shield or the nozzle ring.
  • the connecting webs are arranged recessed relative to the clamping edge 7 in the axial direction.
  • the clamping edge protrudes (for example by less than 1 mm or even by at most 0.5 mm and / or by more than 0.1 mm) in the axial direction beyond the connecting webs (for example in the direction away from the turbine housing or towards to the bearing housing of the exhaust gas turbine).
  • the connecting webs form part of a recess bottom.
  • the material recesses 4 provided between each two adjacent housing connection bores are arranged so as to be deeper than the connection webs in the axial direction.
  • the clamping edge can run continuously (without interruption) in the circumferential direction or have recesses.
  • the connecting flange 2 has an annular recess 5 which has a recess bottom 6.
  • the adjacent housing connecting bores 3 are made in the recess bottom.
  • the material recesses 4 provided between each two adjacent housing connecting bores are provided in the recess bottom.
  • a preferred aspect of the present invention relates to a turbine housing for an exhaust gas turbine, which has a connecting flange for connecting the turbine housing on the bearing housing side to a bearing housing of the exhaust gas turbine.
  • This connecting flange is preferably a side wall of the turbine housing on the bearing housing side.
  • the side wall of the turbine housing is preferably designed to be directly connected to a turbine-side side wall of the bearing housing, or connected directly to the turbine-side side wall of the bearing housing.
  • the side wall of the turbine housing is preferably to be connected to a turbine-side side wall of the bearing housing by means of a (penetrating into the housing connecting bores of the turbine housing) common connecting element, for example a connecting screw, or connected to the turbine-side side wall of the bearing housing by means of such a common connecting element.
  • a common connecting element for example a connecting screw

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a turbine casing for an exhaust-gas turbine, which turbine casing has a connection flange for bearing-casing-side attachment to a bearing casing in which casing-connection holes that are mutually spaced in the circumferential direction are provided, wherein, between adjacent casing-connection holes, material recesses that are open radially inwards towards a central longitudinal axis of the turbine casing are provided in the connection flange. The invention further relates to an exhaust-gas turbine which is equipped with such a turbine casing.

Description

Turbinengehäuse mit einem spannungsarmen Verbindungsflansch und Abgasturbine mit einem solchen Turbinengehäuse Turbine housing with a low-stress connecting flange and exhaust gas turbine with such a turbine housing
Technisches Gebiet der Erfindung Technical field of the invention
Die Erfindung betrifft ein Turbinengehäuse mit einem spannungsarmen Verbindungsflansch und eine Abgasturbine mit einem solchen Turbinengehäuse. Je nach Ausführungsform kann die Abgasturbine beispielsweise eine Turbolader-Turbine für einen Turbolader oder eine Nutzturbine sein. The invention relates to a turbine housing with a low-stress connecting flange and an exhaust gas turbine with such a turbine housing. Depending on the embodiment, the exhaust gas turbine can be, for example, a turbocharger turbine for a turbocharger or a utility turbine.
Stand der Technik State of the art
Aus der US 2015/0143814 A1 ist ein einstückiges Abgassystem einer Gasturbine bekannt. Dieses Abgassystem weist ein Turbinenaustrittsgehäuse und einen Turbinenabgaskrümmer auf, wobei das Turbinenaustrittsgehäuse mit dem Turbinenabgaskrümmer an nach außen gerichteten Schnittstellenflanschen verbunden ist. Dies ermöglicht es, bei Bedarf den Turbinenabgaskrümmer durch ein einfaches Entkoppeln vom Turbinenaustrittsgehäuse zu lösen und durch ein neues Bauteil zu ersetzen. A one-piece exhaust system of a gas turbine is known from US 2015/0143814 A1. This exhaust system has a turbine outlet housing and a turbine exhaust manifold, the turbine outlet housing being connected to the turbine exhaust manifold at outwardly directed interface flanges. This makes it possible, if necessary, to detach the turbine exhaust manifold by simply decoupling it from the turbine outlet housing and to replace it with a new component.
Aus der EP 3 103 972 A1 ist eine Gasturbine bekannt, bei welcher ein Hochdruckturbinengehäuse mit einem Diffusorgehäuse an nach außen gerichteten Flanschen verbunden ist. A gas turbine is known from EP 3 103 972 A1, in which a high-pressure turbine housing is connected to a diffuser housing on outwardly directed flanges.
Aus der EP 1 273 760 A1 ist ein Turbolader bekannt, bei welchem zwischen einer Turbineneinlaufspirale und einem einen kreisförmigen Durchgang definierenden Turbinendüsenring Dichtmittel angeordnet sind. From EP 1 273 760 A1 a turbocharger is known in which sealing means are arranged between a turbine inlet spiral and a turbine nozzle ring defining a circular passage.
Ein typischer Turbolader weist ein Turbinengehäuse, ein Lagergehäuse und ein Verdichtergehäuse auf, wobei das Turbinengehäuse mit dem Lagergehäuse und das Lagergehäuse des Weiteren mit dem Verdichtergehäuse verbunden ist. Die Verbindung zwischen dem Turbinengehäuse und dem Lagergehäuse muss mehrere Anforderungen erfüllen. Zu diesen Anforderungen gehören eine Gewährleistung von Gasdichtheit, eine Verhinderung einer Verdrehung zwischen den beiden Gehäusen aufgrund äußerer Kräfte und eine Gewährleistung des Zusammenhalts der beiden Gehäuse auch in einem Berstfall. Um diese Anforderungen erfüllen zu können muss die Verbindung zwischen dem Turbinengehäuse und dem Lagergehäuse insbesondere derart ausgebildet sein, dass sie großen Temperaturunterschieden zwischen dem Turbinengehäuse und dem Lagergehäuse und hohen Kräften in einem Berstfall gerecht wird. Eine zuverlässige Sicherheitsumschliessung - im Englischen „Containment“ genannt - ist in einem solchen Berstfall eine sehr wichtige und daher konstruktiv sehr anspruchsvolle Anforderung an eine Abgasturbine. A typical turbocharger has a turbine housing, a bearing housing and a compressor housing, the turbine housing being connected to the bearing housing and the bearing housing also being connected to the compressor housing. The connection between the turbine housing and the bearing housing must meet several requirements. These requirements include ensuring gas tightness, preventing twisting between the two housings due to external forces and ensuring that the two housings are held together even in the event of a burst. In order to be able to meet these requirements, the connection between the turbine housing and the bearing housing must in particular be designed in such a way that it can cope with large temperature differences between the turbine housing and the bearing housing and high forces in the event of a burst. A reliable safety enclosure - called "containment" in English - is a very important and therefore structurally very demanding requirement for an exhaust gas turbine in such a burst.
Es ist bereits bekannt, ein Turbinengehäuse mit einem Lagergehäuse unter Verwendung eines Klemmringes zu verbinden, der einen Endabschnitt eines Flansches des Turbinengehäuses mit einem am Endabschnitt des Flansches des Turbinengehäuses anliegenden Endabschnitt eines Flansches des Lagergehäuses verbindet. Eine derartige Klemmringverbindung kommt insbesondere bei Turboladern mit vergleichsweise geringen Leistungen zum Einsatz. Ein Nachteil einer derartigen Klemmringverbindung besteht darin, dass sie den Zusammenhalt der Gehäuse beim Auftreten eines Berstfalles, bei welchem hohe Kräfte wirksam werden, nicht gewährleisten können. It is already known to connect a turbine housing to a bearing housing using a clamping ring which connects an end portion of a flange of the turbine housing to an end portion of a flange of the bearing housing bearing against the end portion of the flange of the turbine housing. Such a clamping ring connection is used in particular in turbochargers with comparatively low outputs. A disadvantage of such a clamping ring connection is that it cannot guarantee the cohesion of the housing in the event of a bursting event in which high forces become effective.
Bei Turboladern mit größerer Leistung, beispielsweise mit mehr als 500 KW Motorleistung pro Turbolader, hat sich in der Praxis eine Verbindung des Turbinengehäuses mit dem Lagergehäuse unter Verwendung eines mit Klemmlaschen ausgestatteten Flansches des Turbinengehäuses durchgesetzt. Durch diese Klemmlaschen sind beispielsweise Schrauben geführt, die in Gewindebohrungen des Turbinengehäuses eingedreht sind und die genannten Klemmlaschen an das Turbinengehäuse und das daran angrenzende Lagergehäuse pressen, wodurch auch das Lagergehäuse an das Turbinengehäuse gepresst wird. Bei Verwendung eines derartigen Klemmlaschenflansches wird aufgrund der starken Kräfte beim Auftreten eines Berstfalles eine vergleichsweise große Eindringtiefe der Schrauben in das Turbinengehäuse benötigt. Um diese große Eindringtiefe der Schrauben bereitstellen zu können ist es notwendig, die Dicke des Verbindungsflansches des Turbinengehäuses entsprechend groß zu dimensionieren. Diese große Dicke des Verbindungsflansches erhöht einerseits die Steifigkeit des Verbindungsflansches, bewirkt aber andererseits eine vergleichsweise langsame und auch ungleichmäßige Erhitzung des Verbindungsflansches des Turbinengehäuses. Dadurch erhöhen sich die thermisch transienten Spannungen im Turbinengehäuse, insbesondere im Bereich des Verbindungsflansches, aber auch im Bereich der Zunge des Turbinengehäuses. Die höheren thermisch transienten Spannungen führen wiederum zu einer reduzierten Lebensdauer des Turbinengehäuses und damit auch des gesamten Turboladers. In the case of turbochargers with greater power, for example with more than 500 KW engine power per turbocharger, a connection of the turbine housing to the bearing housing using a flange of the turbine housing equipped with clamping lugs has become established in practice. Screws, for example, which are screwed into threaded bores in the turbine housing and press said clamping lugs against the turbine housing and the bearing housing adjoining it, for example, thereby pressing the bearing housing against the turbine housing, are passed through these clamping lugs. When using such a clamping bracket flange, a comparatively large penetration depth of the screws into the turbine housing is required due to the strong forces when a burst occurs. To this great depth of penetration In order to be able to provide screws, it is necessary to dimension the thickness of the connecting flange of the turbine housing to be correspondingly large. This great thickness of the connecting flange on the one hand increases the rigidity of the connecting flange, but on the other hand causes a comparatively slow and also uneven heating of the connecting flange of the turbine housing. This increases the thermal transient stresses in the turbine housing, in particular in the area of the connecting flange, but also in the area of the tongue of the turbine housing. The higher thermal transient stresses in turn lead to a reduced service life of the turbine housing and thus also of the entire turbocharger.
Die Figur 1 zeigt eine erste Schnittdarstellung zur Veranschaulichung eines Turbinengehäuses nach dem Stand der Technik. Dieses Turbinengehäuse weist einen Verbindungflansch 2 auf, über welchen das Turbinengehäuse 1 mit dem Lagergehäuse 14 eines Turboladers verbunden ist. Diese Verbindung ist unter Verwendung von in Gehäuseverbindungsbohrungen des Verbindungsflansches eingedrehten Verbindungselementen realisiert, welche mittels Muttern 17 Klemmlaschen 16 auf den Verbindungsflansch 2 des Turbinengehäuses 1 und auf das Lagergehäuse 14 pressen, wodurch des Weiteren das Lagergehäuse 14 an das Turbinengehäuse gepresst wird. Die genannten Gehäuseverbindungsbohrungen sind voneinander beabstandet (das heisst räumlich voneinander entfernt) und sind in Umfangsrichtung entlang eines Kreises angeordnet. Die Klemmlaschen sind ebenfalls in Umfangsrichtung des Turbinengehäuses entlang eines Kreises angeordnet. Da - wie oben ausgeführt- die Anforderungen an die Verbindung zwischen dem Turbinengehäuse und dem Lagergehäuse hoch sind, muss die Eindringtiefe der Verbindungselemente in den Verbindungsflansch groß sein. Dies wiederum erfordert eine vergleichsweise große Flanschdicke 19 des Verbindungsflansches 2 im Bereich der Verbindung von Turbinengehäuse und Lagergehäuse. FIG. 1 shows a first sectional view to illustrate a turbine housing according to the prior art. This turbine housing has a connecting flange 2, via which the turbine housing 1 is connected to the bearing housing 14 of a turbocharger. This connection is implemented using connecting elements screwed into the housing connecting bores of the connecting flange, which press clamping lugs 16 onto the connecting flange 2 of the turbine housing 1 and onto the bearing housing 14 by means of nuts 17, whereby the bearing housing 14 is also pressed against the turbine housing. The mentioned housing connection bores are spaced from one another (that is to say spatially apart from one another) and are arranged in the circumferential direction along a circle. The clamping lugs are also arranged along a circle in the circumferential direction of the turbine housing. Since - as stated above - the requirements for the connection between the turbine housing and the bearing housing are high, the depth of penetration of the connecting elements into the connecting flange must be great. This in turn requires a comparatively large flange thickness 19 of the connecting flange 2 in the area of the connection between the turbine housing and the bearing housing.
Die Figur 2 zeigt eine zweite Schnittdarstellung zur Veranschaulichung eines Turbinengehäuses nach dem Stand der Technik. Diese zweite Schnittdarstellung veranschaulicht das Turbinengehäuse an einer Schnittstelle, an welcher ein Verbindungselement 15 in eine Gehäuseverbindungsbohrung 3 des Verbindungsflansches 2 des Turbinengehäuses eingedreht ist. Auch aus der Figur 2 ist ersichtlich, dass eine Klemmlasche 16 sowohl auf das Turbinengehäuse 2 als auch auf das Lagergehäuse 14 gepresst wird, was unter Verwendung einer Mutter 17 und einer Unterlagscheibe 18 realisiert ist. FIG. 2 shows a second sectional view to illustrate a turbine housing according to the prior art. This second sectional illustration illustrates the turbine housing at an interface at which a connecting element 15 is screwed into a housing connecting bore 3 of the connecting flange 2 of the turbine housing. Also from FIG. 2 It can be seen that a clamping lug 16 is pressed both onto the turbine housing 2 and onto the bearing housing 14, which is implemented using a nut 17 and a washer 18.
Aufgabe der Erfindung Object of the invention
Die Aufgabe der Erfindung besteht darin, ein Turbinengehäuse und eine Abgasturbine anzugeben, bei welchen die oben anhand eines Turboladers genannten Nachteile reduziert sind. The object of the invention is to provide a turbine housing and an exhaust gas turbine in which the disadvantages mentioned above with reference to a turbocharger are reduced.
Kurze Darstellung der Erfindung Summary of the invention
Diese Aufgabe wird durch ein Turbinengehäuse mit den im Anspruch 1 angegebenen Merkmalen bzw. eine Abgasturbine mit den im Anspruch 1 1 angegebenen Merkmalen gelöst. This object is achieved by a turbine housing with the features specified in claim 1 or an exhaust gas turbine with the features specified in claim 11.
Ein derartiges Turbinengehäuse weist einen Verbindungsflansch zur lagergehäuseseitigen Anbindung an ein Lagergehäuse hin auf, in welchem in Umfangsrichtung voneinander beabstandete Gehäuseverbindungsbohrungen vorgesehen sind, wobei zwischen einander benachbarten Gehäuseverbindungsbohrungen radial nach innen in Richtung zu einer Längsmittelachse des Turbinengehäuses geöffnete Materialaussparungen im Verbindungsflansch vorgesehen sind. Je nach Ausführungsform und Anforderungen kann das Turbinengehäuse dabei auch mehrteilig sein. Je nach Anforderungen kann zwischen dem Turbinengehäuse und dem Lagergehäuse ein Hitzeschild oder ein Düsenring angeordnet sein. A turbine housing of this type has a connecting flange for connection on the bearing housing side to a bearing housing, in which housing connecting bores spaced apart from one another in the circumferential direction are provided, with material recesses in the connecting flange being provided between adjacent housing connecting bores radially inwardly towards a longitudinal center axis of the turbine housing. Depending on the embodiment and requirements, the turbine housing can also be in several parts. Depending on the requirements, a heat shield or a nozzle ring can be arranged between the turbine housing and the bearing housing.
In jedem Fall ist in dieser gesamten Beschreibung der Begriff“Bohrung“ funktionell zu interpretieren und nicht herstellungsbedingt auf eine mechanische Bearbeitung mittels einer Bohrmaschine oder Fräsmaschine. In any case, in this entire description, the term “drilling” is to be interpreted functionally and not, due to manufacturing reasons, to mechanical processing using a drilling machine or milling machine.
Gemäß einer Ausführungsform der Erfindung sind die voneinander beabstandeten Gehäuseverbindungsbohrungen im Verbindungsflansch entlang mindestens eines Kreises angeordnet. Gemäß einer Ausführungsform der Erfindung weist das Turbinengehäuse einen Klemmrand auf, der den Gehäuseverbindungsbohrungen in Radialrichtung benachbart angeordnet ist. According to one embodiment of the invention, the spaced apart housing connecting bores in the connecting flange are arranged along at least one circle. According to one embodiment of the invention, the turbine housing has a clamping edge which is arranged adjacent to the housing connecting bores in the radial direction.
Gemäß einer Ausführungsform der Erfindung ist im Klemmrand eine ringförmige Vertiefung vorgesehen, die einen Vertiefungsboden aufweist, wobei die benachbarten Gehäuseverbindungsbohrungen in den Vertiefungsboden eingebracht sind und wobei die zwischen jeweils zwei benachbarten Gehäuseverbindungsbohrungen vorgesehenen Materialaussparungen im Vertiefungsboden vorgesehen sind. According to one embodiment of the invention, an annular recess is provided in the clamping edge, which has a recess base, the adjacent housing connection bores being made in the recess base and the material recesses provided between two adjacent housing connection bores being provided in the recess base.
Gemäß einer Ausführungsform der Erfindung weist der Klemmrand im Bereich zwischen zwei benachbarten Gehäuseverbindungsbohrungen jeweils eine die ringförmige Vertiefung verbreiternde Klemmrandaussparung auf. According to one embodiment of the invention, the clamping edge in the area between two adjacent housing connecting bores each has a clamping edge recess that widens the annular recess.
Gemäß einer Ausführungsform der Erfindung stimmt die Tiefe der Klemmrandaussparung mit der Summe der Tiefe der ringförmigen Vertiefung und der Tiefe der in der ringförmigen Vertiefung vorgesehenen Materialaussparungen überein. According to one embodiment of the invention, the depth of the clamping edge recess corresponds to the sum of the depth of the annular recess and the depth of the material recesses provided in the annular recess.
Gemäß einer Ausführungsform der Erfindung ist das Turbinengehäuse mehrstückig ausgebildet. According to one embodiment of the invention, the turbine housing is constructed in several pieces.
Gemäß einer Ausführungsform der Erfindung bildet der Klemmrand ein separates Teil des Turbinengehäueses. According to one embodiment of the invention, the clamping edge forms a separate part of the turbine housing.
Gemäß einer Ausführungsform der Erfindung bildet ein Hitzeschild oder ein Düsenring ein separates Teil des Turbinengehäuses. According to one embodiment of the invention, a heat shield or a nozzle ring forms a separate part of the turbine housing.
Gemäß einer Ausführungsform der Erfindung ist der Klemmrand Bestandteil des Hitzeschildes oder des Düsenringes. According to one embodiment of the invention, the clamping edge is part of the heat shield or the nozzle ring.
Gemäß einer Ausführungsform der Erfindung weist eine Abgasturbine ein Turbinengehäuse mit den erfindungsgemäßen Merkmalen auf. According to one embodiment of the invention, an exhaust gas turbine has a turbine housing with the features according to the invention.
Gemäß einer Ausführungsform der Erfindung weist eine Abgasturbine ein mit dem Turbinengehäuse verbundenes Lagergehäuse auf, wobei das Turbinengehäuse mit dem Lagergehäuse mittels Verbindungselementen verbunden ist. According to one embodiment of the invention, an exhaust gas turbine has a bearing housing connected to the turbine housing, the turbine housing being connected to the bearing housing by means of connecting elements.
Gemäß einer Ausführungsform der Erfindung weist eine Abgasturbine Klemmelemente auf, die jeweils von einem Verbindungselement oder von mehreren Verbindungselementen an den Verbindungsflansch des Turbinengehäuses und an das Lagergehäuse gepresst sind. According to one embodiment of the invention, an exhaust gas turbine has clamping elements, each of which is formed by a connecting element or by several Connecting elements are pressed to the connecting flange of the turbine housing and to the bearing housing.
Gemäß einer Ausführungsform der Erfindung sind die Klemmelemente der Abgasturbine an den Klemmrand gepresst. According to one embodiment of the invention, the clamping elements of the exhaust gas turbine are pressed against the clamping edge.
In einer sowohl konstruktiv als auch montagetechnisch einfachen Ausführungsform sind die Verbindungselemente Schrauben oder Gewindestifte. In an embodiment that is simple in terms of both construction and assembly, the connecting elements are screws or threaded pins.
Die Vorteile der Erfindung bestehen insbesondere darin, dass die zwischen den Gehäuseverbindungsbohrungen vorgesehenen Materialaussparungen im Betrieb der jeweiligen Abgasturbine eine schnellere und gleichmäßigere Aufwärmung des Verbindungsflanschbereiches ermöglichen. Aufgrund dieser Materialaussparungen liegt des Weiteren im Bereich des Verbindungsflansches eine reduzierte Steifigkeit des Turbinengehäuses vor. Dadurch treten im Betrieb der Abgasturbine geringere thermisch-transiente Spannungen auf. Dies wiederum führt zu einer Verlängerung der Lebensdauer des Turbinengehäuses und damit auch zu einer Verlängerung der Lebensdauer der gesamten Abgasturbine. The advantages of the invention are in particular that the material recesses provided between the housing connecting bores enable the connecting flange area to be heated more quickly and more evenly during operation of the respective exhaust gas turbine. Due to these material cutouts, there is also a reduced rigidity of the turbine housing in the area of the connecting flange. As a result, lower thermal transient stresses occur when the exhaust gas turbine is in operation. This in turn leads to an extension of the service life of the turbine housing and thus also to an extension of the service life of the entire exhaust gas turbine.
Kurze Beschreibung der Zeichnungen Brief description of the drawings
Es zeigt: It shows:
Figur 1 eine erste Schnittdarstellung zur Veranschaulichung eines Figure 1 is a first sectional view to illustrate a
Turbinengehäuses nach dem Stand der Technik, State-of-the-art turbine housing,
Figur 2 eine zweite Schnittdarstellung zur Veranschaulichung eines Figure 2 is a second sectional view to illustrate a
Turbinengehäuses nach dem Stand der Technik, State-of-the-art turbine housing,
Figur 3 eine Skizze zur Veranschaulichung eines erfindungsgemäßen Figure 3 is a sketch to illustrate an inventive
Turbinengehäuses, Turbine housing,
Figur 4 eine Schnittdarstellung in Radialrichtung zur Veranschaulichung einer Figure 4 is a sectional view in the radial direction to illustrate a
Ausführungsform der Erfindung, Embodiment of the invention,
Figur 5 eine Schnittdarstellung gemäß der in der Figur 4 gezeigten Schnittlinie C-C, Figur 6 eine Skizze zur Veranschaulichung einer anderen Ausführungsform der FIG. 5 shows a sectional illustration according to the section line C-C shown in FIG. 4, FIG. 6 shows a sketch to illustrate another embodiment of FIG
Erfindung, Figur 7 eine Schnittdarstellung in Richtung der in der Figur 6 gezeigten Schnittlinie A-A, Invention, FIG. 7 shows a sectional illustration in the direction of the section line AA shown in FIG. 6,
Figur 8 eine Skizze zur Veranschaulichung einer weiteren Ausführungsform der Figure 8 is a sketch to illustrate a further embodiment of the
Erfindung und Invention and
Figur 9 eine Schnittdarstellung in Richtung der in der Figur 8 gezeigten Schnittlinie FIG. 9 shows a sectional illustration in the direction of the cutting line shown in FIG
B - B. B - B.
Detaillierte Beschreibung von Ausführungsbeispielen Detailed description of exemplary embodiments
Die Figur 3 zeigt eine Skizze zur Veranschaulichung eines erfindungsgemäßen Turbinengehäuses, wobei in der Figur 3 nur ein Teilbereich dieses Turbinengehäuses dargestellt ist. Das Turbinengehäuse weist einen koaxial zu einer Längsmittelachse des Turbinengehäuses angeordneten Verbindungsflansch 2 auf, welcher mit einem Klemmrand 7 ausgestattet ist. In diesem Klemmrand 7 sind sich in Radialrichtung 8 nach innen erstreckende Verbindungsstege 19 vorgesehen, in welche Gehäuseverbindungsbohrungen 3 eingebracht sind. Die genannten Verbindungsstege 19 und damit auch die in diese eingebrachten Gehäuseverbindungsbohrungen 3 sind in Umfangsrichtung 9 des Turbinengehäuses voneinander beabstandet. Sie sind im Verbindungsflansch in Umfangsrichtung 9 entlang eines oder mehrerer Kreise angeordnet. Zwischen jeweils zwei in Umfangsrichtung 9 voneinander beabstandeten Gehäuseverbindungsbohrungen 3 sind im Klemmrand 7 des Verbindungsflansches 2 radial nach innen geöffnete Materialaussparungen 4 vorgesehen. Diese Materialaussparungen 4 können durch eine Materialabtragung in den Klemmrand des Verbindungsflansches eingebracht werden oder bei einer Verwendung eines formgebenden Fertigungsverfahrens direkt modelliert werden. Die Geometrie der Materialaussparungen kann unterschiedlich gewählt werden. Beispielsweise können die Materialaussparungen halbrund, elliptisch, glockenförmig oder rechteckig ausgeführt sein. FIG. 3 shows a sketch to illustrate a turbine housing according to the invention, only a partial area of this turbine housing being shown in FIG. The turbine housing has a connecting flange 2 which is arranged coaxially to a longitudinal center axis of the turbine housing and which is equipped with a clamping edge 7. In this clamping edge 7, connecting webs 19 extending inward in the radial direction 8 are provided, in which housing connecting bores 3 are made. Said connecting webs 19 and thus also the housing connecting bores 3 introduced into them are spaced apart from one another in the circumferential direction 9 of the turbine housing. They are arranged in the connection flange in the circumferential direction 9 along one or more circles. Between two housing connection bores 3 spaced apart from one another in the circumferential direction 9, material recesses 4 which are open radially inward are provided in the clamping edge 7 of the connecting flange 2. These material recesses 4 can be introduced into the clamping edge of the connecting flange by material removal or, if a shaping manufacturing process is used, they can be modeled directly. The geometry of the material recesses can be selected differently. For example, the material recesses can be made semicircular, elliptical, bell-shaped or rectangular.
Eine Verbindung des Turbinengehäuses mit einem in der Figur 3 nicht dargestellten Lagergehäuse eines Turboladers erfolgt ebenso wie oben im Zusammenhang mit der Figur 2 erläutert wurde unter Verwendung von Verbindungselementen, die in jeweils eine Gehäuseverbindungsbohrung 3 des Verbindungsflansches 2 eingebracht sind, wobei des Weiteren in Umfangsrichtung des Turbinengehäuses entlang eines Kreises angeordnete Klemmelemente, bei denen es sich in einer Ausführungsform um Klemmlaschen handelt, sowohl auf das Turbinengehäuse als auch auf das Lagergehäuse gepresst werden, was jeweils unter Verwendung einer Mutter und einer Unterlagscheibe realisiert ist. A connection of the turbine housing to a bearing housing of a turbocharger (not shown in FIG. 3) takes place in the same way as was explained above in connection with FIG. 2 using connecting elements which are each introduced into a housing connecting bore 3 of the connecting flange 2, Furthermore, clamping elements arranged along a circle in the circumferential direction of the turbine housing, which in one embodiment are clamping lugs, are pressed onto both the turbine housing and the bearing housing, which is implemented using a nut and a washer.
Die im Unterschied zum Stand der Technik vorgesehenen Materialaussparungen 4 bewirken im Betrieb des Turboladers eine schnellere und gleichmäßigere Aufwärmung des Verbindungsflansches 2 des Turbinengehäuses. Des Weiteren liegt aufgrund der in den Verbindungsflansch 2 eingebrachten Materialaussparungen 4 eine reduzierte Steifigkeit des Turbinengehäuses im Bereich des Verbindungsflansches 2 vor. Dies wiederum hat zur Folge, dass im Bereich des Verbindungsflansches 2 im Vergleich zum Stand der Technik verringerte thermisch-transiente Spannungen auftreten. Durch diese Verringerung der therm ische-transienten Spannungen im Bereich des Verbindungsflansches werden die Lebensdauer des Turbinengehäuses und damit auch die Lebensdauer des gesamten Turboladers verlängert. The material recesses 4 provided in contrast to the prior art bring about faster and more uniform heating of the connecting flange 2 of the turbine housing when the turbocharger is in operation. Furthermore, due to the material cutouts 4 made in the connecting flange 2, there is a reduced rigidity of the turbine housing in the area of the connecting flange 2. This in turn has the consequence that in the area of the connecting flange 2, reduced thermal transient stresses occur in comparison with the prior art. This reduction in thermal transient stresses in the area of the connecting flange extends the service life of the turbine housing and thus also the service life of the entire turbocharger.
Die Figur 4 zeigt eine Schnittdarstellung in Radialrichtung zur Veranschaulichung einer Ausführungsform der Erfindung. Dargestellt sind der Verbindungsflansch 2 des Turbinengehäuses und das mit dem Verbindungsflansch 2 und damit mit dem Turbinengehäuse verbundene Lagergehäuse 14. Weiterhin ist aus der Figur 4 ersichtlich, dass in der dargestellten Schnittebene die Verbindung des Turbinengehäuses mit dem Lagergehäuse unter Verwendung einer Klemmlasche 16 realisiert ist. Diese Klemmlasche 16 wird auf den Verbindungsflansch 2 des Turbinengehäuses und auf das Lagergehäuse 14 gepresst. Diese Pressung ist unter Verwendung einer Mutter 17 und einer zwischen der Mutter 17 und der Klemmlasche 16 angeordneten Unterlagscheibe 18 realisiert. Ferner geht aus der Figur 4 hervor, dass durch diese Pressung das Lagergehäuse gegen den Verbindungsflansch 2 des Turbinengehäuses gepresst wird, da das Lagergehäuse 14 einen radial nach außen, d.h. in der Figur 4 nach oben, gerichteten Klemmrand aufweist, dessen Rückseite auf einen in Radialrichtung nach innen, d.h. in der Figur 4 nach unten, gerichteten Fortsatz des Verbindungsflansches 2 gepresst wird. Schließlich ist aus der Figur 4 auch eine der in der Figur 3 veranschaulichten Aussparungen 4 ersichtlich, welche im miteinander verbundenen Zustand des Turbinengehäuses mit dem Lagergehäuse in der gezeigten Schnittebene in Axialrichtung zwischen der Klemmlasche 16 und dem Verbindungsflansch 2 vorgesehen ist. FIG. 4 shows a sectional illustration in the radial direction to illustrate an embodiment of the invention. The connection flange 2 of the turbine housing and the bearing housing 14 connected to the connection flange 2 and thus to the turbine housing 14 are shown. Furthermore, it can be seen from FIG. 4 that the connection of the turbine housing to the bearing housing is realized using a clamping bracket 16 in the sectional plane shown. This clamping lug 16 is pressed onto the connecting flange 2 of the turbine housing and onto the bearing housing 14. This pressing is implemented using a nut 17 and a washer 18 arranged between the nut 17 and the clamping bracket 16. Furthermore, it can be seen from FIG. 4 that the bearing housing is pressed against the connecting flange 2 of the turbine housing by this pressing, since the bearing housing 14 has a clamping edge directed radially outward, ie upward in FIG. 4, the rear side of which faces a radial direction inward, ie in FIG. 4 downward, extension of the connecting flange 2 is pressed. Finally, one of the recesses 4 illustrated in FIG. 3 can also be seen from FIG. 4, which in the interconnected state of the turbine housing with the bearing housing in the section plane shown is provided in the axial direction between the clamping strap 16 and the connecting flange 2.
Die Figur 5 zeigt eine Schnittdarstellung gemäß der in der Figur 4 gezeigten Schnittlinie C-C. Aus dieser Darstellung ist insbesondere ersichtlich, dass zwischen jeweils zwei in Umfangsrichtung 9 voneinander beabstandeten Gehäuseverbindungsbohrungen 3, in welche Verbindungselemente 15 eingebracht sind, im Klemmrand 7 des Verbindungsflansches 2 des Turbinengehäuses Materialaussparungen 4 vorgesehen sind, die sich in der gezeigten Schnittebene in Radialrichtung 8 außerhalb des Lagergehäuses 14 befinden und radial nach innen geöffnet sind. FIG. 5 shows a sectional view according to the section line C-C shown in FIG. From this illustration it can be seen in particular that between each two housing connection bores 3 spaced apart from one another in the circumferential direction 9, in which connection elements 15 are introduced, material recesses 4 are provided in the clamping edge 7 of the connection flange 2 of the turbine housing, which in the sectional plane shown are in the radial direction 8 outside the Bearing housing 14 are located and are open radially inward.
Die Figur 6 zeigt eine Skizze zur Veranschaulichung einer anderen Ausführungsform der Erfindung. Bei dieser anderen Ausführungsform ist im radial inneren Randbereich des Klemmrandes 7 des Verbindungsflansches 2 des Turbinengehäuses eine ringförmige Vertiefung 5 vorgesehen, die sich in Umfangrichtung 9 über den gesamten Umfang des Turbinengehäuses erstreckt. Diese ringförmige Vertiefung 5 weist einen Vertiefungsboden 6 auf. FIG. 6 shows a sketch to illustrate another embodiment of the invention. In this other embodiment, an annular recess 5 is provided in the radially inner edge area of the clamping edge 7 of the connecting flange 2 of the turbine housing, which extends in the circumferential direction 9 over the entire circumference of the turbine housing. This annular recess 5 has a recess bottom 6.
Bei dieser Ausführungsform der Erfindung sind die in Umfangsrichtung 9 voneinander beabstandeten Gehäuseverbindungsbohrungen 3 in den Vertiefungsboden 6 der ringförmigen Vertiefung 5 eingebracht. In this embodiment of the invention, the housing connecting bores 3, which are spaced apart from one another in the circumferential direction 9, are introduced into the recess bottom 6 of the annular recess 5.
Des Weiteren sind bei dieser Ausführungsform die zwischen jeweils zwei benachbarten Gehäuseverbindungsbohrungen 3 vorgesehenenFurthermore, in this embodiment, the two adjacent housing connection bores 3 are provided
Materialaussparungen 4 ebenfalls in den Vertiefungsboden 6 der ringförmigen Vertiefung 5 eingebracht. Diese Materialaussparungen 4 erstrecken sich in Radialrichtung 8 über den gesamten Vertiefungsboden 6. Material recesses 4 also made in the recess bottom 6 of the annular recess 5. These material recesses 4 extend in the radial direction 8 over the entire recess base 6.
Durch das Einbringen der Gehäuseverbindungsbohrungen 3 und der Materialaussparungen 4 in den Vertiefungsboden 6 der ringförmigen Vertiefung 5 wird die Dicke des Verbindungsflansches 2 des Turbinengehäuses im Verbindungsbereich des Turbinengehäuses mit dem Lagergehäuse und damit die im Betrieb des Turboladers auftretenden thermisch-transienten Spannungen im Verbindungsflansch 2 weiter reduziert. Die Figur 7 zeigt eine Schnittdarstellung in Richtung der in der Figur 6 gezeigten Schnittlinie A - A. In dieser Figur 7 ist die Tiefe der in den Vertiefungsboden 6 eingebrachten Gehäuseverbindungsbohrungen 3 mit der Bezugszahl 12 bezeichnet. Des Weiteren ist ersichtlich, dass bei dieser Ausführungsform die Tiefe der Materialaussparungen 4 mit der Tiefe 12 der in den Vertiefungsboden 6 eingebrachten Gehäuseverbindungsbohrungen 3 übereinstimmt. Gemäß anderer Ausführungsformen kann sich die Tiefe der Materialaussparungen 4 auch von der Tiefe der Gehäuseverbindungsbohrungen 3 unterscheiden. Die Tiefe der ringförmigen Vertiefung 5 ist mit der Bezugszahl 1 1 bezeichnet. Die Summe der Tiefe 1 1 der ringförmigen Vertiefung und der Tiefe 12 der in den Vertiefungsboden eingebrachten Gehäuseverbindungsbohrungen ist mit der Bezugszahl 20 bezeichnet. By making the housing connection bores 3 and the material recesses 4 in the recess bottom 6 of the annular recess 5, the thickness of the connecting flange 2 of the turbine housing in the connecting area of the turbine housing with the bearing housing and thus the thermal-transient stresses occurring in the connecting flange 2 during operation of the turbocharger are further reduced . FIG. 7 shows a sectional illustration in the direction of the section line AA shown in FIG. 6. In this FIG. 7, the depth of the housing connecting bores 3 made in the recess base 6 is designated by the reference number 12. Furthermore, it can be seen that, in this embodiment, the depth of the material recesses 4 corresponds to the depth 12 of the housing connecting bores 3 made in the recess base 6. According to other embodiments, the depth of the material recesses 4 can also differ from the depth of the housing connecting bores 3. The depth of the annular recess 5 is denoted by the reference number 11. The sum of the depth 1 1 of the annular recess and the depth 12 of the housing connecting bores made in the recess base is denoted by the reference number 20.
Die Figur 8 zeigt eine Skizze zur Veranschaulichung einer weiteren Ausführungsform der Erfindung. Bei dieser weiteren Ausführungsform ist wiederum im radial inneren Randbereich des Klemmrandes 7 des Verbindungsflansches 2 des Turbinengehäuses eine ringförmige Vertiefung 5 vorgesehen, die sich in Umfangsrichtung 9 über den gesamten Umfang des Turbinengehäuses erstreckt. In den Vertiefungsboden 6 der ringförmigen Vertiefung 5 sind wiederum in Umfangsrichtung 9 voneinander beabstandete Gehäuseverbindungsbohrungen 3 eingebracht, zwischen denen sich die Materialaussparungen 4 befinden. Diese Aussparungen 4 sind in Radialrichtung 8 nach innen geöffnet und erstrecken sich bis in den Bereich des Klemmrandes 7. Folglich weist bei dieser Weiterbildung der Klemmrand 7 Klemmrandaussparungen 10 auf, die jeweils zwischen zwei einander benachbarten Gehäuseverbindungsbohrungen 3 vorgesehen sind. Diese Klemmrandaussparungen 10 erstrecken sich beim gezeigten Ausführungsbeispiel in Radialrichtung 8 durch den gesamten Klemmrand 7. FIG. 8 shows a sketch to illustrate a further embodiment of the invention. In this further embodiment, an annular recess 5 is again provided in the radially inner edge region of the clamping edge 7 of the connecting flange 2 of the turbine housing, which extends in the circumferential direction 9 over the entire circumference of the turbine housing. Housing connection bores 3 spaced apart from one another in the circumferential direction 9, between which the material recesses 4 are located, are again made in the recess bottom 6 of the annular recess 5. These recesses 4 are open inward in the radial direction 8 and extend into the area of the clamping edge 7. Consequently, in this development, the clamping edge 7 has clamping edge recesses 10, which are each provided between two adjacent housing connection bores 3. In the exemplary embodiment shown, these clamping edge recesses 10 extend in the radial direction 8 through the entire clamping edge 7.
Die Figur 9 zeigt eine Schnittdarstellung in Richtung der in der Figur 8 gezeigten Schnittlinie B - B. Gemäß dieser Figur 9 weist die im Klemmrand 7 vorgesehene Klemmrandaussparung 10 eine erste Tiefe 20 auf. Die ringförmige Vertiefung 5 weist eine zweite Tiefe 1 1 auf. Die in den Vertiefungsboden 6 eingebrachten Gehäuseverbindungsbohungen 3 weisen eine dritte Tiefe 12 auf. Die erste Tiefe 20 der Klemmrandaussparung 10 stimmt beim gezeigten Ausführungsbeispiel mit der Summe der zweiten Tiefe 1 1 der ringförmigen Vertiefung 5 und der dritten Tiefe 12 der in der ringförmigen Vertiefung 5 vorgesehenen Gehäuseverbindungsbohrung 3 überein. Die Tiefen 20, 1 1 und 12 erstrecken sich jeweils in Axialrichtung 13 des Turbinengehäuses. FIG. 9 shows a sectional illustration in the direction of the section line BB shown in FIG. 8. According to this FIG. 9, the clamping edge recess 10 provided in the clamping edge 7 has a first depth 20. The annular recess 5 has a second depth 11. The housing connection bores 3 made in the recess bottom 6 have a third depth 12. The first depth 20 of the clamping edge recess 10 agrees with the embodiment shown Sum of the second depth 1 1 of the annular recess 5 and the third depth 12 of the housing connecting bore 3 provided in the annular recess 5. The depths 20, 11 and 12 each extend in the axial direction 13 of the turbine housing.
Im Folgenden werden bevorzugte allgemeine Aspekte der Erfindung beschrieben, wobei sich die Bezugszeichen auf alle vorgenannten Ausführungsformen beziehen, das Gesagte jedoch auf keine einzelne Ausführungsform beschränkt ist, sondern vielmehr mit beliebigen Ausführungsformen und Aspekten kombinierbar ist. Preferred general aspects of the invention are described below, the reference symbols referring to all of the aforementioned embodiments, but what has been said is not limited to any single embodiment, but rather can be combined with any desired embodiments and aspects.
Gemäß einem Aspekt ist aufgrund der in den Verbindungsflansch 2 zusätzlich zu den Gehäuseverbindungsbohrungen 3 eingebrachten Aussparungen 4 bzw. 10 die Flanschdicke 19 des Verbindungsflansches 2 reduziert, so dass im Vergleich zum Stand der Technik die im Verbindungsflansch 2 auftretenden thermisch-transienten Spannungen reduziert sind, was zu einer verlängerten Lebensdauer des Turbinengehäuses und damit des gesamten Turboladers führt. Dieser Turbolader weist ein Turbinengehäuse auf, wie es vorstehend erläutert wurde. According to one aspect, due to the recesses 4 and 10 made in the connecting flange 2 in addition to the housing connecting bores 3, the flange thickness 19 of the connecting flange 2 is reduced, so that the thermal transient stresses occurring in the connecting flange 2 are reduced compared to the prior art, which leads to an extended service life of the turbine housing and thus of the entire turbocharger. This turbocharger has a turbine housing, as has been explained above.
Gemäß einem weiteren Aspekt weist dieser Turbolader ein mit dem Turbinengehäuse verbundenes Lagergehäuse auf, wobei das Turbinengehäuse mit dem Lagergehäuse mittels in die Gehäuseverbindungsbohrungen 3 des Turbinengehäuses eingebrachter Verbindungselemente 15 verbunden ist, bei denen es sich beispielsweise um Schrauben oder Gewindestifte handelt. According to a further aspect, this turbocharger has a bearing housing connected to the turbine housing, the turbine housing being connected to the bearing housing by means of connecting elements 15 introduced into the housing connection bores 3 of the turbine housing, which are for example screws or threaded pins.
Gemäß einem weiteren Aspekt weist der Turbolader als Klemmlaschen 16 realisierte Klemmelemente auf, die jeweils von einem oder mehreren Verbindungselementen an den Verbindungsflansch 2 des Turbinengehäuses und an das Lagergehäuse 14 gepresst sind. Die Klemmelemente sind dabei an einen Klemmrand des Verbindungsflansches gepresst. An Stelle von Klemm laschen können auch beispielsweise Klemmscheiben oder Klemmringe verwendet werden. Die Klemmelemente sind vorzugsweise zumindest geringfügig elastisch ausgebildet, um beim Anziehen der Muttern zumindest geringfügig nachgeben zu können. Gemäß einem weiteren Aspekt sind die voneinander beabstandetenAccording to a further aspect, the turbocharger has clamping elements implemented as clamping lugs 16, which are each pressed by one or more connecting elements onto the connecting flange 2 of the turbine housing and onto the bearing housing 14. The clamping elements are pressed against a clamping edge of the connecting flange. Instead of clamping tabs, clamping disks or clamping rings can also be used, for example. The clamping elements are preferably designed to be at least slightly elastic in order to be able to yield at least slightly when the nuts are tightened. According to a further aspect, the spaced apart
Gehäuseverbindungsbohrungen 3 im Verbindungsflansch 2 in Umfangsrichtung entlang mindestens eines Kreises, bevorzugt höchstens dreier oder höchstens zweier (zueinander und/oder zur Turbinenachse konzentrischer) Kreise angeordnet und erstrecken sich entlang des gesamten mindestens einen Kreises, vorzugsweise über den gesamten Kreisumfang in regelmäßigen Abständen verteilt. Die Anzahl an erforderlichen Gehäuseverbindungsbohrungen richtet sich nach den Festigkeitsanforderungen bei einem Schadenfall (Containment) und den Dichtigkeitsanforderungen. Housing connection bores 3 arranged in the connection flange 2 in the circumferential direction along at least one circle, preferably at most three or at most two (concentric to each other and / or to the turbine axis) and extend along the entire at least one circle, preferably distributed over the entire circumference at regular intervals. The number of housing connection holes required depends on the strength requirements in the event of damage (containment) and the tightness requirements.
Gemäß einem weiteren Aspekt können die voneinander beabstandetenAccording to a further aspect, the spaced apart
Gehäuseverbindungsbohrungen 3 im Verbindungsflansch 2 in Umfangsrichtung auch entlang zweier oder mehrerer Kreise angeordnet sein, wobei beispielsweise jede zweite Gehäuseverbindungsbohrung 3 entlang eines ersten Kreises angeordnet ist und jede dazwischenliegende Gehäuseverbindungsbohrung 3 entlang eines zweiten Kreises angeordnet ist. Housing connection bores 3 in the connection flange 2 can also be arranged in the circumferential direction along two or more circles, with, for example, every second housing connection bore 3 being arranged along a first circle and each housing connection bore 3 lying in between being arranged along a second circle.
Gemäß einem Aspekt weist der Flansch mindestens fünf Gehäuseverbindungsbohrungen 3 und/oder mindestens zwei, vorzugsweise mindestens vier, besonders bevorzugt mindestens fünf der Materialaussparungen 4 zwischen einander benachbarten Gehäuseverbindungsbohrungen 3 auf. According to one aspect, the flange has at least five housing connection bores 3 and / or at least two, preferably at least four, particularly preferably at least five of the material recesses 4 between adjacent housing connection bores 3.
Gemäß einem weiteren Aspekt sind zwischen allen Gehäuseverbindungsbohrungen 3 Materialaussparungen 4 vorgesehen. Die Materialaussparungen 4 sind radial nach innen geöffnet. Die Materialaussparungen 4 sind vorzugsweise in axialer Richtung durch eine (z.B. ringförmige) Rückseite des Verbindungsflansches abgeschlossen, sind also in axialer Richtung nicht durchgängig. According to a further aspect, 3 material recesses 4 are provided between all housing connecting bores. The material recesses 4 are open radially inward. The material recesses 4 are preferably closed in the axial direction by a (e.g., ring-shaped) rear side of the connecting flange, so they are not continuous in the axial direction.
Alternativ dazu können Materialaussparungen 4 nicht zwischen allen Gehäuseverbindungsbohrungen 3 vorgesehen sein, sondern nur dort, wo der Einfluss auf die Lebensdauer relevant ist, beispielsweise im Bereich des Eintrittes in die Spirale. Gemäß einem Aspekt ist der Flansch koaxial zur Längsmittelache des Turbinengehäuses angeordnet. As an alternative to this, material recesses 4 cannot be provided between all the housing connecting bores 3, but only where the influence on the service life is relevant, for example in the area of the entry into the spiral. According to one aspect, the flange is arranged coaxially to the longitudinal center axis of the turbine housing.
Gemäß einem weiteren Aspekt ist der Flansch zu einem Lagergehäuse der Abgasturbine hin ausgerichtet bzw. für die Verbindung des Turbinengehäuses mit dem Lagergehäuse angeordnet (optional mit einem Teil eines Hitzeschilds und/oder eines Diffusorrings zwischen dem Flansch und dem entsprechenden Teil des Lagergehäuses). According to a further aspect, the flange is oriented towards a bearing housing of the exhaust gas turbine or is arranged for the connection of the turbine housing to the bearing housing (optionally with part of a heat shield and / or a diffuser ring between the flange and the corresponding part of the bearing housing).
Gemäß einem Aspekt hat die Aussparung 4 eine Bogenlänge in Umfangsrichtung von mehr als dem halben Abstand zwischen den Zentren der beiden Gehäuseverbindungsbohrungen 3. According to one aspect, the recess 4 has an arc length in the circumferential direction of more than half the distance between the centers of the two housing connection bores 3.
Gemäß einem Aspekt weist der Verbindungsflansch 2 Verbindungsstege 19 auf, welche die Gehäuseverbindungsbohrungen 3 zumindest abschnittsweise unmittelbar umgeben und welche in Umfangsrichtung zwischen den benachbarten Gehäuseverbindungsbohrungen 3 und der dazwischenliegenden Materialaussparung 4 angeordnet sind. According to one aspect, the connecting flange 2 has connecting webs 19 which directly surround the housing connecting bores 3 at least in sections and which are arranged in the circumferential direction between the adjacent housing connecting bores 3 and the material recess 4 lying between them.
Gemäß einem Aspekt weist der Verbindungsflansch 2 einen Klemmrand 7 auf, der den Gehäuseverbindungsbohrungen 3 in Radialrichtung 8 benachbart angeordnet ist. According to one aspect, the connection flange 2 has a clamping edge 7 which is arranged adjacent to the housing connection bores 3 in the radial direction 8.
Gemäß einem Aspekt verlaufen die Verbindungsstege 19 ausgehend von dem Klemmrand 7 radial nach innen. Der Klemmrand kann als separates Teil des Turbinengehäuses vorgesehen sein oder einstückig mit dem übrigen Turbinengehäuse bzw. Verbindungsflansch vorgesehen sein. According to one aspect, the connecting webs 19 run radially inward, starting from the clamping edge 7. The clamping edge can be provided as a separate part of the turbine housing or be provided in one piece with the rest of the turbine housing or connecting flange.
Gemäß einem Aspekt kann das Turbinengehäuse mehrstückig ausgebildet sein. In diesem Fall kann ein Hitzeschild oder ein Düsenring ein separates Teil des Turbinengehäuses bilden. Der Klemmrand des Turbinengehäuses kann in diesem Fall Teil des Hitzeschildes oder des Düsenrings sein, d.h. in das Hitzeschild oder den Düsenring integriert sein. Gemäß einem Aspekt sind die Verbindungsstege gegenüber dem Klemmrand 7 in axialer Richtung vertieft angeordnet. Mit anderen Worten steht der Klemmrand (z.B. um weniger als 1 mm oder sogar um höchstens 0,5 mm und/oder um mehr als 0,1 mm) in axialer Richtung über die Verbindungsstege hervor (z.B. in Richtung weg von dem Turbinengehäuse bzw. hin zu dem Lagergehäuse der Abgasturbine). Demnach bilden die Verbindungsstege einen Teil eines Vertiefungsbodens. Gemäß einem Aspekt sind die zwischen jeweils zwei benachbarten Gehäuseverbindungsbohrungen vorgesehenen Materialaussparungen 4 gegenüber den Verbindungsstegen noch weiter in axialer Richtung vertieft angeordnet. According to one aspect, the turbine housing can be designed in several pieces. In this case, a heat shield or a nozzle ring can form a separate part of the turbine housing. In this case, the clamping edge of the turbine housing can be part of the heat shield or the nozzle ring, ie it can be integrated into the heat shield or the nozzle ring. According to one aspect, the connecting webs are arranged recessed relative to the clamping edge 7 in the axial direction. In other words, the clamping edge protrudes (for example by less than 1 mm or even by at most 0.5 mm and / or by more than 0.1 mm) in the axial direction beyond the connecting webs (for example in the direction away from the turbine housing or towards to the bearing housing of the exhaust gas turbine). Accordingly, the connecting webs form part of a recess bottom. According to one aspect, the material recesses 4 provided between each two adjacent housing connection bores are arranged so as to be deeper than the connection webs in the axial direction.
Gemäß einem Aspekt kann der Klemmrand in Umfangsrichtung durchgehend (unterbrechungsfrei) verlaufen oder Aussparungen aufweisen. According to one aspect, the clamping edge can run continuously (without interruption) in the circumferential direction or have recesses.
Gemäß einem Aspekt weist der Verbindungsflansch 2 eine ringförmige Vertiefung 5 auf, die einen Vertiefungsboden 6 aufweist. According to one aspect, the connecting flange 2 has an annular recess 5 which has a recess bottom 6.
Gemäß einem Aspekt sind die benachbarten Gehäuseverbindungsbohrungen 3 in den Vertiefungsboden eingebracht. According to one aspect, the adjacent housing connecting bores 3 are made in the recess bottom.
Gemäß einem Aspekt sind die zwischen jeweils zwei benachbarten Gehäuseverbindungsbohrungen vorgesehenen Materialaussparungen 4 im Vertiefungsboden vorgesehen. According to one aspect, the material recesses 4 provided between each two adjacent housing connecting bores are provided in the recess bottom.
Wie aus den vorstehenden Ausführungen ersichtlich ist, betrifft ein bevorzugter Aspekt der vorliegenden Erfindung ein T urbinengehäuse für eine Abgasturbine, welches einen Verbindungsflansch zur lagergehäuseseitigen Anbindung des Turbinengehäuses an ein Lagergehäuse der Abgasturbine aufweist. Bei diesem Verbindungsflansch handelt es sich vorzugsweise um eine lagergehäuseseitige Seitenwand des Turbinengehäuses. Die Seitenwand des Turbinengehäuses ist vorzugsweise zu einer direkten Verbindung mit einer turbinenseitigen Seitenwand des Lagergehäuses ausgebildet, bzw. direkt mit der turbinenseitigen Seitenwand des Lagergehäuses verbunden. Die Seitenwand des Turbinengehäuses ist vorzugsweise zu einer Verbindung mit einer turbinenseitigen Seitenwand des Lagergehäuses mittels eines (in die Gehäuseverbindungsbohrungen des Turbinengehäuses eindringenden) gemeinsamen Verbindungselements, z.B. einer Verbindungsschraube, ausgebildet, bzw. mittels eines solchen gemeinsamen Verbindungselements mit der turbinenseitigen Seitenwand des Lagergehäuses verbunden. Gemäß einem bevorzugten Aspekt sindan der Verbindungsstelle keine radial nach außen gerichteten Verbindungsflansche vorhanden, und/oder solche Verbindungsflansche werden nicht benötigt, um das Turbinengehäuse mit dem Lagergehäuse zu verbinden. As can be seen from the above, a preferred aspect of the present invention relates to a turbine housing for an exhaust gas turbine, which has a connecting flange for connecting the turbine housing on the bearing housing side to a bearing housing of the exhaust gas turbine. This connecting flange is preferably a side wall of the turbine housing on the bearing housing side. The side wall of the turbine housing is preferably designed to be directly connected to a turbine-side side wall of the bearing housing, or connected directly to the turbine-side side wall of the bearing housing. The side wall of the turbine housing is preferably to be connected to a turbine-side side wall of the bearing housing by means of a (penetrating into the housing connecting bores of the turbine housing) common connecting element, for example a connecting screw, or connected to the turbine-side side wall of the bearing housing by means of such a common connecting element. According to a preferred aspect, there are no radially outwardly directed connecting flanges at the connection point, and / or such connecting flanges are not required to connect the turbine housing to the bearing housing.
Bezugszeichenliste List of reference symbols
1 Turbinengehäuse 1 turbine housing
2 Verbindungsflansch 2 connecting flange
3 Gehäuseverbindungsbohrung 3 housing connection hole
4 Materialaussparung 4 material recess
5 ringförmige Vertiefung im Verbindungsflansch 5 annular recess in the connecting flange
6 Vertiefungsboden 6 recess bottom
7 Klemmrand des Verbindungsflansches 7 Clamping edge of the connection flange
8 Radialrichtung 8 radial direction
9 Umfangsrichtung 9 circumferential direction
10 Klemmrandaussparung 10 clamping edge recess
11 Tiefe der ringförmigen Vertiefung 5 11 Depth of the annular recess 5
12 Tiefe der Gehäuseverbindungsbohrungen 3 12 Depth of the housing connection holes 3
13 Axialrichtung; Richtung der Längsmittelachse des Turbinengehäuses 13 axial direction; Direction of the longitudinal center axis of the turbine housing
14 Lagergehäuse 14 bearing housings
15 Verbindungselement 15 connecting element
16 Klemmelement 16 clamping element
17 Mutter 17 mother
18 Beilagscheibe 18 washer
19 Verbindungssteg 19 connecting bridge
20 Summe der Tiefe der ringförmigen Vertiefung 5 und der Tiefe der Gehäuseverbindungsbohrungen 3 20 Sum of the depth of the annular recess 5 and the depth of the housing connecting bores 3
21 Längsmittelachse des Turbinengehäuses 21 Longitudinal central axis of the turbine housing

Claims

Patentansprüche Claims
1 . Turbinengehäuse (1 ) für eine Abgasturbine, welches einen Verbindungsflansch (2) zur lagergehäuseseitigen Anbindung an ein Lagergehäuse hin aufweist, in welchem in Umfangsrichtung (9) voneinander beabstandete Gehäuseverbindungsbohrungen (3) vorgesehen sind, wobei zwischen einander benachbarten Gehäuseverbindungsbohrungen radial nach innen in Richtung zu einer Längsmittelachse des Turbinengehäuses geöffnete Materialaussparungen (4) im Verbindungsflansch vorgesehen sind. 1 . Turbine housing (1) for an exhaust gas turbine, which has a connecting flange (2) for connection on the bearing housing side to a bearing housing, in which housing connection bores (3) spaced apart in the circumferential direction (9) are provided, with housing connection bores adjacent to one another radially inwards towards Material recesses (4) open to a longitudinal center axis of the turbine housing are provided in the connecting flange.
2. Turbinengehäuse nach Anspruch 1 , bei welchem die voneinander beabstandeten Gehäuseverbindungsbohrungen (3) im Verbindungsflansch (2) in Umfangsrichtung (9) entlang mindestens eines Kreises angeordnet sind. 2. Turbine casing according to claim 1, in which the spaced-apart casing connecting bores (3) in the connecting flange (2) are arranged in the circumferential direction (9) along at least one circle.
3. Turbinengehäuse nach Anspruch 2, welches einen Klemmrand (7) aufweist, der den Gehäuseverbindungsbohrungen (3) in Radialrichtung (8) benachbart angeordnet ist. 3. The turbine housing according to claim 2, which has a clamping edge (7) which is arranged adjacent to the housing connecting bores (3) in the radial direction (8).
4. Turbinengehäuse nach Anspruch 3, bei welchem die benachbarten Gehäuseverbindungsbohrungen (3) zumindest abschnittsweise von Verbindungsstegen (19) umgeben sind, welche gegenüber dem Klemmrand (7) in Axialrichtung (13) des Turbinengehäuses vertieft angeordnet sind, wobei die zwischen jeweils zwei benachbarten Gehäuseverbindungsbohrungen vorgesehenen Materialaussparungen (4) gegenüber den Verbindungsstegen (19) in Axialrichtung (13) des Turbinengehäuses vertieft angeordnet sind. 4. Turbine housing according to claim 3, in which the adjacent housing connection bores (3) are at least partially surrounded by connecting webs (19) which are arranged recessed in the axial direction (13) of the turbine housing opposite the clamping edge (7), the between each two adjacent housing connection bores provided material recesses (4) are arranged recessed relative to the connecting webs (19) in the axial direction (13) of the turbine housing.
5. Turbinengehäuse nach Anspruch 4, bei welchem der Klemmrand (7) im Bereich zwischen zwei benachbarten Gehäuseverbindungsbohrungen (3) jeweils eine die ringförmige Vertiefung (5) verbreiternde Klemmrandaussparung (10) aufweist. 5. Turbine housing according to claim 4, in which the clamping edge (7) in the area between two adjacent housing connection bores (3) each has a clamping edge recess (10) which widens the annular recess (5).
6. Turbinengehäuse nach Anspruch 5, bei welchem eine erste Tiefe (20) der Klemmrandaussparung (10) mit der Summe einer zweiten Tiefe (1 1 ) der ringförmigen Vertiefung (5) und einer dritten Tiefe (12) der in der ringförmigen Vertiefung vorgesehenen Gehäuseverbindungsbohrungen (3) übereinstimmt, wobei sich diese Tiefen in Axialrichtung (13) des Turbinengehäuses erstrecken. 6. Turbine housing according to claim 5, wherein a first depth (20) of the clamping edge recess (10) with the sum of a second depth (1 1) of the annular Recess (5) and a third depth (12) of the housing connecting bores (3) provided in the annular recess, these depths extending in the axial direction (13) of the turbine housing.
7. Turbinengehäuse nach einem der vorhergehenden Ansprüche, wobei das Turbinengehäuse mehrstückig ausgebildet ist. 7. Turbine housing according to one of the preceding claims, wherein the turbine housing is constructed in several pieces.
8. Tubinengehäuse nach Anspruch 7, bei welchem der Klemmrand (7) ein separates Bauteil des Turbinengehäuses bildet. 8. tubine housing according to claim 7, wherein the clamping edge (7) forms a separate component of the turbine housing.
9. Turbinengehäuse nach Anspruch 7, bei welchem ein Hitzeschild oder ein Düsenring ein separates Bauteil des Turbinengehäuses bildet. 9. The turbine housing according to claim 7, in which a heat shield or a nozzle ring forms a separate component of the turbine housing.
10. Turbinengehäuse nach Anspruch 9, bei welchem der Klemmrand (7) Bestandteil des Hitzeschildes oder des Düsenringes ist. 10. Turbine housing according to claim 9, wherein the clamping edge (7) is part of the heat shield or of the nozzle ring.
1 1 . Abgasturbine (15), welche ein Turbinengehäuse (1 ) nach einem der Ansprüche 1 - 10 aufweist. 1 1. Exhaust gas turbine (15) which has a turbine housing (1) according to one of Claims 1 to 10.
12. Abgasturbine nach Anspruch 1 1 , welche ein mit dem Turbinengehäuse (1 ) verbundenes Lagergehäuse (14) aufweist, wobei das Turbinengehäuse mit dem Lagergehäuse mittels Verbindungselementen (15) verbunden ist. 12. The exhaust gas turbine of claim 1 1, which has a bearing housing (14) connected to the turbine housing (1), the turbine housing being connected to the bearing housing by means of connecting elements (15).
13. Abgasturbine nach Anspruch 12, welche Klemmelemente (16) aufweist, die jeweils von einem oder mehreren Verbindungselementen (15) an den Verbindungsflansch (2) des Turbinengehäuses (1 ) und an das Lagergehäuse (14) gepresst sind. 13. The exhaust gas turbine according to claim 12, which has clamping elements (16) which are each pressed by one or more connecting elements (15) to the connecting flange (2) of the turbine housing (1) and to the bearing housing (14).
14. Abgasturbine nach Anspruch 1 1 , bei welcher die Klemmelemente (16) an den Klemmrand (7) gepresst sind. 14. Exhaust gas turbine according to claim 1 1, wherein the clamping elements (16) are pressed against the clamping edge (7).
15. Abgasturbine nach einem der Ansprüche 1 1 - 14, bei welcher die Verbindungselemente (15) Schrauben oder Gewindestifte sind. 15. Exhaust gas turbine according to one of claims 1 1 - 14, wherein the connecting elements (15) are screws or threaded pins.
EP20733442.6A 2019-07-15 2020-06-22 Turbine casing comprising a low-stress connection flange, and exhaust-gas turbine having such a turbine casing Pending EP3999721A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP19186327.3A EP3767081A1 (en) 2019-07-15 2019-07-15 Turbine housing with a reduced stress connecting flange and exhaust gas turbine comprising such a turbine housing
PCT/EP2020/067326 WO2021008816A1 (en) 2019-07-15 2020-06-22 Turbine casing comprising a low-stress connection flange, and exhaust-gas turbine having such a turbine casing

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EP3999721A1 true EP3999721A1 (en) 2022-05-25

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EP19186327.3A Withdrawn EP3767081A1 (en) 2019-07-15 2019-07-15 Turbine housing with a reduced stress connecting flange and exhaust gas turbine comprising such a turbine housing
EP20733442.6A Pending EP3999721A1 (en) 2019-07-15 2020-06-22 Turbine casing comprising a low-stress connection flange, and exhaust-gas turbine having such a turbine casing

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EP (2) EP3767081A1 (en)
JP (1) JP2022541034A (en)
KR (1) KR20220025240A (en)
CN (1) CN114144574A (en)
WO (1) WO2021008816A1 (en)

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FR3122900A1 (en) * 2021-05-11 2022-11-18 Safran Ventilation Systems DEVICE FOR MAKING A FAN OR COMPRESSOR FOR THE AEROSPACE INDUSTRY
KR20240000854A (en) 2022-06-24 2024-01-03 무진정밀(주) Heat-resistant steel with improved high-temperature properties and bolt-nut fastening member used for turbine casing for thermal power comprising the same

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4612407Y1 (en) * 1967-07-28 1971-04-30
US6287091B1 (en) * 2000-05-10 2001-09-11 General Motors Corporation Turbocharger with nozzle ring coupling
EP1353041A1 (en) * 2002-04-12 2003-10-15 ABB Turbo Systems AG Turbocharger with means on the shaft to axially restrain said shaft in the event of the compressor bursting
EP1460237B1 (en) * 2003-03-19 2010-05-12 ABB Turbo Systems AG Casing of a turbocharger
EP1536103B1 (en) * 2003-11-28 2013-09-04 BorgWarner, Inc. Turbo machine having inlet guide vanes and attachment arrangement therefor
DE102009052961A1 (en) * 2009-11-12 2011-05-19 Continental Automotive Gmbh Exhaust gas turbocharger, motor vehicle and method for mounting an exhaust gas turbocharger
CN104040142B (en) * 2012-01-26 2017-05-17 博格华纳公司 Exhaust-gas turbocharger
US9512740B2 (en) * 2013-11-22 2016-12-06 Siemens Energy, Inc. Industrial gas turbine exhaust system with area ruled exhaust path
US9856753B2 (en) * 2015-06-10 2018-01-02 United Technologies Corporation Inner diameter scallop case flange for a case of a gas turbine engine

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JP2022541034A (en) 2022-09-21
US20220268177A1 (en) 2022-08-25
KR20220025240A (en) 2022-03-03
EP3767081A1 (en) 2021-01-20
WO2021008816A1 (en) 2021-01-21
US11852030B2 (en) 2023-12-26
CN114144574A (en) 2022-03-04

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