EP3324002A1 - Système d'étanchéité pour une turbomachine axiale et turbomachine axiale - Google Patents

Système d'étanchéité pour une turbomachine axiale et turbomachine axiale Download PDF

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Publication number
EP3324002A1
EP3324002A1 EP17198765.4A EP17198765A EP3324002A1 EP 3324002 A1 EP3324002 A1 EP 3324002A1 EP 17198765 A EP17198765 A EP 17198765A EP 3324002 A1 EP3324002 A1 EP 3324002A1
Authority
EP
European Patent Office
Prior art keywords
shroud
sealing
sealing system
tip
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.)
Granted
Application number
EP17198765.4A
Other languages
German (de)
English (en)
Other versions
EP3324002B1 (fr
Inventor
Hermann Klingels
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.)
MTU Aero Engines AG
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MTU Aero Engines AG
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
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Publication of EP3324002A1 publication Critical patent/EP3324002A1/fr
Application granted granted Critical
Publication of EP3324002B1 publication Critical patent/EP3324002B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention relates to a sealing system for an axial flow machine according to the preamble of claim 1. Furthermore, the present invention relates to an axial flow machine according to claim 14.
  • the pressure in the working fluid changes from stage to stage.
  • the pressure in the compressor is usually downstream of a row of blades higher than the pressure upstream, in the turbine, however downstream of a row of blades less than the pressure upstream.
  • a sealing system is provided in the region of an outer annular space boundary, which is designed for example as a labyrinth system.
  • Such sealing systems have the task of keeping a leakage current through a sealing gap between the rotating blading and a housing minimal and thus to allow a stable operating behavior with high efficiency.
  • the rotating components of a turbine on sealing fins or sealing tips, which can strip or shrink against honeycomb seals.
  • the seals are designed as a squint and inlet coverings.
  • An object of the present invention is to propose a further sealing system for an axial flow machine. It is another object of the present invention to provide an axial flow machine with a sealing system according to the invention.
  • the object of the invention is achieved by a sealing system having the features of claim 1. It is further achieved by an axial flow machine having the features of claim 14.
  • a sealing system for an axial flow machine which comprises at least one impeller with a shroud arranged radially on the outside and a housing surrounding the impeller. Between the shroud and the housing, a gap is arranged. The gap is bounded on the one hand by means of a seal connected to the housing and on the other hand by means of at least one sealing tip arranged on the cover band.
  • This arranged on the shroud sealing tip can be referred to as a rotating sealing tip, as it rotates with the impeller.
  • the seal is, viewed in the radial direction, arranged opposite the shroud. The limitation of the gap by the seal and the shroud can reduce the flow losses of the slit flow.
  • static sealing tip At the downstream end portion of the housing-side seal another, connected to the housing, static sealing tip is arranged.
  • this static sealing tip By means of this static sealing tip, the flow through the gap is influenced, in particular reduced.
  • the flow downstream of the static sealing tip is influenced by means of the static sealing tip.
  • An influence in particular a reduction of the flow through the gap by means of the static sealing tip, can be caused by flow losses of the static sealing tip.
  • a possible vortex formation downstream of the static sealing tip can be influenced by the static sealing tip.
  • the gap flow between the static sealing tip and the shroud may cause a vortex or vortex region downstream, the direction of rotation of which has primarily the same flow direction as the adjacent main flow.
  • the flow losses and / or the disturbance of the main flow through these vortices can be reduced. This can advantageously increase the efficiency of the axial flow machine by the sealing system according to the invention.
  • a reduced main flow disturbance due to the described direction of rotation of the vortices may be referred to as a low loss mixing with the main flow.
  • a sealing system without static sealing tip lead to a vortex formation whose primary direction of rotation is opposite to the main flow. This would lead to a lossy mixture with the main flow and could contribute to a reduction in the efficiency of the turbomachine.
  • the shroud arranged radially on the outside of the impeller can be referred to as an outer shroud or as a shovel outer shroud.
  • the arranged between the shroud and the housing gap may be referred to as a running gap.
  • the axial flow machine according to the invention comprises at least one low-pressure turbine stage with a sealing system according to the invention.
  • the axial flow machine may further comprise at least one high-pressure turbine stage, a low-pressure compressor stage and a high-pressure compressor stage. Each of said stages may comprise a sealing system according to the invention.
  • the axial flow machine may be a gas turbine, in particular an aircraft gas turbine or an aircraft engine.
  • Inventive exemplary embodiments may have one or more of the following features.
  • a static and / or a circumferential sealing tip can be referred to as Dichtfin.
  • the seal associated with the housing may be an inlet seal.
  • An inlet seal can be called an abradable seal.
  • An inlet seal may have an insertable coating or an insertable layer into which, for example, a sealing tip can penetrate to form a sealing gap. This sealing gap can be made small by the penetration or shrinkage of a sealing tip, in particular during an intended operating state and thus contribute advantageously to optimize the efficiency of the turbomachine.
  • the inlet seal may comprise a honeycomb structure for penetrating a sealing tip.
  • the inlet seal may be connected to the housing cohesively and / or positively.
  • the inlet seal may be glued, soldered, riveted or clamped, or otherwise attached to the housing.
  • the inlet seal is attached only to the housing.
  • the inlet seal is thus arranged only on one side of the gap.
  • the shroud may include at least two sealing tips.
  • Two sealing tips can engage in two opposite inlet seals on the housing and form a sealing gap.
  • the at least two sealing tips can be arranged axially one behind the other on a radius or at a radial height.
  • the two sealing tips can be arranged axially one behind the other at different radii or at radially different heights, that is, offset radially.
  • the shroud has no seal, in particular no inlet seal.
  • the shroud has three or more sealing tips.
  • the sealing tips may be arranged radially at a height or at different heights. For example, two axially successively arranged sealing tips have the same radius, whereas a third sealing tip is arranged radially further outside.
  • the at least one sealing tip of the shroud is arranged inclined upstream.
  • the angle of inclination between the radial direction and the axial direction may be, for example, at least 15 degrees.
  • a non-sloped sealing tip in the radial direction would be zero degrees.
  • An inclined sealing tip can favor the flow losses due to a smaller flow through the gap influence.
  • An inclined sealing tip can also be advantageous in terms of the shroud configuration, for example, in an arrangement of multiple sealing tips on the shroud.
  • the structural strength of the shroud with an inclined sealing tip can be advantageously higher.
  • the upstreammost sealing tip of the shroud can be inclined.
  • the incline can be twenty degrees, twenty-five degrees, thirty degrees or more.
  • the shroud has wear protection in the opposite region of the static sealing tip.
  • the wear protection can advantageously prevent direct contact of the static sealing tip with the base material of the shroud. Direct contact could damage the shroud causing more damage.
  • the wear protection of the shroud extends beyond the opposite region of the static sealing tip, in particular at least to the adjacent shroud end.
  • the wear protection can extend over more area of the shroud.
  • the wear protection is a, at least in sections, coating of the shroud.
  • the wear-resistant layer can also be understood as a flake-like element fastened to the shroud in a material- and / or non-positive manner, for example of a material with the trade name "stellite".
  • the wear protection is arranged in regions over the circumference of the shroud.
  • the wear protection can be arranged only at individual points of the shroud.
  • the material of the static sealing tip has a lower hardness than the hardness of the wear protection layer.
  • the hardness of the material can be a measure of the resistance of the material to wear.
  • the material of the wear protection layer preferably differs from the base material of the shroud and, in particular, also has a greater hardness relative to this base material.
  • greater hardness in the sense of the present invention is meant in particular a “greater wear resistance”.
  • the wear protection is superior to the rest of the shroud surface, or in other words, the height of the wear protection extends beyond the surface of the shroud.
  • the wear protection thickness can have, for example, 5 ⁇ m, 10 ⁇ m, 20 ⁇ m or another thickness.
  • a wear protection is produced by means of a local surface layer hardening, in particular by means of a laser-supported method.
  • the static sealing tip is fastened to the housing with a positive-locking component, in particular a holding element.
  • the static sealing tip can be materially connected to the holding element.
  • the static sealing tip is secured to the housing with a positive fit component, particularly a retainer, on the downstream baffle, or the baffle connection.
  • the static sealing tip can be materially connected to the holding element.
  • the impeller is a turbine runner, particularly a low-pressure turbine runner.
  • the shroud is segmented about the circumference of the impeller.
  • the segments are designed as z-shroud segments.
  • the impeller blades can advantageously be braced with one another.
  • the contact regions of the shroud segments have wear protection in the circumferential direction.
  • This wear protection can be designed as wear protection in the opposite region of the static sealing tip.
  • this wear protection projects as a wear protection layer beyond the shroud surface, so that in the event of contact of the static sealing tip with the shroud, initially only the wear protection layer touches becomes.
  • the hardness of the wear protection layer is greater than the hardness of the static sealing tip. This advantageously allows the shroud to be protected from contact with the static sealing tip. Such contact could damage the shroud.
  • the wear protection can be integrally connected to the shroud, for example by means of welding (for example by laser deposition welding).
  • the material of the wear protection can be a cobalt-based hard alloy, for example a cobalt-chromium alloy, or have such.
  • the hardness of the wear-resistant coating can be greater than 600 Vickers hardness (HV for short) purely by way of example.
  • the static sealing tip is connected in a form-fitting and / or material-locking manner to the housing by means of a holding element.
  • the static sealing tip on the side opposite the shroud has a circumferentially variable, in particular wave-shaped structure.
  • a circumferentially variable, in particular wave-shaped structure By means of the variable or wave-like structure, when the sealing tip contacts the shroud, or with a wear protection layer on the shroud, an axially larger area of a contact surface of the sealing tip can be used in comparison with a non-variable or wavy, ie straight, structure over the circumference.
  • the heat input during a contact process or a rubbing process between the sealing tip and the shroud (or the wear protection layer) can advantageously be distributed over a larger area and a larger volume of material. As a result, the load, in particular the thermal material stress, of the wear protection layer can be locally reduced.
  • Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.
  • the leakages that is to say the bypass flow or the gap flow
  • the leaks can be referred to as primary losses.
  • the gap flow can be reduced.
  • the main flow less disturbed and thus the efficiency of the turbomachine can be increased.
  • the disturbances of the main flow can be called secondary losses.
  • the vortex formation can be influenced downstream of the static sealing tip and thus the vortex rotation direction of the main flow direction can be adjusted. As a result, a low-loss mixture of the vortices resulting from the slit flow can be achieved with the main flow.
  • FIG. 1 shows a known from the prior art sealing system 100 'of a turbine stage with an inlet seal 12 and two rotating (rotating) sealing tips 5 in longitudinal section.
  • a sealing system 100 ' may be synonymously referred to as a sealing system.
  • the inlet seal 12 may be referred to as inlet lining.
  • a housing portion 10 is shown on the housing side, in which a seal carrier 11 is mounted.
  • the housing portion 10 could also be referred to as a static sealing part.
  • the inlet seal 12 is fixed, for example, materially by means of soldering or gluing.
  • two sealing tips 5, which can be referred to as sealing fins In the inlet seal 12 engage two sealing tips 5, which can be referred to as sealing fins.
  • a running gap 6 between the inlet seal 12 and the sealing tips 5 is generated or generated by means of shrinkage or cutting in of the sealing tips 5.
  • the sealing tips 5 are arranged on a radially outer shroud 4, which in turn is connected to an impeller 3.
  • the shroud 4 may be integrally connected to the impeller 3, for example by means of a laser sintering process.
  • the flow direction of a leakage flow (the leakage flow may be referred to as a split flow or bypass flow) is shown by the arrow of the reference numeral 6 of the nip 6.
  • the flow direction is in the arrow direction of the reference character of the nip 6.
  • a stiffening structure 13 is optionally shown on the shroud 4.
  • the moving blade 3 is unambiguously positioned with respect to the inlet seal 12, and thus with respect to the surrounding housing 30 and the guide wheels 1, 2, which may be referred to as stator.
  • the rotor connected to the impeller 3 (in Fig. 1 not shown) move axially within certain limits relative to the stator, for example due to a play of the bearings, thermal expansions and other factors. Due to these axial movements of the rotor and the impeller 3, only a few sealing tips 5 can be arranged on the shroud 4.
  • Fig. 1 are two sealing tips 5 are arranged as an example. Due to this limited number of sealing tips 5, the sealing effect, depending on the running gap 6, limited.
  • Fig. 2 shows a sealing system according to the invention 100 a turbine stage with an inlet seal 12, two circumferential sealing tips 5 and connected to a housing 30 static sealing tip 20 in longitudinal section.
  • the arrangement of the upstream stator 1, the downstream stator 2, the blade 3, the housing portion 10 and the seal carrier 11 (which is shown in FIG Fig. 2 designed differently than in Fig. 1 ) is analogous to the description of Fig. 1 ,
  • the two rotating sealing tips 5 are axially offset on the shroud 5 relative to the arrangement of Fig. 1 arranged.
  • a case-side static sealing tip 20 is installed opposite to the downstream end portion of the shroud 4.
  • the static sealing tip 20 is in the exemplary embodiment of Fig. 2 fixed by means of a holding element 21 on the static housing section 10 and the housing-side holder of the downstream stator 2.
  • the fixation can be designed as a clamp.
  • An additional cohesive fixation of the static sealing tip 20 on the holding element 21 and / or of the holding element 21 on the housing section 10, for example by means of a soldered or welded connection, is optionally possible.
  • Fig. 2 a so-called Griffinbegrenzer 22 introduced into the housing 30 inside.
  • the room delimiter 22 can for example contribute to the reduction of flow losses.
  • the additional static sealing tip 20 can advantageously reduce the leakage resulting from the running gap 6. Furthermore, the direction of rotation of the downstream of the static sealing tip 20 forming vortex W with respect to the direction of rotation of the sealing system 100 'from the Fig. 1 reverse, so that a low-loss mixture with the main flow H is advantageously possible.
  • the low-loss mixture with the main flow H is through the same parallel flow direction of the main flow H with the flow direction of the immediately emerging vortex in Fig. 2 shown. Due to these two effects of the static sealing tip 20, reduction of the leakage and low-loss mixing of the vortex W with the main flow H, the total losses of the turbine stage can be advantageously reduced.
  • the front upstream seal tip 5 is inclined, with respect to the radial direction r, against the main flow direction aligned in the axial direction.
  • the inclination is about 30 degrees.
  • the leakage flow can be influenced by the running gap 6.
  • the two sealing tips 5 are arranged radially offset and thus approximately form the widening flow channel of the turbine stage.
  • the shroud 4 is executed segmented over the circumference u.
  • the segments are often executed as so-called z-shrouds (see Fig. 4 that look as View B Fig. 2 is shown), since their peripheral edges are not rectilinear in the axial direction of the turbomachine, but are formed substantially z-fömig. With this z-shape, it is possible to clamp in the mounted state, the circumferentially adjacent blades 3 a rotor stage with each other.
  • a wear protection layer 8 which in the Figures 2 . 3 and 4 is shown dark.
  • the wear protection view 8 is applied in the axial direction of the turbomachine not only in the central region of the z-fömigen peripheral edge of the shroud 4, in which by contact substantially the bracing forces between two circumferentially adjacent blades 3 are transmitted to the shroud 4, but the wear protection layer extends axially even further to the rear.
  • the wear protection layer 8 extends in the axial direction of the turbomachine at least up to the axial position of the static sealing tip 20 to the rear. In the present embodiment, the wear protection layer 8 extends even to the downstream end of the shroud. 4
  • the wear protection layer 8 projects beyond the surface of the shroud 4. This has the advantage that in case of an unwanted contact of the static sealing tip 20 with the shroud 4, for example in the case of a hard landing of an aircraft provided with the turbomachine as an engine, the static sealing tip 20 does not If the material of the wear protection layer 8 has a higher hardness than the material of the static sealing tip 20, the static sealing tip 20 is removed from the rotating impeller 3 or abraded.
  • the static sealing tip 20 may be slightly shortened, for example, in the radial direction r. In this way, damage to the impeller 3 is prevented.
  • a grinding of the static sealing tip 20 through the wear protection layer 8, however, is much less critical and the static sealing tip 20 can also be replaced relatively easily and inexpensively.
  • Fig. 3 shows the sealing system 100 according to the invention in a cross-sectional plane (section A - A, see Fig. 2 ) with the static sealing tip 20, the seal carrier 11, the impeller 3 with shroud 4 and a wear protection layer 8 between the shroud segments.
  • the shroud 4 is segmented.
  • the so-called z-shroud has wear protection layers 7, 8 at the contact points of the abutting segments.
  • the wear protection layer 8 which extends in the axial direction further downstream than the wear protection layer 7, projects slightly beyond the radial extent of the shroud surface. In Fig. 3 this is represented by the heel height 23.
  • the static sealing tip 20 Due to this increase of the wear protection layer 8 over the surface of the shroud 4, the static sealing tip 20, for example, in the aforementioned case, first the increased wear protection layer 8 touched at a lower hardness of the material of the static sealing tip 20 against the hardness of the material of the wear protection layer 8 the static sealing tip 20 ground or deformed, but without touching the shroud 4 itself and damage.
  • the wear-resistant layer 8 used for the contact of two circumferentially adjacent shrouds 4 can be synergistically used here in order to prevent possible damage to the base material of the shroud 4 by contact with the static sealing tip 20.
  • the wear protection layer 8 in the axial and radial directions of the turbomachine is to be dimensioned only slightly larger than would otherwise be the case.
  • Fig. 4 shows the shroud 4 in a view B from the radial outside (see Fig. 2 ) with the wear protection layers 7, 8.
  • the profile shape of the blade shape of the impeller 3 is schematically indicated below the shroud.
  • the sealing tips 5 of the shroud 4 project out of the plane of representation.
  • the wear protection layers 7, 8 are located at the contact surfaces of the z-shroud to the circumferentially adjacent (not shown) segments of other bucket cover strips.
  • the shaded anti-wear layer 8 was already in the cutting plane of Fig. 2 opposite the static sealing tip 20.
  • Fig. 5a, b show two different courses of the radially inner edge, or inner edge of the static sealing tip 20 in the circumferential direction u in a view C (see Fig. 3 ).
  • Fig. 5a is a straight waveform and shown in Fig. 5b a waveform.
  • the waveform has the advantage that in the case of contact of the static sealing tip 20 with the wear protection layer 8 of the shroud 4, an axially larger area of the wear protection layer 8 for a grinding or deformation of the static sealing tip 20 is available.
  • the heat input is distributed over a larger volume of material, as a result of which the wear protection layer 8 is loaded less locally.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17198765.4A 2016-11-18 2017-10-27 Système d'étanchéité pour une turbomachine et turbomachine axiale Active EP3324002B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016222720.3A DE102016222720A1 (de) 2016-11-18 2016-11-18 Dichtungssystem für eine axiale Strömungsmaschine und axiale Strömungsmaschine

Publications (2)

Publication Number Publication Date
EP3324002A1 true EP3324002A1 (fr) 2018-05-23
EP3324002B1 EP3324002B1 (fr) 2021-06-16

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EP17198765.4A Active EP3324002B1 (fr) 2016-11-18 2017-10-27 Système d'étanchéité pour une turbomachine et turbomachine axiale

Country Status (4)

Country Link
US (1) US20180142567A1 (fr)
EP (1) EP3324002B1 (fr)
DE (1) DE102016222720A1 (fr)
ES (1) ES2881326T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3822461A1 (fr) * 2019-11-15 2021-05-19 MTU Aero Engines AG Système d'étanchéité de turbomachine axiale
FR3107720A1 (fr) * 2020-02-27 2021-09-03 Safran Aircraft Engines Aube de turbine, procédé de fabrication ou de reconditionnement du talon de ladite aube

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Publication number Priority date Publication date Assignee Title
US11060407B2 (en) * 2017-06-22 2021-07-13 General Electric Company Turbomachine rotor blade
FR3100271B1 (fr) * 2019-09-04 2022-08-26 Safran Aircraft Engines Aube de turbomachine comportant un talon pourvu d’un becquet à plateforme déportée
DE102019216646A1 (de) * 2019-10-29 2021-04-29 MTU Aero Engines AG Laufschaufelanordnung für eine strömungsmaschine
WO2021199718A1 (fr) * 2020-03-30 2021-10-07 株式会社Ihi Structure de suppression d'écoulement secondaire

Citations (5)

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Also Published As

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US20180142567A1 (en) 2018-05-24
ES2881326T3 (es) 2021-11-29
EP3324002B1 (fr) 2021-06-16
DE102016222720A1 (de) 2018-05-24

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