EP3375980A1 - Porte-joint pour une turbomachine - Google Patents

Porte-joint pour une turbomachine Download PDF

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Publication number
EP3375980A1
EP3375980A1 EP17160464.8A EP17160464A EP3375980A1 EP 3375980 A1 EP3375980 A1 EP 3375980A1 EP 17160464 A EP17160464 A EP 17160464A EP 3375980 A1 EP3375980 A1 EP 3375980A1
Authority
EP
European Patent Office
Prior art keywords
seal carrier
sealing structure
cavity
turbomachine
sealing
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
EP17160464.8A
Other languages
German (de)
English (en)
Other versions
EP3375980B1 (fr
Inventor
Steffen Schlothauer
Frank Stiehler
Alexander Ladewig
Christian Liebl
Johannes Casper
Jürgen Kraus
Andreas Jakimov
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
Original Assignee
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
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP17160464.8A priority Critical patent/EP3375980B1/fr
Priority to US15/911,380 priority patent/US20180258784A1/en
Publication of EP3375980A1 publication Critical patent/EP3375980A1/fr
Application granted granted Critical
Publication of EP3375980B1 publication Critical patent/EP3375980B1/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
    • 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
    • F01D11/12—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
    • F01D11/122—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 erodable or abradable material
    • F01D11/125—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 erodable or abradable material with a reinforcing structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • 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

Definitions

  • the present invention relates to a seal carrier for a turbomachine.
  • the turbomachine may preferably be a jet engine.
  • One component of this is a so-called seal carrier, which encloses the hot gas duct radially outward in the region of a rotor blade ring.
  • a seal carrier has a first and a second seal carrier segment, which are assembled successively relative to a circulation about a longitudinal axis of the turbomachine. Radially inside, the first seal carrier segment has a first sealing structure and the second seal carrier segment has a second sealing structure.
  • the present invention is based on the technical problem of specifying a particularly advantageous seal carrier for a turbomachine.
  • this object solves, on the one hand, a seal carrier according to claim 1, in which the first and the second sealing structure are entangled with respect to the circulation about the longitudinal axis of the turbomachine in such a way that a sectional plane which includes the longitudinal axis of the turbomachine both the first and also the second sealing structure intersects, as well as to the other a seal carrier according to claim 9, wherein the first and the second sealing structure abut each other.
  • the two solution variants ie the "entanglement" of the sealing structures according to claim 1 or their “contact” to each other according to claim 9, is based on the same inventive idea, namely to extend or block the flow path between the sealing structures.
  • the sealing effect can be improved and thus achieve a higher efficiency.
  • a parting line between the sealing structures is generally located between the sealing structures with a size of between 0.3 mm and 0.4 mm (taken in the direction of rotation) and continuous axially in an axial direction extends. This causes leaks and loss of efficiency result.
  • sealing structures are entangled with each other or abut each other, the latter at least in the hot state, preferably also already in the cold state.
  • the flow path is thus at least extended.
  • cutting plane which includes the longitudinal axis of the turbomachine (hereinafter also “turbomachine longitudinal axis”), that extends axially and radially, intersects both the first and the second sealing structure due to the entanglement.
  • the first and the second seal carrier segment may preferably each be a half-shell, see below.
  • the second transition between the sealing structures of the half-shells is optimized, preferably analogous to the first (ie the two transitions are then optimized either by the entanglement or the system) , Quite generally, in the seal carrier, preferably all transitions between circumferentially successive sealing structures, which are respectively assigned to different seal carrier segments, are flow-optimized in the manner according to the invention.
  • the seal carrier is "composed" of the seal carrier segments, the latter are thus previously made separately for each separately and then assembled.
  • the assembly can generally be made cohesively, for example by welding or soldering, such as inductive soldering.
  • a seal carrier which is composed of two seal carrier half-shells, which are assembled together only form-fitting and / or non-positively.
  • the seal carrier half-shells can, however, for example, in turn be constructed in each case from a plurality of seal carrier segments which are materially connected to each seal carrier half-shell, in particular soldered, preferably each of three seal carrier segments. Both transitions are preferred between the seal carrier half-shells as well as those within a respective half-shell in accordance with the invention flow-optimized.
  • the production of the seal carrier segments is preferably generative, that is to say by selective solidification of a shapeless or shape-neutral material, see below in detail. With the generative structure, the interlacing or investment structures can be generated particularly well.
  • the parting line has a parting line between the first and the second sealing structure seen in the radial direction, looking approximately radially from the turbomachine longitudinal axis thereon, at least in sections an angled to the axial direction course.
  • the parting line should not extend axially straight through, but for example.
  • the flow path between the sealing structures is lengthened by the course, which is angled at least in sections, that is to say in any case in an axial section, to the axial direction.
  • Angled may mean, for example, an angle of 90 °, for example in the case of a pure step shape, also in conjunction with an otherwise axis-parallel extent;
  • any angle smaller than 90 ° are possible (considered always the smallest included with the axial direction angle), wherein the angle over the axial extent of the parting line can also change.
  • the parting line can extend at least in sections angled to the radial direction; However, preferred is a parting line with a straight line in the radial direction, only radial extent.
  • turbomachine longitudinal axis As far as generally referred to in the context of this disclosure to an arrangement “axial” or an “axial direction”, this refers to the turbomachine longitudinal axis.
  • the “turbomachine longitudinal axis” is then, for example, an axis of rotation about which the rotor blade ring arranged in the seal carrier is rotatably mounted.
  • radial or the “radial direction” refer to the turbomachine longitudinal axis, namely, are perpendicular to it.
  • circulation and “circulation direction” refer to it, namely to a circulation around the turbomachine longitudinal axis as a rotation axis.
  • the sealing structures preferably form a cavity structure with a plurality of cavities axially and circumferentially separated from one another via cavity walls.
  • the cavities are enclosed axially and circumferentially by the cavity walls and are preferably closed radially outward, to the turbomachine longitudinal axis, ie radially inward, they are open.
  • a honeycomb structure may be preferable.
  • the cavities delimited by the cavity walls then each have a hexagonal shape when viewed in the radial direction. However, this is generally not mandatory.
  • the parting line passes through at least one of the cavities.
  • This at least one cavity is then formed jointly by the first and the second sealing structure, the sealing structures are at the parting line to each other so at least partially open (relative to the direction of rotation).
  • the sealing structures are closed at the parting line to each other, so the parting line is circumferentially enclosed on both sides of separating gap side cavity walls of the two sealing structures over its entire extent.
  • the parting line is at least in sections angled extending parting line inserted into the cavity structure such that it extends between the cavities of the sealing structures and thereby passes through any of the cavities.
  • the parting line is thus laid exclusively along cavity walls through the structure.
  • the cavities are arranged regularly at least in the direction of rotation, even beyond the parting line.
  • a specific sequence of differently shaped and / or arranged cavities may occur periodically, ie repeatedly, over the course of time, in general, for example.
  • exactly one type cavity (a shape) is repeated over the revolution, and more preferably circumferentially in equidistant arrangement and alignment (the arrangement is rotationally symmetric with a certain number of counts).
  • the cavities are also regularly arranged in the axial direction, that is to say that the same type of cavity is particularly preferably repeated in the axial direction in an equidistant arrangement.
  • the cavities as seen in the radial direction, each have a polygonal outer shape, particularly preferably a hexagonal shape (honeycomb shape).
  • the parting line can then extend along two side edges for each adjacent honeycomb, ie, describe a zig-zag line.
  • the sealing structures are entangled with one another such that a cavity wall of the first sealing structure extends in the circumferential direction into the second sealing structure. This cavity wall of the first sealing structure is then arranged axially between cavity walls of the second sealing structure, but preferably also axially spaced therefrom.
  • a cavity wall of the second sealing structure preferably also extends in the direction of rotation into the first sealing structure (and is arranged axially between cavity walls of the first sealing structure). More preferably, each sealing structure has a respective plurality of cavity walls extending in the direction of rotation into the respective other sealing structure.
  • a cavity wall of the first sealing structure merges into a cavity wall of the second sealing structure at the sectional plane, namely the two cavity walls together form a positive connection with one another.
  • This positive engagement is intended to block relative displacement with respect to the axial direction, generally only with respect to one of the axial directions, but preferably with respect to both opposite axial directions.
  • the intermeshing cavity walls are nut and spring-like composite, thus forming one of the cavity walls at its circumferential end a groove into which the other cavity wall is inserted with its circumferential end.
  • Their longitudinal extent, the groove base and the spring in this case each have substantially in the radial direction.
  • the first sealing structure has a spring element and rests with this spring element on the second sealing structure.
  • the spring element forms a contact surface, which is mounted elastically displaceable as a result of the spring property in the direction of rotation.
  • This "elastic-displaceable-bearing-being" goes beyond a material inherent, beyond the E-modulus detected elasticity, namely, for example, supported by an at least partially or partially cantilever designed spring element geometry.
  • the spring element can, for example, have a clasp or bridge shape.
  • the second sealing structure on a spring element which forms an elastically displaceably mounted bearing surface, wherein the two sealing structures then abut each other with their spring elements.
  • an elastically mounted contact surface may be of interest with a view to a certain offset compensation, cf. also the comments above.
  • a seal carrier can be realized in which the sealing structures lie against one another in both the cold and the hot state, without material-critical strains.
  • the spring element is slidably mounted with a storage area in the remaining sealing structure, wherein the offset of the contact surface in the direction of rotation is proportionately converted into a displacement of the storage area.
  • the spring element can also be formed monolithically with the rest of the sealing structure at its opposite end, but preferably it has a further storage area, which is likewise displaceably mounted in the remaining sealing structure.
  • a relative mobility (of the storage point with respect to the remaining sealing structure) with at least one directional component in the axial direction results as a result of the "displaceably stored" being, preferably a total axially aligned displacement distance.
  • a corresponding sealing structure with a spring element can be generated generatively in a particularly advantageous manner produce, where the bearing is then, for example, partially constructed with a sacrificial material and the relative mobility is then given after its release.
  • the seal carrier segments each have a support structure radially outside the respective sealing structure.
  • the seal carrier segments are connected to each other via their support structures, in particular positive and / or non-positive, but apart from that, in their sealing structures movable relative to each other.
  • the first seal carrier segment is a first seal carrier half-shell and the second seal carrier segment is a second seal carrier half-shell, see. also the comments at the beginning.
  • each of the seal carrier half shells circumferentially extends over 180 °.
  • the seal carrier is then, based on the direction of rotation, composed exclusively of the two seal carrier half shells, these are positively and / or non-positively connected to each other, preferably exclusively positive and / or non-positive. In other words, form the two half-shells over the entire circulation the seal carrier, so there are in the seal carrier apart from the half-shells no further seal carrier segments.
  • the seal carrier segments are each in a preferred embodiment for themselves generatively manufactured parts.
  • the parts are constructed on the basis of a data model from an informal or shape-neutral material which, for example, is converted selectively into regions in a dimensionally stable state by means of physical and / or chemical processes, for example by selective local melting.
  • a wide range of different geometries can be produced, that is, for example, in the sealing structure, a spring element can be molded or can be realized in the circumferential direction protruding cavity walls, which then protrude into the other sealing structure after assembly.
  • a support structure which is then ideally constructed with the sealing structure in the same process, can be made to special structural mechanical requirements are optimized.
  • a construction of a powder bed may be preferred for the seal carrier segments, that is to say by layerwise selective solidification of a powder bed by appropriately selective irradiation, preferably by a laser beam.
  • the invention also relates to a turbomachine with a presently disclosed seal carrier, in particular a jet engine.
  • FIGS. 1a-c each illustrate a first sealing structure 1a and a second sealing structure 1b, looking radially to a turbomachine longitudinal axis 2 thereon.
  • the sealing structures 1a, b are each part of a respective seal carrier half-shell (not shown in detail), the seal carrier half-shells are assembled into a seal carrier.
  • the seal carrier half shells radially outside the respective sealing structure 1a, b each have a support structure, via which the half shells are connected to one another.
  • the sealing structures 1a, b shown in the figures form the radially inner part of the seal carrier.
  • the seal carrier has an overall ring shape and limits the hot gas channel of a jet engine radially outward. In the jet engine, the seal carrier accommodates a blade ring, with its radially outer ends, the blades then strip along the sealing structure 1 shown in the figures, this is also referred to as inlet lining.
  • the first sealing structure 1a and the second sealing structure 1a form a cavity structure with a plurality of radially inwardly open, honeycomb-shaped cavities 3. Axially and in the direction of rotation 4, the cavities 3 via cavity walls 5 are separated from each other.
  • first 1a and the second sealing structure are open at the parting line 6 towards each other.
  • the parting line 6 thus passes through some of the cavities 3, the cavities 3 arranged on the parting line 6 are delimited both by cavities 5 of the first 1a and by the second sealing structure 1b.
  • FIGS. 1a-c then in the course of the parting line 6.
  • FIG. 1a a parting line 6 with a step, but apart from axis-parallel extension.
  • the parting line 6 according to FIG. 1b over its entire axial extent a curved course, the included with the axial direction angle changes over the axial extent.
  • the parting line 6 of the embodiment according to Figure 1c Although considered by itself a straight line extension, but is tilted overall to the axial direction.
  • Each of these embodiments is advantageous insofar as the parting line 6 is lengthened compared to a rectilinear and exclusively axially parallel extension, which lengthens the flow path accordingly and thus increases the flow resistance. This can improve the efficiency, cf. also the description introduction.
  • FIG. 2 An improved efficiency also gives the embodiment according to FIG. 2 in which the parting line 6 describes a zig-zag line.
  • the first 1a and the second sealing structure 1b in this case closed to each other at the parting line 6.
  • the parting line 6 does not penetrate any of the cavities 3. It is encircled on both sides by separating-cavity-side cavity walls 5aa, 5ba of the respective sealing structure 1a, b.
  • An extension of the flow path between the sealing structures 1a, b is achieved by extending cavity walls 5ab of the first sealing structure 1a into the second sealing structure 1b and extending cavity walls 5bb of the second sealing structure 1b into the first sealing structure 1a.
  • the flow path is thus extended labyrinth-like.
  • the first 1a and the second sealing structure 1b were entangled with each other, so there is a sectional plane containing the turbomachine longitudinal axis 2 (the sectional plane extends axially and radially) which intersects both the first 1a and the second sealing structure 1b , In the illustrated embodiments, this cutting plane would be horizontal in the plane of the drawing and perpendicular thereto.
  • an extension or blockage of the flow paths between the sealing structures 1a, b is achieved.
  • the sealing structures abut one another, for which purpose they each have a spring element 50a, b.
  • the spring elements 50a, b each form a contact surface 51a, b, so they rest against each other. Due to the resilient properties of the contact surfaces 51a, b mounted in the direction of rotation a bit far elastically displaceable, which allows an offset compensation, such as in the case of temperature fluctuations.
  • the spring elements 50a, b are each axially end connected to the rest of the respective sealing structure 1a, b, between them they are designed to support the spring function cantilevered.
  • the spring element 50a is mounted so as to be displaceable in the remaining sealing structure, with two bearing regions 50aa arranged at the axially opposite ends. If the abutment surface 51 is thus offset in the direction of rotation 4, a part of this offset is converted into a displacement of the bearing regions 50aa, ab.
  • FIG. 6 shows a turbomachine 60, namely a jet engine, in a schematic section, wherein the cutting plane includes the longitudinal axis 2 of the turbomachine 60.
  • the turbomachine is functionally divided into compressor 60a, combustion chamber 60b and turbine 60c.
  • the compressor 60a is constructed of a plurality of stages 61a, b, in each of which a blade ring follows a vane ring (not shown in detail).
  • the turbine is also constructed in several stages, with only one blade ring 62 being shown for the sake of clarity. After radially outward, the blade ring 62 is bordered by a seal carrier 63, which is constructed in a manner described above. The blades therefore graze along the in FIG. 6 Not shown in detail sealing structure of the seal carrier 63.
  • the blade rings of the compressor 60a can each be enclosed by a seal carrier according to the invention, which is also not shown in detail.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gasket Seals (AREA)
EP17160464.8A 2017-03-13 2017-03-13 Porte-joint pour une turbomachine Active EP3375980B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17160464.8A EP3375980B1 (fr) 2017-03-13 2017-03-13 Porte-joint pour une turbomachine
US15/911,380 US20180258784A1 (en) 2017-03-13 2018-03-05 Seal carrier for a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17160464.8A EP3375980B1 (fr) 2017-03-13 2017-03-13 Porte-joint pour une turbomachine

Publications (2)

Publication Number Publication Date
EP3375980A1 true EP3375980A1 (fr) 2018-09-19
EP3375980B1 EP3375980B1 (fr) 2019-12-11

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EP17160464.8A Active EP3375980B1 (fr) 2017-03-13 2017-03-13 Porte-joint pour une turbomachine

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US (1) US20180258784A1 (fr)
EP (1) EP3375980B1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021018333A1 (fr) * 2019-08-01 2021-02-04 MTU Aero Engines AG Module pour une turbomachine
WO2021110191A1 (fr) 2019-12-06 2021-06-10 MTU Aero Engines AG Support d'étanchéité conçu pour une turbomachine comportant des ouvertures de type fentes dans le corps d'étanchéité

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3081499B1 (fr) * 2018-05-23 2021-05-28 Safran Aircraft Engines Secteur angulaire d'aubage de turbomachine a etancheite perfectionnee

Citations (3)

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Publication number Priority date Publication date Assignee Title
EP0716218A1 (fr) * 1994-12-05 1996-06-12 United Technologies Corporation Virole de compresseur
DE102005002270A1 (de) * 2005-01-18 2006-07-20 Mtu Aero Engines Gmbh Triebwerk
EP2617949A2 (fr) * 2012-01-23 2013-07-24 MTU Aero Engines GmbH Agencement d'étanchéité pour turbomachines

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Publication number Priority date Publication date Assignee Title
US4431376A (en) * 1980-10-27 1984-02-14 United Technologies Corporation Airfoil shape for arrays of airfoils
FR2577281B1 (fr) * 1985-02-13 1987-03-20 Snecma Carter de turbomachine associe a un dispositif pour ajuster le jeu entre aubes mobiles et carter
US6341938B1 (en) * 2000-03-10 2002-01-29 General Electric Company Methods and apparatus for minimizing thermal gradients within turbine shrouds
DE10259963B4 (de) * 2002-12-20 2010-04-01 Mtu Aero Engines Gmbh Wabendichtung
US8534993B2 (en) * 2008-02-13 2013-09-17 United Technologies Corp. Gas turbine engines and related systems involving blade outer air seals
GB201614070D0 (en) * 2016-08-17 2016-09-28 Rolls Royce Plc A component for a gas turbine engine and method of manufacture

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0716218A1 (fr) * 1994-12-05 1996-06-12 United Technologies Corporation Virole de compresseur
DE102005002270A1 (de) * 2005-01-18 2006-07-20 Mtu Aero Engines Gmbh Triebwerk
EP2617949A2 (fr) * 2012-01-23 2013-07-24 MTU Aero Engines GmbH Agencement d'étanchéité pour turbomachines

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021018333A1 (fr) * 2019-08-01 2021-02-04 MTU Aero Engines AG Module pour une turbomachine
WO2021110191A1 (fr) 2019-12-06 2021-06-10 MTU Aero Engines AG Support d'étanchéité conçu pour une turbomachine comportant des ouvertures de type fentes dans le corps d'étanchéité
DE102019219090A1 (de) * 2019-12-06 2021-06-10 MTU Aero Engines AG Dichtungsträger für eine Turbomaschine mit schlitzartigen Öffnungen im Dichtungskörper

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US20180258784A1 (en) 2018-09-13
EP3375980B1 (fr) 2019-12-11

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