EP3587739A1 - Agencement d' anneau de carter pour une turbomachine - Google Patents

Agencement d' anneau de carter pour une turbomachine Download PDF

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Publication number
EP3587739A1
EP3587739A1 EP19182756.7A EP19182756A EP3587739A1 EP 3587739 A1 EP3587739 A1 EP 3587739A1 EP 19182756 A EP19182756 A EP 19182756A EP 3587739 A1 EP3587739 A1 EP 3587739A1
Authority
EP
European Patent Office
Prior art keywords
ring
segment
segments
arrangement
jacket
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
EP19182756.7A
Other languages
German (de)
English (en)
Inventor
Manfred Feldmann
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
Publication of EP3587739A1 publication Critical patent/EP3587739A1/fr
Pending legal-status Critical Current

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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
    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and 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
    • 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
    • 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
    • F01D11/12—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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/11—Shroud seal segments
    • 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
    • F05D2240/11—Shroud seal segments
    • 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 jacket ring arrangement for a turbomachine.
  • the turbomachine can, for example, be a jet engine, e.g. B. a turbofan engine.
  • the fluid machine is functionally divided into a compressor, combustion chamber and turbine.
  • the air drawn in is compressed by the compressor and burned in the downstream combustion chamber with added kerosene.
  • the resulting hot gas a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process.
  • the turbine is typically subdivided into several modules, so it can have, for example, a high-pressure and a low-pressure turbine module.
  • Each of the turbine modules then generally comprises a number of stages, each stage being composed of a guide vane ring and a rotor blade ring which follows downstream.
  • the jacket ring arrangement in question comprises a housing part and a jacket ring segment which is mounted radially on the inside of the housing part.
  • the casing ring segment delimits the gas channel radially outward, specifically at the axial height of a rotor blade ring.
  • the jacket ring segment can be equipped, for example, with a sealing system or an inlet lining, along which the rotor blades of the ring graze with their outer cover bands. This should, such as. B. also the reference to a jet engine, illustrate the present subject, but initially not restrict it in its generality.
  • the present invention is based on the technical problem of specifying a particularly advantageous casing ring arrangement.
  • the object relates to the attachment or assembly of the jacket ring segment to the housing part, which is done with a segment ring.
  • This segment ring is or is assembled from the radially inside with a positive locking element of the housing part.
  • the segment ring is circumferentially divided into a plurality of segments, which are handled individually and can therefore be assembled one after the other from radially inside to radially outside with the form-locking element of the housing part.
  • the fully assembled segment ring is held on the housing part in an axially positive manner.
  • the segment ring also forms a support on which the jacket ring segment is seated and is thus supported radially inwards.
  • the approach according to the invention can initially be advantageous for thermal reasons.
  • the shielding of the housing can be improved, and the support of the jacket ring segment can also be better sealed off from the gas channel.
  • comparatively high thermal gradients would also occur on this or in the housing, which can limit the service life.
  • the jacket ring segment itself could also bring a suspension element at its front end, which is positively mounted on the housing part instead of the segment ring.
  • the jacket ring segment would have to be provided as a casting with a corresponding thickness in order to create a sufficiently stable suspension element.
  • the jacket ring segment can preferably be designed as a sheet metal part (see below), which offers cost and weight advantages. Due to the greater weight, a casting is also in its extension limited in the direction of circulation, there would be a larger number of impacts over the entire circulation (heating in the narrow gaps).
  • a jacket ring segment with an integral suspension element is also comparatively complex and cost-intensive, which can be disadvantageous with regard to manufacture and also maintenance.
  • An inlet seal can be arranged on the casing ring segment, into which the rotor blades or outer sealing fins of the rotor blades can run.
  • axially generally relates to the longitudinal axis of the turbine module, and thus therefore the longitudinal axis of the turbomachine, which coincides, for example, with an axis of rotation of the rotors.
  • Rotary relates to the radial directions pointing away from it, and a “rotation” or “circumferential” or the “rotation direction” relates to the rotation about the longitudinal axis.
  • Forward and “rear” refer to the axial flow direction component of the hot gas, so this passes “front” parts axially in front of “rear” parts.
  • “one” and “one” are to be read as indefinite articles without expressly stated otherwise and therefore always as “at least one” or "at least one”.
  • the jacket ring segment is supported with its axially front end on the segment ring, with its axially rear end it preferably lies on the outer shroud of the following guide vane ring.
  • a module is usually assembled from axially front to axially rear, in the present case, for example, the segment ring can first be mounted on the housing part and the jacket ring segment can then be inserted.
  • assembly or disassembly from the front axially is also possible with the segmented segment ring. This can be particularly advantageous when overhauling the turbomachine, see below in detail.
  • the segment ring or its segments can be produced from a forged ring, for example, by turning and milling.
  • the segments can also be cast parts (in connection with a reworking of the functional surfaces).
  • additive manufacturing is also possible, ie the segment ring or segments can be built additively layer by layer from a previously formless or neutral material.
  • the segment ring can, for example, form an inverted T-shape at its radially inner end. Its inner circumferential surface can preferably form a seal to an axially upstream gas channel component, for example, represent a piston ring running surface.
  • the assembled segment ring is held on the form-fitting element in an axially positive manner.
  • the positive locking element of the housing part z. B. be a radially inward open groove in which the segment ring engages with a radially protruding web.
  • the arrangement is exactly the reverse, that is to say the form-locking element of the housing part is a web projecting radially inwards and seated in a receptacle of the segment ring which is open radially outwards.
  • the individual segments of the segment ring are or are pushed radially outward onto the web of the housing part.
  • the segments can each be U-shaped in a radially outer section, the U-shape is pushed onto the web.
  • the web of the housing part viewed in an axial section, extends at an angle of at most 30 ° to the radial direction, with at most 20 ° or 10 ° being further preferred.
  • the smaller of two angles is considered here, which includes a straight line in the axial section in the web with the radial direction.
  • the web is preferably perpendicular to the longitudinal axis, so the angle is 0 °. This can be the design and also simplify the assembly, although in general an assembly from the inside is still possible even with an inclined web, as long as the assembly play and the elasticity of the segments can bridge undercuts (which result with increasing angle).
  • a securing ring is provided, on which the segments of the segment ring are supported in a radially inward manner.
  • the locking ring presses the segments radially outward into contact with the form-locking element.
  • the locking ring can extend uninterrupted in the circumferential direction.
  • a radial locking of the segments with or via a housing part is generally also conceivable, for example an axially upstream housing part could provide a corresponding fixation of the segments.
  • the retaining ring which is closed all the way round (continuous without interruption), is pressed axially into a receptacle in the segment ring.
  • the receptacle preferably faces the front axially, that is to say the retaining ring is pressed in axially to the rear.
  • the retaining ring is held in the receptacle by a press fit.
  • the segment ring forms a radially protruding projection on the receptacle, behind which the retaining ring is held in an axially positive manner.
  • This projection is preferably formed on an inner wall surface of the segment ring pointing radially inwards, against which the securing ring used rests with an outer wall surface.
  • the projection is dimensioned such that the locking ring can be pressed in axially, but is then secured axially in the opposite direction. This is preferably supported by an inclined flank (sawtooth profile), along which the locking ring slides when pressed in.
  • the jacket ring segment is a sheet metal part, which can be advantageous, for example, in terms of costs (first production and also maintenance), but also in terms of weight.
  • a seal can be attached radially on the inside of the sheet metal part be (e.g. soldered on), such as a so-called honeycomb seal.
  • a sheet metal part is not mandatory, and many of the advantages mentioned (for example, mountability "from the front") can also be achieved with a jacket ring segment produced as a cast part or generatively.
  • At least one of the segments has abutting edges that are parallel to one another when viewed in the axial direction.
  • the segment with the mutually parallel abutting edges can also be pushed in or pushed on when the all-round neighboring segments are already arranged in their assembly position.
  • the segment can be inserted along an insertion direction parallel to its abutting edges. In the direction of insertion, the segment is brought into its position in the segment ring.
  • the mutually parallel abutting edges are preferably oriented such that they or their extensions towards the opposite side of the segment ring surround the center of the circle of the segment ring in the center.
  • every second segment has mutually parallel abutting edges in the circumferential direction.
  • the segments with the abutting edges parallel to each other are preferably identical to one another and the complementary segments arranged between them are also identical to one another, so that the entire segment ring can be constructed with only two different segment types.
  • the segments are or are set up in such a way that the segment ring can ideally be constructed from only a single segment ring type.
  • This can be achieved with a butt edge, which in Axial direction is oriented obliquely to the radial direction.
  • the oblique butt edge forms an angle ⁇ of at least 85 ° and at most 110 ° with a connecting line that extends diagonally through the segment to the outer corner of the oblique butt edge.
  • Further preferred upper limits are at most 100 ° or 95 °, further preferred lower limits are (irrespective of this) at least 88 ° or 90 ° (in the order in which they are mentioned increasingly preferred).
  • the segment can also be used when the circumferentially next-adjacent segments are already arranged in their assembly position.
  • the segment can first be brought into position with the opposite butt edge and then, as it were, turned into a system with the oblique butt edge, cf. Figure 4 for illustration.
  • all segments are identical to one another, that is to say rotationally symmetrical about the longitudinal axis. Keeping and assembling just one type of segment ring can simplify assembly and warehousing.
  • a sealing insert preferably a sealing plate, is used on a joint where two segments adjoin one another with their abutting edges.
  • a pocket open to the joint is provided in each of these two segments; the sealing insert is held axially therein and extends over the joint. So that these segments can still be assembled from the radially inside, one of the pockets is preferably open radially outwards.
  • the sealing insert is then placed in the other pocket, which is closed radially inwards and outwards, and when the other segment is positioned, it slides into the pocket, which is open radially outwards.
  • the invention also relates to a turbine module with a jacket ring arrangement disclosed herein.
  • a rotor blade ring is arranged radially within the casing ring segment.
  • the turbine module preferably has an axially downstream guide vane ring, on the outer shroud of which the jacket ring segment rests with its axially rear end (supported radially inward).
  • the jacket ring arrangement with the jacket ring segment is preferably part of the axially foremost stage of the module because it is possible to remove it axially from the front.
  • other or all stages of the turbine module can also be equipped with a jacket ring arrangement according to the invention.
  • the invention also relates to a method for overhauling a corresponding turbine module, the jacket ring segment being removed from the front axially by removing the segment ring.
  • the individual modules (low pressure or high pressure etc.) of the turbine can be separated from one another comparatively easily, so that each module is accessible from the axially front and axially rear. Accessibility from the front axially can also be advantageous insofar as axially front components can be subjected to greater loads.
  • the invention also relates to the use of a corresponding turbine module or a jacket ring arrangement disclosed in a turbomachine, in particular in a jet engine, for example a jacket power engine.
  • Fig. 1 shows a turbomachine 1, specifically a turbofan engine, in an axial section.
  • the flow machine 1 is functionally divided into a compressor 1a, a combustion chamber 1b and a turbine 1c.
  • Both the compressor 1a and the turbine 1c are each made up of several stages, each stage being composed of a guide vane ring and a subsequent rotor blade ring.
  • the rotor blades rotate during operation about the longitudinal axis 2 of the turbomachine 1.
  • the air sucked in is compressed in the compressor 1a and then burned in the downstream combustion chamber 1b with added kerosene.
  • the hot gas flows through the hot gas duct 3 and drives the rotor blades, which rotate about the longitudinal axis 2.
  • Fig. 2 shows a jacket ring arrangement 20, which is provided as part of a module of the turbine 1c. It has a housing part 21 and a jacket ring segment 22, on which a seal 23 is arranged radially on the inside, in the present case an inlet coating in the form of a honeycomb seal.
  • the jacket ring segment 22 surrounds the blades 24 radially outward.
  • a segment ring 25 is provided, which is divided into a plurality of segments in the circumferential direction (cf. Fig. 3 and 4 ).
  • the individual segments of the segment ring 25 are assembled from the inside radially with a form-locking element 26 of the housing part 21.
  • the form-locking element 26 is provided in the present case as a radially inwardly projecting housing web onto which the segments of the segment ring 25 are pushed until the housing web finds a radial contact in a receptacle 25a of the segment ring 25.
  • the segments of the segment ring are then also held in an axially positive manner.
  • the segment ring 25 forms a support 27 which supports the jacket ring segment 22 radially inward at its axially front end.
  • a locking ring 28 is used to hold the segments of the segment ring 25 radially in position. This extends circumferentially without interruption and is pressed axially into a receptacle 29 of the segment ring 25. In the receptacle 29, it is held axially positively behind a projection 30.
  • a bore 31 is provided in the form-locking element 26 or the housing web of the housing part 21, which can be used (and is optional) for supplying a cooling fluid.
  • the shielding plates 32 arranged radially between the housing part 21 and the casing ring segment 22 are optional; the approach according to the invention could also be realized with an insulating material or the like between the housing part 21 and the casing ring segment 22.
  • Fig. 3 shows the segment ring 25 in a section perpendicular to the longitudinal axis 2 (for the sake of clarity without hatching), namely a section of the segment ring with some segments 35, 36.
  • the segments 35, 36 each have abutting edges 35a, 36a with which they adjoin one another.
  • the segment ring 25 is constructed from two types of segment rings. On the one hand there are the segments 35, the abutting edges 35a of each segment 35 are parallel to one another. These segments 35 and the complementary segments 36 follow one another alternately. Due to the mutually parallel abutting edges 35a, the segments 35 can each be pushed into their installation position in an insertion direction 37; the next neighboring segments 36 are brought into position beforehand.
  • Fig. 4 points to Fig. 3 alternative segments 40, with which the entire segment ring 25 can be constructed from a single segment ring type.
  • a butt edge 40a is inclined in such a way that it forms an angle ⁇ of around 90 ° with a connecting line 41.
  • the opposite abutting edge 40b is complementarily oblique, it forms an obtuse angle on an inner peripheral surface 42 of the segment ring and an acute angle on the outer peripheral surface 43.
  • a corresponding segment 40 can first be hooked in with the abutting edge 40b if the circumferentially next adjacent segments 40 are already in the assembly position. The segment 40 is then screwed into its assembly position.
  • sealing inserts 46 are provided on the joints 45.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19182756.7A 2018-06-28 2019-06-27 Agencement d' anneau de carter pour une turbomachine Pending EP3587739A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018210600.2A DE102018210600A1 (de) 2018-06-28 2018-06-28 Mantelringanordnung für eine strömungsmaschine

Publications (1)

Publication Number Publication Date
EP3587739A1 true EP3587739A1 (fr) 2020-01-01

Family

ID=67105801

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19182756.7A Pending EP3587739A1 (fr) 2018-06-28 2019-06-27 Agencement d' anneau de carter pour une turbomachine

Country Status (3)

Country Link
US (1) US11434785B2 (fr)
EP (1) EP3587739A1 (fr)
DE (1) DE102018210600A1 (fr)

Cited By (1)

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Publication number Priority date Publication date Assignee Title
EP4028644B1 (fr) * 2019-09-13 2023-06-07 Safran Aircraft Engines Anneau d'étanchéité de turbomachine

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Publication number Priority date Publication date Assignee Title
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
CN116517641A (zh) * 2022-01-24 2023-08-01 通用电气公司 弯曲梁堆叠结构柔性的护罩
US12031443B2 (en) * 2022-11-29 2024-07-09 Rolls-Royce Corporation Ceramic matrix composite blade track segment with attachment flange cooling chambers

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