EP3409902A1 - Abdichtungssystem für kompressor einer strömungsmaschine - Google Patents

Abdichtungssystem für kompressor einer strömungsmaschine Download PDF

Info

Publication number
EP3409902A1
EP3409902A1 EP18173133.2A EP18173133A EP3409902A1 EP 3409902 A1 EP3409902 A1 EP 3409902A1 EP 18173133 A EP18173133 A EP 18173133A EP 3409902 A1 EP3409902 A1 EP 3409902A1
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.)
Granted
Application number
EP18173133.2A
Other languages
English (en)
French (fr)
Other versions
EP3409902B1 (de
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/de
Application granted granted Critical
Publication of EP3409902B1 publication Critical patent/EP3409902B1/de
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
    • 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
    • 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
    • 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 an inner ferrule.
  • the invention also relates to an axial turbomachine, such as an aircraft turbojet engine or an aircraft turboprop engine.
  • the invention also proposes a method of manufacturing a compressor.
  • the compression ratio at the outlet of a turbojet compressor depends on the seal between the ferrules and the rotor. This seal must adapt to vibrations as well as ingestions when it comes to a low pressure compressor. The centrifugal force and the expansion remain constraints that add to the previous ones.
  • Each inner ferrule or each inner 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 blade positioned in said opening for attachment.
  • the wall comprises a radial flange which passes through the openings in the circumferential direction of the ferrule or ferrule segment, so as to form a mechanical link within each opening to bond opposite edges.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to reduce leakage in a compressor. The invention also aims to offer a simple, durable, lightweight, economical, reliable, easy to produce, convenient maintenance, easy inspection, and improved performance.
  • the invention relates to a turbomachine compressor, in particular a low-pressure turbine engine compressor, the compressor comprising: a rotor with at least one annular rib; an annular row of stator vanes; an inner ferrule connected to the stator vanes and comprising at least one layer of abradable material adapted to cooperate with the at least one annular rib of the rotor to ensure a seal; remarkable in that the inner 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 inner 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 measured radial clearances axially 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, which is 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 for manufacturing a turbomachine compressor, the method comprising the following steps: (a) supplying or producing an annular row of stator vanes; (b) attaching an inner ferrule to the annular row of stator vanes, said inner ferrule comprising abradable material; (d) positioning the abradable material of the inner ferrule around an annular rib of a rotor of the compressor; remarkable in that prior to step (d) positioning it comprises a step (c) addition of at least one annular tooth 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 comprises a phase of molding, or gluing, 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 comprises a machining phase of the abradable in order to cut the annular tooth.
  • the abradable form 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 is combinable with the other objects, and the objects of the invention are also combinable with the embodiments of the description, which in addition are combinable with each other, according to all possible technical combinations, unless otherwise be explicitly specified.
  • the invention allows to create other wipers embedded by the inner ferrule. Their presence brings an effect that is added to that of the rotor, by amplifying the vortices under the ferrule to slow down the secondary flows.
  • the seal is improved without penalizing the inertia of the rotor.
  • teeth of abradable material respects the integrity of the rotor.
  • Radially two levels of tightness are created and act in series, while allowing implantation that respects the axial and radial compactness.
  • 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 to limit the wear of the latter.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power 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 vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8.
  • a commonly designated fan or fan input fan 16 is coupled to the rotor 12 and generates a flow of air which splits 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-ducted 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 streams are coaxial annular flows and fitted into one another. They are channeled by the casing of the turbomachine and / or ferrules.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 4. It can observe 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 monobloc drum. It forms a solid connecting all its rows of blades.
  • one or more or each row of rotor blades 24 is rigidly connected to the rotor, and thus to the drum if necessary.
  • the rotor blades are dovetail attachment.
  • 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 substantially radially from an outer casing 28, and can be fixed and immobilized by means of axes.
  • the housing 28 may be formed of two half-shells.
  • the rows of stator vanes 26 support inner shells 30 whose outer surfaces guide the primary flow 18.
  • the inner shells 30 may have a profile of revolution about the axis of rotation 14. They provide dynamic sealing with the rotor 12 , especially in combination with its annular ribs, commonly known as wipers. They minimize leakage in that they allow a rimpedement with the rotor, said approximation closing the mechanical clearances in operation.
  • a ferrule and a rotor portion 12 may form a sealing system.
  • the figure 3 sketch a sealing system such as those of the figure 2 .
  • a stator blade 26 representative of its row
  • an axial rotor portion 12 and an inner ring 30.
  • the shell 30 may be segmented. It can be made of organic matrix composite material reinforced with fibers.
  • the system is here represented 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 outwardly 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 inner ferrule 30, in particular radially opposite layers of abradable material 36 dedicated. These layers 36 may be housed in the radial thickness of the annular wall 38 of the inner 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 inner surface 44 of the ferrule 30. The teeth 42 project from this inner surface 44.
  • the teeth 42 may be distributed axially along the length of the shell 30, possibly homogeneously. That upstream may be axially, or upstream, the leading edge 46 of the blade 26. The downstream may be at the axial level, or downstream, the trailing edge 48 of the blade 26.
  • the teeth 42 and the ribs 32 form an alternation, so that they enclose annular chambers between the rotor 12 and the ferrule 30; said chambers see their circular edges close in operation, hence improving the sealing, 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 may overlap radially, possibly on the majority of their respective radial heights. Their axial faces, possibly flat or substantially conical, are facing axially.
  • the teeth 42 and the ribs 32 may be of equal heights or the like, ie with a difference of at most: 10%, or 5%.
  • the one or more or each set J1 radially remaining between one of the teeth 42 and the rotor 12, more precisely between one of the teeth 42 and the envelope 34, may be equal to at least one, or several, or each set J2 between the ferrule 38 and one of the ribs 32.
  • all the games 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 both sides, 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 in front of the ribs 32. Thus, different properties may be chosen.
  • the first abradable material used in the teeth 42 may be softer than the second which is present in the layers 36. This preserves the rotor 12.
  • These materials may be elastomers, possibly with concentrations of spheres different digs, or different charge contents.
  • the teeth can be softer than the ribs.
  • the ribs may 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 may be thinner axially than the teeth 42. This optimizes the occupancy under the shell, optimizes the rotating mass and the mechanical strength.
  • the inner 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 of the teeth 42, especially from the inner surface 44. This allows a better closure of the games in operation.
  • Each set J2 can be measured against the bottom of the corresponding groove 50.
  • the grooves 50 are formed in the layers 36.
  • the figure 4 represents a sealing system according to a second embodiment of the invention. This figure 4 resumes the numbering of the preceding figures for identical or similar elements, however, the numbering is incremented by 100. Specific numbers are used for the specific elements of 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 abradable layer 136 which cooperates further with the ribs 132.
  • the latter is carried by the wall 138 of the inner shell 130, and forms the inner 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 according to the figure 4 .
  • Circular grooves may be added, especially in layer 136.
  • the figure 5 sketch a diagram of the manufacturing process of a turbomachine compressor. This process can be a method of assembly and / or shaping.
  • the compressor may correspond to that described in relation to the figures 1 and 2 , the compressor sealing systems being for example according to the teachings of the figures 3 and / or 4.
  • Step (c) addition 204 may be a step of making or mounting a tooth inside the ferrule.
  • Step (c) addition 204 may comprise an application phase 208 of abradable material in the ferrule.
  • the application phase 208 can be performed by molding, or gluing, or plasma projection.
  • step (c) addition 204 comprises a machining step 210 of the abradable to cut the annular tooth.
  • the machining can be by turning, in particular by placing the ferrule on a mandrel.
  • the phase application 208 tends to implement an annular layer of abradable extra thickness relative to the teeth.
  • the superfluous material is cut to keep only the material proper to the teeth.
  • the application phase 208 of abradable can directly form one or each tooth.
  • a tooth has its final shape, another shows a surplus of material that 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 Abdichtungssystem für kompressor einer strömungsmaschine Active EP3409902B1 (de)

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 true EP3409902A1 (de) 2018-12-05
EP3409902B1 EP3409902B1 (de) 2020-02-19

Family

ID=59093325

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18173133.2A Active EP3409902B1 (de) 2017-06-02 2018-05-18 Abdichtungssystem für kompressor einer strömungsmaschine

Country Status (4)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3088671A1 (fr) * 2018-11-16 2020-05-22 Safran Aircraft Engines Etancheite entre une roue mobile et un distributeur d'une turbomachine
FR3091720A1 (fr) * 2019-01-14 2020-07-17 Safran Aircraft Engines Ensemble pour une turbomachine

Families Citing this family (1)

* 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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1712743A2 (de) * 2005-04-12 2006-10-18 The General Electric Company Turbine mit einer abreibbaren Dichtung zwischen einem Rotor und einem stationären Bauteil
US20140205444A1 (en) * 2013-01-21 2014-07-24 General Electric Company Turbomachine having swirl-inhibiting seal
WO2016059348A1 (fr) * 2014-10-15 2016-04-21 Snecma Ensemble rotatif pour turbomachine comprenant une virole de rotor auto-portee
EP3023595A1 (de) 2014-11-18 2016-05-25 Techspace Aero S.A. Stator-innenring eines kompressors eines axialen turbotriebwerks
EP3073055A2 (de) * 2015-03-24 2016-09-28 United Technologies Corporation Dämpfer für statoranordnung und statoranordnung

Family Cites Families (12)

* 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 (de) * 1975-09-22 1977-03-26
DE10196832T1 (de) * 2000-11-06 2003-11-13 Advanced Components & Material Federnde Bürstenmantelanordnung für Kompressoren von Gasturbinenmaschinen
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
EP2801702B1 (de) * 2013-05-10 2020-05-06 Safran Aero Boosters SA Stator-innenring eines turbotriebwerks mit abriebmaterial
US9243511B2 (en) * 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
WO2016133583A1 (en) * 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Turbine shroud with abradable layer having ridges with holes
FR3039589B1 (fr) * 2015-07-28 2020-01-10 Safran Aircraft Engines Etage de turbomachine, en particulier de turbine basse-pression

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1712743A2 (de) * 2005-04-12 2006-10-18 The General Electric Company Turbine mit einer abreibbaren Dichtung zwischen einem Rotor und einem stationären Bauteil
US20140205444A1 (en) * 2013-01-21 2014-07-24 General Electric Company Turbomachine having swirl-inhibiting seal
WO2016059348A1 (fr) * 2014-10-15 2016-04-21 Snecma Ensemble rotatif pour turbomachine comprenant une virole de rotor auto-portee
EP3023595A1 (de) 2014-11-18 2016-05-25 Techspace Aero S.A. Stator-innenring eines kompressors eines axialen turbotriebwerks
EP3073055A2 (de) * 2015-03-24 2016-09-28 United Technologies Corporation Dämpfer für statoranordnung und statoranordnung

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3088671A1 (fr) * 2018-11-16 2020-05-22 Safran Aircraft Engines Etancheite entre une roue mobile et un distributeur d'une turbomachine
FR3091720A1 (fr) * 2019-01-14 2020-07-17 Safran Aircraft Engines Ensemble pour une turbomachine
FR3091725A1 (fr) * 2019-01-14 2020-07-17 Safran Aircraft Engines Ensemble pour une turbomachine
WO2020148489A1 (fr) * 2019-01-14 2020-07-23 Safran Aircraft Engines Ensemble pour une turbomachine
US11585230B2 (en) 2019-01-14 2023-02-21 Safran Aircraft Engines Assembly for a turbomachine

Also Published As

Publication number Publication date
CN108979738A (zh) 2018-12-11
US10746036B2 (en) 2020-08-18
BE1025283B1 (fr) 2019-01-11
BE1025283A1 (fr) 2019-01-04
CN108979738B (zh) 2022-05-31
US20180347579A1 (en) 2018-12-06
EP3409902B1 (de) 2020-02-19

Similar Documents

Publication Publication Date Title
EP3064708B1 (de) Verbundwerkstoffschaufel eines kompressors eines axialen turbotriebwerks mit einem verstäkungsblech und zugehörige turbomachine mit solch eine schaufel.
EP2801702B1 (de) Stator-innenring eines turbotriebwerks mit abriebmaterial
EP3361055B1 (de) Anordnung einer axialen turbomaschine und verfahren zur regelung von umfangsspalten
EP3409902B1 (de) Abdichtungssystem für kompressor einer strömungsmaschine
EP3095963B1 (de) Laufradschaufel und deckband eines kompressors eines axialen turbotriebwerks
EP3121375B1 (de) Verbundwerkstoffschaufelarmatur eines kompressors eines axialen turbotriebwerks
EP2762681B1 (de) Rotortrommel einer axialen Turbomaschine und zugehörige Turbomaschine
EP3382242B1 (de) Bürstendichtung für rotor einer turbomaschine
BE1025299B9 (fr) Compresseur a geometrie variable de turbomachine axiale
EP3382155B1 (de) Dichtungssystem für eine strömungsmaschine, und zugehörige strömungsmaschine
BE1024523B1 (fr) Stator a 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 (de) Hybridrotor mit einem aussenmantel, der an der ringgförmigen verbundwand anliegt
BE1026058B1 (fr) Joint d’étanchéité pour compresseur de turbomachine axiale
BE1026006B1 (fr) Systeme d’aubes a calage variable pour compresseur de turbomachine
BE1024699B1 (fr) Compresseur basse pression a memoire de forme pour turbomachine axiale
BE1024125B1 (fr) Aube de compresseur de turbomachine axiale a treillis
EP3477052A1 (de) Nicht-axialsymmetrisches profil eines gehäuses für einen kompressor eines gasturbinenmotors

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: FR

Payment date: 20230420

Year of fee payment: 6

Ref country code: DE

Payment date: 20230419

Year of fee payment: 6

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

Ref country code: BE

Payment date: 20230419

Year of fee payment: 6

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

Ref country code: GB

Payment date: 20230420

Year of fee payment: 6