Nothing Special   »   [go: up one dir, main page]

EP3409902B1 - Système d'étanchéité pour compresseur de turbomachine - Google Patents

Système d'étanchéité pour compresseur de turbomachine Download PDF

Info

Publication number
EP3409902B1
EP3409902B1 EP18173133.2A EP18173133A EP3409902B1 EP 3409902 B1 EP3409902 B1 EP 3409902B1 EP 18173133 A EP18173133 A EP 18173133A EP 3409902 B1 EP3409902 B1 EP 3409902B1
Authority
EP
European Patent Office
Prior art keywords
annular
compressor
rotor
tooth
rib
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.)
Active
Application number
EP18173133.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3409902A1 (fr
Inventor
Stéphane Hiernaux
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.)
Safran Aero Boosters SA
Original Assignee
Safran Aero Boosters SA
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 Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP3409902A1 publication Critical patent/EP3409902A1/fr
Application granted granted Critical
Publication of EP3409902B1 publication Critical patent/EP3409902B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D11/001—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/022—Multi-stage pumps with concentric rows of vanes
    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/312—Layer deposition by plasma spraying
    • 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
    • F05D2230/60—Assembly methods
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/506—Hardness

Definitions

  • the invention relates to sealing in an axial turbomachine compressor, in particular at the level of an internal shroud.
  • the invention also relates to an axial turbomachine, such as an aircraft turbojet or an aircraft turboprop.
  • the invention also provides a method of manufacturing a compressor.
  • the compression ratio at the outlet of a turbojet compressor depends on the tightness between the ferrules and the rotor. This tightness must adapt to vibrations as well as ingestion when it is a low pressure compressor. The centrifugal force and the expansion remain constraints which are added to the previous ones.
  • each internal ferrule or each internal ferrule segment comprises: a circular or semi-circular wall whose profile extends mainly axially; and a row of openings formed in the axial wall. Each opening has opposite edges intended to be arranged laterally on either side of a stator vane positioned in said opening for its attachment.
  • the wall comprises a radial flange which crosses the openings in the circumferential direction of the ferrule or of the ferrule segment, so as to form a mechanical link within each opening to link the opposite edges.
  • the invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to be able to reduce leaks in a compressor. The invention also aims to propose a simple, resistant, light, economical, reliable solution, easy to produce, convenient to maintain, easy to inspect, and improving performance.
  • the subject of the invention is a turbomachine compressor, in particular a low pressure turbomachine compressor, the compressor comprising: a rotor with at least one annular rib; an annular row of stator vanes; an internal ferrule connected to the stator vanes and comprising at least one layer of abradable material capable of cooperating with the at least one annular rib of the rotor in order to ensure sealing; remarkable in that the internal ferrule comprises at least one annular tooth made of abradable material and extending radially towards the rotor.
  • the invention also relates to a turbomachine compressor comprising: a rotor with at least one annular rib; an annular row of stator vanes; an internal ferrule connected to the stator vanes which comprises: at least one layer of abradable material capable of cooperating with the at least one annular rib of the rotor, an annular tooth made of abradable material and extending radially towards the rotor, the radial clearances measured axially at the level of the annular rib and the annular tooth being equal.
  • the invention also relates to a turbomachine, in particular an aircraft turbojet, comprising a compressor, remarkable in that the compressor is in accordance with the invention, preferably the annular tooth comprises an organic material such as a polymer.
  • the invention also relates to a method of manufacturing a turbomachine compressor, the method comprising the following steps: (a) supplying or producing an annular row of stator vanes; (b) fixing an internal ferrule to the annular row of stator vanes, said internal ferrule comprising abradable material; (d) positioning the abradable material of the internal ferrule around an annular rib of a rotor of the compressor; remarkable in that, prior to step (d) positioning, it comprises a step (c) adding at least one annular tooth made of abradable material inside the internal ferrule, at the end of step (d ) positioning, the compressor may be in accordance with the invention.
  • step (c) addition comprises a molding phase, or bonding, or plasma spraying of abradable material inside the inner shell; at the end of step (d) positioning, the compressor is optionally in accordance with the invention.
  • step (c) addition includes a machining phase of the abradable in order to cut the annular tooth there.
  • the abradable material forms the annular tooth.
  • the thicknesses and / or the heights can be average values.
  • each object of the invention is also applicable to the other objects of the invention.
  • Each object of the invention can be combined with the other objects, and the objects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another, according to all possible technical combinations, unless the opposite be explicitly stated.
  • the invention makes it possible to create other wipers on board by the internal ferrule. Their presence brings an effect which is added to that of the rotor, by amplifying the vortices under the ferrule to slow secondary flows. The seal is improved without penalizing the inertia of the rotor.
  • the terms “internal” and “external” refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.
  • abradable material is meant a material capable of crumbling in contact with the rotor in order to limit wear of the latter.
  • the figure 1 represents in a simplified manner an axial turbomachine.
  • the turbojet engine 2 comprises a first level of compression, called a low-pressure compressor 4, a second level of compression, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • a first level of compression called a low-pressure compressor 4
  • a second level of compression called a high-pressure compressor 6
  • a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power from the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator blades.
  • the rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until the inlet of the combustion chamber 8.
  • An inlet fan commonly designated as a fan or blower 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and into a secondary flow 20 passing through an annular duct. (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • the blower may be of the non-vetted type.
  • the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
  • the primary 18 and secondary 20 flows are annular coaxial flows which are fitted one inside the other. They are channeled through the casing of the turbomachine and / or of the ferrules.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor can be a low-pressure compressor 4.
  • One can observe there the separation nozzle 22 of the primary flow 18 and the secondary flow 20.
  • the rotor 12 comprises several rows of rotor blades 24, in this case three. It can be a one-piece drum. It forms a solid connecting all its rows of blades.
  • one, or more, or each of the rows of rotor blades 24 is rigidly linked to the rotor, and therefore to the drum if necessary.
  • the rotor blades are fixed by dovetail.
  • the low-pressure compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.
  • the rectifiers are associated with the fan or a row of rotor vanes to straighten the air flow, so converting the speed of the flow into pressure, in particular into static pressure.
  • the stator vanes 26 extend essentially radially from an external casing 28, and can be fixed and immobilized therein using pins.
  • the casing 28 can be formed from two half-shells.
  • the rows of stator vanes 26 support internal ferrules 30 whose external surfaces guide the primary flow 18.
  • the internal ferrules 30 may have a profile of revolution around the axis of rotation 14. They provide dynamic seals with the rotor 12 , especially in combination with its annular ribs, commonly called wipers. They minimize leaks in the sense that they allow approximation with the rotor, said approximation closing the mechanical clearances in operation.
  • a ferrule and a rotor portion 12 can form a sealing system.
  • the figure 3 outlines a sealing system such as those of the figure 2 .
  • the following are visible: a stator blade 26 representative of its row, an axial section of rotor 12, and an internal ferrule 30.
  • the ferrule 30 can be segmented. It can be made of composite material with an organic matrix reinforced by fibers. The system is shown here at rest, the speed of rotation of the ribs 42 relative to the teeth 32 being zero.
  • the rotor 12 comprises at least one, in this case two annular ribs 32 which extend radially outwards from the casing 34 of the rotor 12.
  • the casing 34 may correspond to that of the drum.
  • These ribs 32 form circular blades with circular points facing the internal ferrule 30, in particular facing radially layers of dedicated abradable material 36. These layers 36 can be housed in the radial thickness of the annular wall 38 of the internal shell 30.
  • the latter has at least one annular tooth 42, for example two or three annular teeth 42. These teeth 42 extend radially from the internal surface 44 of the shell 30 The teeth 42 protrude from this internal surface 44.
  • the teeth 42 can be distributed axially along the length of the ferrule 30, possibly homogeneously. That upstream can be axially, or upstream, from the leading edge 46 of the blade 26. That downstream can be axially, or downstream, from the trailing edge 48 of the blade 26.
  • the teeth 42 and the ribs 32 form an alternation, so that they contain annular chambers between the rotor 12 and the ferrule 30; said chambers see their circular edges close in operation, hence improving the seal, increasing the compression ratio, and optimizing the engine efficiency.
  • the teeth 42 and the ribs 32 extend radially in opposite directions. They can cross radially. They can overlap radially, possibly over the majority of their respective radial heights. Their axial faces, possibly flat or substantially conical, are opposite axially.
  • the teeth 42 and the ribs 32 can be of equal or similar heights, that is to say with a difference of at most: 10%, or 5%.
  • the one or more or each set J1 remaining radially between one of the teeth 42 and the rotor 12, more precisely between one of the teeth 42 and the casing 34, can be equal to at least one, or more, or each set J2 between the ferrule 38 and one of the ribs 32.
  • all the sets J1 are equal; and / or all J2 games are equal.
  • This arrangement favors sealing, and allows the teeth to play a role substantially equivalent to the ribs.
  • the ribs reduce their margins with the ferrule simultaneously. In case of contact, on either side, the mechanical impact is controlled since the teeth can crumble against the rotor without damaging it.
  • the abradable material of the teeth 42 may differ from that of the layers 36 radially opposite the ribs 32. Thus, different properties can be chosen.
  • the first abradable material, used in the teeth 42 can be softer than the second which is present in the layers 36. This preserves the rotor 12.
  • These materials can be elastomers, possibly with concentrations of spheres different hollows, or different fill contents.
  • the teeth can be softer than the ribs.
  • the ribs can be made of titanium, and / or with a Vickers hardness greater than or equal to: 200 MPa, or 900 MPa. The Vickers hardness of the teeth is less than or equal to: 100 MPa, or 10 MPa.
  • the ribs 32 can be axially thinner than the teeth 42. This optimizes the occupation under the shell, optimizes the rotating mass and the mechanical strength.
  • the internal ferrule 30 may comprise at least one circular groove 50, possibly one for each rib 32.
  • Each circular groove 50 is open radially inward, and can receive the circular tip of a rib 32.
  • Each groove 50 s 'extends radially in a different direction from the teeth 42, in particular from the internal surface 44. This allows better closing of the games in operation.
  • Each clearance J2 can be measured against the bottom of the corresponding groove 50.
  • the grooves 50 are formed in the layers 36.
  • the figure 4 shows a sealing system according to a second embodiment of the invention.
  • This figure 4 uses the numbering of the previous figures for identical or similar elements, the number being however incremented by 100. Specific numbers are used for the elements specific to this embodiment.
  • This sealing system is substantially identical to that of the figure 3 , however, it differs in that the annular teeth 142 are formed in a same layer of abradable 136 which also cooperates with the ribs 132. The latter is carried by the wall 138 of the internal ferrule 130, and forms the internal surface 144. The numbers of teeth 142 and rib 132 also change.
  • the ribs 132 and the teeth 142 are placed alternately.
  • the ribs 142 are opposite two teeth 132.
  • the radial heights of teeth are equal to the heights of the ribs.
  • a mixed compressor that is to say one which comprises one or more sealing systems according to the figure 3 , and one or more sealing systems depending on the figure 4 .
  • Circular grooves can be added, in particular in layer 136.
  • the figure 5 sketch a diagram of the manufacturing process of a turbomachine compressor.
  • This process can be an assembly and / or shaping process.
  • the compressor can correspond to that described in relation to the figures 1 and 2 , the compressor sealing systems being for example according to the teachings of figures 3 and / or 4.
  • Step (c) addition 204 can be a step of making or mounting a tooth inside the ferrule.
  • Step (c) addition 204 may include a phase 208 of application of abradable material in the shell.
  • the application phase 208 can be carried out by molding, or gluing, or plasma spraying.
  • step (c) addition 204 comprises a machining phase 210 of the abradable in order to cut the annular tooth there.
  • the machining can be by turning, in particular by placing the ferrule on a mandrel.
  • the phase 208 application tends to implement an annular layer of abradable in excess thickness relative to the teeth. The superfluous material is cut to keep only the material clean for the teeth.
  • the abradable application phase 208 makes it possible to directly form one or each tooth.
  • one tooth has its final shape, another shows a surplus of material which is removed, by cutting and / or machining.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP18173133.2A 2017-06-02 2018-05-18 Système d'étanchéité pour compresseur de turbomachine Active EP3409902B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2017/5396A BE1025283B1 (fr) 2017-06-02 2017-06-02 Systeme d'etancheite pour compresseur de turbomachine

Publications (2)

Publication Number Publication Date
EP3409902A1 EP3409902A1 (fr) 2018-12-05
EP3409902B1 true EP3409902B1 (fr) 2020-02-19

Family

ID=59093325

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18173133.2A Active EP3409902B1 (fr) 2017-06-02 2018-05-18 Système d'étanchéité pour compresseur de turbomachine

Country Status (4)

Country Link
US (1) US10746036B2 (zh)
EP (1) EP3409902B1 (zh)
CN (1) CN108979738B (zh)
BE (1) BE1025283B1 (zh)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2955646A1 (en) * 2016-01-19 2017-07-19 Pratt & Whitney Canada Corp. Gas turbine engine rotor blade casing
FR3088671B1 (fr) * 2018-11-16 2021-01-29 Safran Aircraft Engines Etancheite entre une roue mobile et un distributeur d'une turbomachine
FR3091725B1 (fr) * 2019-01-14 2022-07-15 Safran Aircraft Engines Ensemble pour une turbomachine
FR3145187A1 (fr) * 2023-01-24 2024-07-26 Safran Aircraft Engines Carter de turbomachine

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3070353A (en) * 1958-12-03 1962-12-25 Gen Motors Corp Shroud assembly
JPS5242906U (zh) * 1975-09-22 1977-03-26
AU2002226029A1 (en) * 2000-11-06 2002-05-15 Advanced Components And Materials, Inc. Compliant brush shroud assembly for gas turbine engine compressors
US20060228209A1 (en) * 2005-04-12 2006-10-12 General Electric Company Abradable seal between a turbine rotor and a stationary component
US7686568B2 (en) * 2006-09-22 2010-03-30 General Electric Company Methods and apparatus for fabricating turbine engines
FR2940352B1 (fr) * 2008-12-23 2014-11-28 Snecma Roue mobile de turbomachine a aubes en materiau composite munies de lechettes metalliques.
GB2492546A (en) * 2011-07-04 2013-01-09 Alstom Technology Ltd A labyrinth seal for an axial fluid flow turbomachine
US9163519B2 (en) * 2011-07-28 2015-10-20 General Electric Company Cap for ceramic blade tip shroud
US9151174B2 (en) * 2012-03-09 2015-10-06 General Electric Company Sealing assembly for use in a rotary machine and methods for assembling a rotary machine
US9394800B2 (en) * 2013-01-21 2016-07-19 General Electric Company Turbomachine having swirl-inhibiting seal
EP2801702B1 (fr) * 2013-05-10 2020-05-06 Safran Aero Boosters SA Virole interne de redresseur de turbomachine avec joint abradable
US9243511B2 (en) * 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
CA2966126C (fr) * 2014-10-15 2023-02-28 Safran Aircraft Engines Ensemble rotatif pour turbomachine comprenant une virole de rotor auto-portee
BE1022513B1 (fr) * 2014-11-18 2016-05-19 Techspace Aero S.A. Virole interne de compresseur de turbomachine axiale
WO2016133583A1 (en) * 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Turbine shroud with abradable layer having ridges with holes
US9790809B2 (en) * 2015-03-24 2017-10-17 United Technologies Corporation Damper for stator assembly
FR3039589B1 (fr) * 2015-07-28 2020-01-10 Safran Aircraft Engines Etage de turbomachine, en particulier de turbine basse-pression

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
BE1025283B1 (fr) 2019-01-11
BE1025283A1 (fr) 2019-01-04
CN108979738A (zh) 2018-12-11
US10746036B2 (en) 2020-08-18
US20180347579A1 (en) 2018-12-06
CN108979738B (zh) 2022-05-31
EP3409902A1 (fr) 2018-12-05

Similar Documents

Publication Publication Date Title
EP3064708B1 (fr) Aube composite de compresseur de turbomachine axiale avec une feuille de renfort et turbomachine comprenant une telle aube
EP3409902B1 (fr) Système d'étanchéité pour compresseur de turbomachine
EP2705223B1 (fr) Dispositif d'étanchéité pour distributeur de turbine de turbomachine
BE1024935A1 (fr) Compresseur avec virole interne segmentee pour turbomachine axiale
CA2964299C (fr) Procede d'intervention sur un rotor et clinquant associe
EP3121375B1 (fr) Armature d'aube composite de compresseur de turbomachine axiale
CA2831522C (fr) Flasque d'etancheite pour etage de turbine de turbomachine d'aeronef, comprenant des tenons anti-rotation fendus
BE1024524B1 (fr) Virole interne et aube orientable de compresseur de turbomachine axiale
EP2762681B1 (fr) Tambour de rotor de turbomachine axiale et turbomachine associée
EP3382242B1 (fr) Joint à brosse pour rotor de turbomachine
BE1025299A9 (fr) Compresseur a geometrie variable de turbomachine axiale
EP3382155B1 (fr) Système d'étanchéité pour turbomachine et turbomachine associée
EP3290657B1 (fr) Stator à aubes ajustables pour compresseur de turbomachine axiale
BE1023367B1 (fr) Fixation de virole interne de compresseur de turbomachine axiale
FR2874232A1 (fr) Rotor metallique renforce de fibres.
BE1027190B1 (fr) Rotor hybride avec inserts
EP3715638B1 (fr) Rotor hybride à coquille externe rapportée contre la paroi annulaire composite
BE1026006B1 (fr) Systeme d’aubes a calage variable pour compresseur de turbomachine
FR3146949A1 (fr) ROUE AUBAGEE POUR TURBOMACHINE D’AERONEF, COMPRENANT UN DISPOSITIF D’AMORTISSEMENT DYNAMIQUE AMELIORE, EQUIPEe DE SECTEURS ANGULAIRES DE ROUE A TALONS FIXES ET A TALONS MOBILES
EP3477052A1 (fr) Profil non-axisymétrique de carter pour compresseur de turbomachine

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

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

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: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20190604

RBV Designated contracting states (corrected)

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/02 20060101ALI20190709BHEP

Ipc: F01D 11/12 20060101ALI20190709BHEP

Ipc: F01D 11/00 20060101AFI20190709BHEP

Ipc: F04D 29/16 20060101ALI20190709BHEP

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

INTG Intention to grant announced

Effective date: 20190809

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190906

INTG Intention to grant announced

Effective date: 20190910

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602018002487

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1235193

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200315

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200219

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200519

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200619

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200519

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200712

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1235193

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200219

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602018002487

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20201120

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200518

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200518

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210531

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200219

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240419

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240418

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240418

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: BE

Payment date: 20240418

Year of fee payment: 7