EP3109407A1 - Dispositif de stator pour une turbomachine comprenant un dispositif de carter et plusieurs aubes directrices - Google Patents

Dispositif de stator pour une turbomachine comprenant un dispositif de carter et plusieurs aubes directrices Download PDF

Info

Publication number
EP3109407A1
EP3109407A1 EP16175988.1A EP16175988A EP3109407A1 EP 3109407 A1 EP3109407 A1 EP 3109407A1 EP 16175988 A EP16175988 A EP 16175988A EP 3109407 A1 EP3109407 A1 EP 3109407A1
Authority
EP
European Patent Office
Prior art keywords
platform
stator
region
gap
housing
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.)
Withdrawn
Application number
EP16175988.1A
Other languages
German (de)
English (en)
Inventor
Markus Goller
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3109407A1 publication Critical patent/EP3109407A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D25/005—Selecting particular materials
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/55—Seals
    • F05D2240/58—Piston ring seals
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/432—PTFE [PolyTetraFluorEthylene]

Definitions

  • the invention relates to a stator device for a turbomachine, in particular an aircraft engine, with a housing device and a plurality of stator blades according to the type defined in more detail in patent claim 1.
  • Stator devices of compressors for aircraft engines which are designed with adjustable about a central axis trained vanes are well known in the art.
  • the circumferentially distributed arranged in a housing means vanes each have an airfoil and a subsequent radially outward direction of the stator device, also referred to as penny platform, the platforms together with the housing means defining a core flow channel of the aircraft engine in the radial direction of the stator.
  • the platforms in the radial direction of the aircraft engine on a side facing away from the blades of the platforms is followed in each case by a spindle-shaped region over which the guide vanes are rotatably mounted about the central axis of the spindle-shaped region relative to the housing means.
  • the platform which has a circular cross-section with respect to the central axis of the spindle-shaped area, has a larger cross section than the spindle-shaped area with respect to the central axis of the spindle-shaped area.
  • the platforms are each mounted in a recess of the housing device which is concentric with the central axis of the spindle-shaped area, the housing device and the platform being spaced apart from one another in the radial direction of the central axis of the spindle-shaped area, so that there is a circumferential gap between the housing device and the platforms of the guide vanes , In addition, a surface facing away from the core flow channel of the platforms with respect to the housing device in the radial direction is spaced.
  • a turbomachine designed with such a stator device disadvantageously has an unsatisfactory efficiency.
  • the invention relates to a stator device of a compressor or a turbine for a turbomachine, in particular an aircraft engine or a stationary gas turbine, with a housing device and a plurality of guide vanes, which are arranged circumferentially distributed on the housing device, the guide vanes each having an airfoil and in each case at least one platform (Penny) are executed.
  • the platforms form, at least in regions, a surface of an annular channel through which working fluid flows during operation of the stator device and are adjustably mounted relative to the housing device, a gap region being provided, at least in regions, by a radial gap between the platform and the housing device in relation to a longitudinal axis of the platform Area of the surface of the annular channel is formed.
  • a sealing device is provided in the region of the gap.
  • the solution according to the invention is based on the recognition that in operation of a turbomachine in conventionally designed stator devices through the gap region, which in addition to the radial gap by an axial spacing - with respect to the longitudinal axis of the platform - between a surface facing away from the annular channel of the platform and the Housing device may be formed, a part of the guided through the annular channel working fluid is guided as a leakage flow.
  • This leakage flow is due to a pressure difference between the pressure side and the suction side of the airfoil or an increasing pressure gradient in the flow direction of the working fluid in the annular channel through the gap region, wherein the leakage flow in particular via the gap in the region of the downstream pressure side of the blade and the side facing away from the annular channel of the platform to an upstream suction side of the blade and there is guided over the gap in the annular channel.
  • the leakage flow in the region of the suction side of the blade leaves the gap region, the leakage flow from the gap region interacts with the main flow of the working fluid in the annular channel, wherein a so-called blocking region with a flow velocity reduced relative to surrounding regions of the main flow occurs in the main flow. This effect causes the leakage flow has a significant negative impact on the efficiency of the turbomachine.
  • the provision of the sealing device in the solution according to the invention has the advantage that the gap region during operation of the stator at least partially in the radial direction of the stator or in the axial direction of the longitudinal axis of the platform is sealable, so that a mass flow of the leakage flow, in the region of the suction side of the airfoil enters the main flow of the annular channel from the gap, reduced or flow of leakage flow into the annular channel in the region of the suction side of the airfoil is completely prevented.
  • a lossy interaction of the leakage flow with the main flow is hereby reduced or completely eliminated, so that an efficiency of a turbomachine designed with the stator device according to the invention is increased over known embodiments without such a sealing device.
  • the leakage flow through the gap region is particularly greatly reduced if the sealing device extends in the radial direction-with respect to the longitudinal axis of the platform-from the platform to the housing device and thus radially overlaps the entire gap.
  • the sealing device may be designed to revolve at least approximately the platform with respect to the longitudinal axis of the platform.
  • the leakage flow in the region of the gap can be completely eliminated here.
  • the sealing in the region of the gap between the platform and the housing device is particularly effective if the sealing device is arranged in an area of the gap adjacent to the annular channel.
  • a leakage flow can be prevented in an annular channel near the area around the platform.
  • the sealing device with a particular high temperature resistant material such as polytetrafluoroethylene or the like, executed.
  • the sealing device can be arranged in a structurally particularly simple manner in the region of the gap, if the sealing device is arranged at least partially in a substantially radial direction with respect to the central axis facing groove of the platform and / or a groove of the housing device.
  • a simple and cost-effective designed stator device is when the sealing device is designed as an O-ring, as a piston ring with in particular circumferentially spaced ends or as a shaft seal.
  • the platform of the guide vane may be arranged in an inner and / or outer edge region of the vane with respect to the radial direction of the stator device, wherein a sealing device is preferably arranged in a gap between the respective platform and the housing device in the region of each platform.
  • Fig. 1 shows a section of a turbomachine, which in the present case is designed as a jet engine 1 of an aircraft, but in an alternative embodiment may also be a stationary gas turbine.
  • an annular channel or core flow channel 3 of the jet engine 1 is shown in the region of a high-pressure compressor 2 Schaufelradvoriques, wherein various stages 6A, 6B, 6C, 6D of the high-pressure compressor 2 can be seen, each consisting of a rotor device 4 and one in the axial direction A of the jet engine 1 downstream of the rotor device 4 arranged stator 5 exist.
  • the rotor device 4 has a multiplicity of rotor blades 9, which are designed with blades 10 and are circumferentially distributed with a disk wheel 11 are operatively connected and rotate during operation of the jet engine 1 about a central axis of the jet propulsion system 1.
  • the stator device 5 is designed with a large number of guide vanes 12, each of which has an airfoil 13, wherein the guide vanes 12, which are constructed identically, are arranged on the outside of a housing device 8 distributed in the radial direction R of the jet engine 1.
  • the platforms or pennies 14 delimit the core flow channel 3 in the radial direction R of the jet engine 1, at least in regions, and are viewed radially outwardly, in each case connected to a spindle-shaped region 15 and in the present case designed integrally therewith.
  • the platforms 14 have a larger cross-section than the spindle-shaped area 15 with respect to a central axis 18 of the spindle-shaped area 15.
  • the guide vanes 12 are arranged with the platforms 14 and the spindle-shaped regions 15 in recesses 16 of the housing device 8, wherein the spindle-shaped regions 15 are mounted in the recesses 16 via bushes 17.
  • the guide vanes 12 are rotatably arranged in the recesses 16 of the housing device 8 in a known manner about the central axis 18 of the spindle-shaped region 15, which is congruent to the longitudinal axis of the platform 14, wherein the guide vanes 12, for example via the spindle-shaped regions 15 by 5 ° to 60 ° relative to the housing device 8 are rotatable.
  • a platform 19 is provided, which is executed in a comparable manner to the platform 14 with a spindle-shaped portion 20 and the core flow channel 3 at least partially in the radial Limited R direction of the jet engine 1.
  • the guide vane 12 in turn via a socket 21 in one Housing part 22 of the housing device 8, a so-called Shroud, stored, wherein the guide vane 12 is rotatably mounted about the central axis 18 relative to the housing part 22.
  • the housing part 22 is arranged overall in a recess 24 which is formed by two rotor devices 4 which are adjacent to one another in the axial direction A of the jet engine 1 or the stator device 5.
  • the area of the rotor device 4 facing the housing part 22 rotates about the engine axis, whereas the housing part 22 is stationary with respect to the engine axis.
  • Fig. 2 a detail of the stator device 5 with the spindle-shaped portion 15 and the platform 14 of the guide vane 12 is shown in more detail.
  • the platform 14, which has a circular cross-section, and the spindle-shaped region 15, which is likewise designed with a circular cross section, are mounted in the recess 16 of the housing device 8 which is concentric with the central axis 18.
  • the housing device 8 Between the platform 14 and the housing device 8, in the region of a surface 27 of the core flow channel 3, there is a gap 28 which circulates in the radial direction r, starting from the surface 27 of the core flow channel 3 substantially in the axial direction a of the central axis 18 extends to the outside.
  • a surface 30 of the platform 14 facing away from the core flow channel 3 is spaced apart from the housing device 8 in the radial direction R of the jet engine 1.
  • a pressure of a working fluid rises in the area of the high-pressure compressor 2 in the core flow channel 3 in the axial direction A of the jet engine 1 and thus in the flow direction, so that a pressure of a main flow flowing through the core flow channel 3 on a pressure side 33 of the airfoil 13 of the vane 12 is greater than on a
  • part of the main flow flows as leakage flow from the pressure side 33 of the airfoil 13 through the gap region 31 to the suction side 34 of the airfoil 13 due to these pressure conditions.
  • the leakage flow is determined by the pressure-side region of the airfoil Slit 28 is guided over the core flow channel 3 facing away from the surface 30 to the suction-side region of the gap 28.
  • Fig. 2 a designed as a piston ring 40 sealing provided, which is arranged in the gap 28 and in Fig. 3 in isolation can be seen.
  • the present case with resistant polytetrafluoroethylene executed piston ring 40 is arranged both in a groove 41 of the platform 14 and in a groove 42 of the housing device 8, so that a width of the gap 28 in the radial direction r with respect to the central axis 18 of the piston ring 40 completely covers becomes.
  • this is designed in the manner of an annular disc with a recess 44.
  • the piston ring 40 is preferably arranged in a gap directly adjacent to the core flow channel 3 or a surface 27 of the core flow channel 3 in the gap 28, so that in the radial direction R of the jet engine 1 within the flow area 43 present in the piston ring 40 is minimized or completely eliminated.
  • the piston ring 40 can be achieved in a simple manner that during operation of the jet engine 1 on a side facing away from the core flow channel 3 of the piston ring 40 no or only one compared to conventional designs without a piston ring 40 greatly reduced leakage flow flows.
  • Fig. 4 to Fig. 6 are shown to the piston ring alternative embodiments of a sealing device 46, 47, 48, wherein in the following only the differences from the embodiment described in more detail above are shown.
  • the sealing device 46 is designed as an O-ring, wherein the O-ring 46 is held in its position by means of a groove 50 provided in the housing device 8.
  • the O-ring 46 bears against a side surface 51 of the platform 14 that extends essentially in the radial direction R of the jet engine 1.
  • Fig. 5 is also shown as an O-ring sealing device 47 is shown, which is arranged in contrast to the sealing device 46 in a provided in the platform 14 groove 52.
  • the O-ring 47 bears against a side surface 58 of the housing device 8 which extends essentially in the radial direction R of the jet engine 1.
  • the O-ring 47 has the same effect as the O-ring 46 and is also completely circumferential in the circumferential direction u of the central axis 18 executed so that the gap 28 is completely sealed in this embodiment in the radial direction r of the central axis 18.
  • the sealing device is designed as a shaft sealing ring 48, which rests in the region of a shoulder 53 of the housing device 8 at this.
  • the shaft sealing ring 48 is again made with polytetrafluoroethylene, but has an integrated reinforcement 54.
  • the reinforcement 54 is embedded in a radial direction R of the jet engine 1 extending leg 55, which cooperates in the assembled state with a substantially in the axial direction a with respect to the central axis 18 extending side surface 58 of the housing means 8.
  • the reinforcement 54 has a substantially in the radial direction r with respect to the central axis 18 extending portion 56, which is designed as a circular ring.
  • the shaft sealing ring 48 cooperates with a surface 59 of the housing device 8 via the region 56, which likewise runs essentially in the radial direction r with respect to the central axis 18.
  • the shaft seal 48 further has a sealing lip 61, which is designed to cooperate with the side surface 51 of the platform 14.
  • the shaft seal 48 has a traction spring 62 designed as traction means.
  • the tension spring 62 is arranged on one of the platform 14 in the radial direction r of the central axis 18 side facing away from the sealing lip 61 and running circumferentially.
  • the sealing device 40, 46, 47, 48 interacts with the platform 14 and / or the housing device 8 in such a way that the guide blade 12 can be adjusted in a simple manner around the central axis 18.
  • the pressing forces of the sealing device 40, 46, 47, 48 on the platform 14 and / or the housing device 8 are adjusted to a predetermined value accordingly.
  • a sealing device can be arranged in a comparable manner, wherein the sealing means between the platform 19 and the housing part 22 in the of these components in radial direction r with respect to the central axis 18 formed gap 28 can be arranged.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP16175988.1A 2015-06-25 2016-06-23 Dispositif de stator pour une turbomachine comprenant un dispositif de carter et plusieurs aubes directrices Withdrawn EP3109407A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015110252.8A DE102015110252A1 (de) 2015-06-25 2015-06-25 Statorvorrichtung für eine Strömungsmaschine mit einer Gehäuseeinrichtung und mehreren Leitschaufeln

Publications (1)

Publication Number Publication Date
EP3109407A1 true EP3109407A1 (fr) 2016-12-28

Family

ID=56203246

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16175988.1A Withdrawn EP3109407A1 (fr) 2015-06-25 2016-06-23 Dispositif de stator pour une turbomachine comprenant un dispositif de carter et plusieurs aubes directrices

Country Status (3)

Country Link
US (1) US20160376900A1 (fr)
EP (1) EP3109407A1 (fr)
DE (1) DE102015110252A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11085315B2 (en) * 2019-07-09 2021-08-10 General Electric Company Turbine engine with a seal
DE102021120384A1 (de) 2021-08-05 2023-02-09 MTU Aero Engines AG Leitschaufelkranz für eine Strömungsmaschine, Strömungsmaschine und Verfahren zum Montieren eines Leitschaufelkranzes

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1010862A2 (fr) * 1998-12-16 2000-06-21 General Electric Company Rondelle et joint pour une aube variable
US20130205800A1 (en) * 2012-02-10 2013-08-15 Richard Ivakitch Vane assemblies for gas turbine engines
US20130343878A1 (en) * 2012-06-22 2013-12-26 United Technologies Corporation Turbine engine variable area vane with feather seal
EP2829735A1 (fr) * 2013-07-23 2015-01-28 Mitsubishi Hitachi Power Systems, Ltd. Compresseur axial
DE102013222980A1 (de) * 2013-11-12 2015-06-11 MTU Aero Engines AG Leitschaufel für eine Strömungsmaschine mit einer Dichtungsvorrichtung, Leitrad sowie Strömungsmaschine

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002195196A (ja) * 2000-12-26 2002-07-10 Ishikawajima Harima Heavy Ind Co Ltd 軸流圧縮機のブリード構造
DE102008015207A1 (de) * 2008-03-20 2009-09-24 Rolls-Royce Deutschland Ltd & Co Kg Fluid-Injektor-Düse
DE102008019603A1 (de) * 2008-04-18 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Strömungsmaschine mit schaufelreiheninterner Fluid-Rückführung

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1010862A2 (fr) * 1998-12-16 2000-06-21 General Electric Company Rondelle et joint pour une aube variable
US20130205800A1 (en) * 2012-02-10 2013-08-15 Richard Ivakitch Vane assemblies for gas turbine engines
US20130343878A1 (en) * 2012-06-22 2013-12-26 United Technologies Corporation Turbine engine variable area vane with feather seal
EP2829735A1 (fr) * 2013-07-23 2015-01-28 Mitsubishi Hitachi Power Systems, Ltd. Compresseur axial
DE102013222980A1 (de) * 2013-11-12 2015-06-11 MTU Aero Engines AG Leitschaufel für eine Strömungsmaschine mit einer Dichtungsvorrichtung, Leitrad sowie Strömungsmaschine

Also Published As

Publication number Publication date
US20160376900A1 (en) 2016-12-29
DE102015110252A1 (de) 2016-12-29

Similar Documents

Publication Publication Date Title
DE102012013160B4 (de) Labyrinthdichtungen
EP2242931B1 (fr) Structure d'écoulement pour turbocompresseur
DE60024541T2 (de) Statoranordnung für eine Rotationsmaschine
DE102013011350A1 (de) Gasturbine mit Hochdruckturbinenkühlsystem
DE112015001237B4 (de) Abgasturbolader
DE112014003165B4 (de) Variable Düseneinheit und Turbolader mit variablem Geometriesystem
EP1694943B1 (fr) Turbomachine
DE102015120127A1 (de) Axialverdichterendwandeinrichtung zur steuerung der leckage in dieser
DE102015122928A1 (de) Gasturbinendichtung
DE102007050916A1 (de) Verfahren und Vorrichtung zum Zusammenbau von Gasturbinen-Triebwerken
EP2140111B1 (fr) Turbomachine
DE3031553A1 (de) Gasturbinenlaufrad.
EP3109407A1 (fr) Dispositif de stator pour une turbomachine comprenant un dispositif de carter et plusieurs aubes directrices
DE102018206601A1 (de) Schaufel, Schaufelsegment und Baugruppe für eine Turbomaschine und Turbomaschine
CH714389B1 (de) Radialverdichter.
EP1673519B1 (fr) Dispositif d'etancheite pour une turbine a gaz
DE102014214775A1 (de) Fluggasturbine mit einer Dichtung zur Abdichtung einer Zündkerze an der Brennkammerwand einer Gasturbine
EP2650520B1 (fr) Turbine à gaz d'aéronef avec canal de décharge dans un pied d'aube de guidage d'un canal de flux secondaire
EP1783325A1 (fr) Assemblage de fixation d'un tuyau sur une surface périphérique
DE102016208706A1 (de) Leitschaufel für ein Eintrittsleitgitter
EP3034784A1 (fr) Possibilité de refroidissement pour turbomachines
WO2005047656A1 (fr) Grille d'aubes directrices et turbomachine comportant une grille d'aubes directrices
EP1531233A2 (fr) Turbine à gaz conprenant des aubes statoriques ayant différentes courbures radiales
DE102004026367A1 (de) Turbomaschine
DE102012011144A1 (de) Hydraulische Dichtungsanordnung

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20170629