WO2014041290A1 - Distributeur de turbomachine comprenant une tôle de protection thermique avec butée radiale, et tôle de protection thermique associée - Google Patents
Distributeur de turbomachine comprenant une tôle de protection thermique avec butée radiale, et tôle de protection thermique associée Download PDFInfo
- Publication number
- WO2014041290A1 WO2014041290A1 PCT/FR2013/052068 FR2013052068W WO2014041290A1 WO 2014041290 A1 WO2014041290 A1 WO 2014041290A1 FR 2013052068 W FR2013052068 W FR 2013052068W WO 2014041290 A1 WO2014041290 A1 WO 2014041290A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- thermal protection
- distributor
- axial
- radial
- protection plate
- Prior art date
Links
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
-
- 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
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
- F01D25/145—Thermally insulated casings
-
- 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
- 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
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/231—Preventing heat transfer
Definitions
- Turbomachine distributor comprising a thermal protection plate with a radial abutment, and a protective plate
- the invention generally relates to the field of turbomachines, and more particularly the thermal protection elements adapted to be mounted in a distributor, for example an annular turbine nozzle on a turbine casing.
- FIG. 1 An example of a turbomachine has been illustrated in FIG.
- a turbomachine typically comprises a nacelle which forms an opening for the admission of a given flow of air to the engine itself.
- the turbomachine comprises one or more compression sections 4 of the air admitted into the engine (generally a low pressure section and a high pressure section) and a combustion chamber 5, in which the air thus compressed is mixed with fuel before being burned.
- the hot combustion gases resulting from this combustion are expanded in the various turbine stages, generally a high-pressure stage 6 immediately downstream of the chamber 5 and receiving the gases at the highest temperature. After this first expansion, the gases are expanded again by being guided through so-called low pressure turbine stages 7.
- a low-pressure turbine 7 conventionally comprises one or more rows of turbine blades spaced circumferentially around the rotor of the turbine 7. It also comprises a low-pressure distributor 2 for directing the flow of gas from the combustion chamber. To the turbine blades at a suitable angle and velocity to rotate the vanes and rotor of the turbine 7.
- the distributor 2 comprises a plurality of blades arranged radially with respect to an axis of rotation of the turbomachine X connecting a radially inner annular element and an annular element radially. external.
- the assembly forms an annular vein opposite the moving blades of the turbine.
- the low pressure distributor 3 is formed of fixed vanes arranged in a wheel divided into a plurality of segments distributed circumferentially around the axis X of the turbomachine.
- Each segment comprises several adjacent stationary vanes integral with a ring sector element, as well as an upstream retaining means and a downstream retaining means.
- upstream and downstream are defined by the flow direction of the gases in the turbomachine.
- These retaining means are, for example, annular rails formed in the inner wall of the casing on which carry bearing surfaces formed on the ring sectors of the distributor segments.
- the assembly is arranged to allow the relative expansion of the distributor relative to the housing which is a function of the variations in speed of the machine.
- due to the axial symmetry of the distributor wheels and tangential forces resulting from the gas flow therethrough it is necessary to provide means for locking rotating sectors.
- the patent FR 2 743 603 in the name of the Applicant describes a method of mounting such distributor segments within a housing.
- the distributor segments comprise a peripheral outer rib, perpendicular to the axis of the distributor (and therefore of the turbomachine), supported by upstream and downstream faces on corresponding faces of the inner wall of the housing.
- a projection on the upstream face of the rib of each segment comprises a notch in which is housed an anti-rotation pin.
- This pin comprises a head housed in the notch and a rod slid in a radial bore of the housing wall, and thus prevents any rotational movement of the distributor segment about its axis.
- a sheet is generally interposed between the distributor and the inner wall of the housing.
- This thermal protection plate is supported upstream against a radial surface portion formed in the inner wall of the housing.
- the upstream edge the protective sheet is bent radially inwardly to form a pin which also bears on an upstream edge of the distributor and participates in maintaining it against the upstream rail of the housing.
- Downstream the protective plate comprises a notch with a tongue in the bottom of the notch.
- This assembly gives complete satisfaction in terms of maintaining the distributor inside the housing and the thermal protection thereof.
- FR 2 960 591 also in the name of the Applicant, and which is illustrated with reference to Figure 1, proposes in turn to modify the anti-rotation pin 40 so that it serves as a stop in the tongue in a possible radial displacement of the sheet during the operation of the turbomachine. Indeed, by interposing a stop between the portion of the sheet 10 may move in operation, eliminates the risk of contact with the inner wall 30 of the housing. For this, a shoulder 40a is formed on the anti-rotation pin 40, extending radially from the pin 40 between the tongue 12a and the inner wall of the casing 30.
- Document DE 100 48 156 describes a protective thermal sheet for a distributor, whose downstream end is bent adapted to come into contact with a ring segment.
- DE 101 22 464 proposes a distributor comprising a thermal protection plate, provided with abutment elements adapted to abut against the housing and prevent rotation of the distributor.
- the abutment elements may rub against the inner face of the housing and wear prematurely.
- An object of the invention is therefore to propose means for blocking in rotation a segment of a distributor, in particular a low pressure distributor of a turbomachine, with respect to a turbine casing of the turbomachine, which are also capable of to protect the casing from the thermal radiation of the distributor and to avoid the risk of premature wear of the casing due to friction, and which is also of moderate cost and easy to achieve.
- the invention proposes for this purpose a distributor for a turbomachine, in particular a low pressure distributor, adapted to be mounted in a housing, comprising:
- thermal protection plate disposed between the housing and the distributor segments, comprising a plurality of tongues, each being adapted to bear against an anti-rotation pin.
- the thermal protection plate comprises at least one axial tongue adapted to come into radial abutment against a lower face of a first anti-rotation pin, and at least one radial tongue adapted to come into axial abutment against an upstream face of a second anti-rotation pin.
- the thermal protection plate comprises a plurality of axial tongues and radial tongues
- the thermal protection plate comprises substantially as many radial tongues as axial tongues
- the radial tongues and the axial tongues alternate along the thermal protection plate, around the axis of rotation of the turbomachine, and are separated by a notch, preferably with removal of material,
- a circumferential width of the at least one axial tongue corresponds to the distance separating three adjacent anti-rotation pins
- the at least one axial tongue is at a distance from the anti-rotation pin when the turbomachine is at rest.
- the invention also proposes a protective thermal protection sheet that can be used in a distributor as described above, comprising at least one so-called radial tab adapted to come into axial abutment against an upstream face of a first anti-block. -rotation, and at least one tongue, called axial, adapted to come into radial abutment against a lower face of a second anti-rotation pin.
- the tongues are integral with said thermal protection plate.
- FIG. 1 is a partial view in axial section of a turbine distributor mounted in a casing of a turbomachine according to the prior art
- FIG. 2 is a partial view in axial section of an exemplary turbine distributor mounted in a casing of a turbomachine according to the invention
- FIG. 3a is a perspective view of an exemplary thermal protection plate according to the invention.
- FIG. 3b is a detailed view of a part of the thermal protection plate of FIG. 3a
- FIG. 4a is a first perspective view of the example of FIG.
- FIG. 4b is a second perspective view of the example of FIG. 2, and
- FIG. 5 represents an example of a turbomachine to which the invention applies.
- the invention will be described very particularly with reference to a low pressure distributor 2 of a turbomachine 1, mounted in a casing 3 of low pressure turbine 7.
- a low pressure distributor 2 is formed of fixed vanes arranged in a wheel divided into a plurality of segments 20 distributed circumferentially around an axis of rotation X of the turbomachine 1.
- Each segment 20 comprises several adjacent stationary vanes integral with a ring sector element, as well as an upstream retaining means and a downstream retaining means.
- These retaining means are, for example, the annular rails 32, 24 formed in an inner wall 30 of the casing 3 on which bear bearing surfaces 22, 24 provided on the ring sectors of the distributor segments 2 described above.
- the distributor 2 comprises a plurality of segment locking devices, each comprising an anti-rotation pin 40, mounted on both a segment 20 of the distributor 2 and on the turbine housing 3.
- a projection on the upstream face of each segment 20 comprises a notch in which is housed the anti-rotation pin 40.
- This pin 40 comprises a head 41 housed in the notch and a rod 42 slid into a radial bore of the wall 30 of the casing 3, and thus prevents any rotational movement of the distributor segment 20 around the axis of the latter (corresponding to the axis of rotation X of the turbomachine ).
- a thermal protection plate 10 is interposed between the segments 20 of the low-pressure distributor 2 and the inner wall 30 of the turbine casing 3, and adapted to limit the thermal radiation of the distributor 2 on the turbine casing 3.
- This thermal protection plate 10 is supported upstream against a radial surface portion 33 formed in the inner wall of the housing.
- the upstream edge 12 of the protective plate 10 is bent radially inwards to form a pin.
- the upstream edge may additionally bear on an upstream edge of the segment 20 of the distributor 2 and participate in maintaining it against the upstream rail 32 of the casing 3.
- the thermal protection plate 10 Downstream, the thermal protection plate 10 comprises a plurality of tongues 14, 16, each being adapted to bear against an anti-rotation pin 40 of the locking devices.
- the sheet 10 is modified at its downstream portion.
- the thermal protection plate 10 comprises tabs 14, 16 adapted so that the sheet is in radial abutment and in axial abutment against the anti-rotation pins 40.
- the thermal protection plate is thus held in position against the pins anti- rotation 40, while its displacement is limited in the direction of the inner wall 30 of the casing 3.
- radial a direction extending substantially transversely relative to the axis X of the turbomachine
- axial direction a s extending substantially parallel to the axis X of the turbomachine.
- the tongues 14, 16 of the thermal protection 10 may comprise axial tongues 14, adapted to come into radial abutment against the anti-rotation pin 40 corresponding, and radial tongues 16, adapted to come into axial abutment against the anti-rotation pin 40 corresponding.
- the radial tongues 16 extend transversely with respect to the axis X of the turbomachine 1, and allow the axial thermal protection plate 10 to be held in axial position relative to the distributor 2. These radial tongues 16 form by therefore axial stops.
- the radial tongues 16 are for example arranged so as to extend facing an upstream face 46 of the anti-rotation pins 40, this upstream face 46 corresponding to the face of the anti-rotation pins directed upstream. the turbomachine 1, facing the flow of gas.
- the axial tongues 14 as for them extend substantially parallel to the axis X of the turbomachine 1, and make it possible to prevent the thermal protection plate 10 from moving towards the turbine casing 3, that is to say in a radial direction. This is why these axial tabs form radial stops.
- the axial tongues 14 are for example arranged so as to extend opposite a lower face 44 of the anti-rotation pins 40, this lower face 44 corresponding to the face of the anti-rotation pins 40 directed towards the axis of rotation X of the turbomachine 1, opposite the distributor 2.
- the thermal protection plate 10 comprises substantially as many axial tongues 14 as radial tongues 16.
- the thermal protection plate 10 may for example comprise thirteen axial tongues 14 and thirteen radial tongues 16.
- the radial tongues 16 and the axial tongues 14 can moreover be distributed alternately along the periphery of the thermal protection plate 10, in order to respect the symmetry of the turbomachine 1 and to balance the distributor 2.
- the thermal protection plate 10 is preferably annular in shape, and may be one-piece, that is to say in one piece, or obtained by combining several annular segments connected to one another.
- the tongues 14, 16 may be formed integrally with the remainder of the thermal protection plate 10. For example, they may be obtained by cutting the downstream edge of the thermal protection plate 10 so as to form notches 18, with or without removal of material. In the embodiment illustrated in FIGS. 7 to 4b, the notches 18 are made with removal of material, in order to avoid any friction of the axial tongues 14 against the anti-rotation pin 40 during the expansion of the distributor 2.
- the thermal protection plate 10 may comprise a tongue 14, 16 by anti-rotation pin 40, so that for a given anti-rotation pin 40, the thermal protection plate 10 has either a radial tongue 16 or a 14.
- the thermal protection plate 10 may comprise a radial tongue 16 and an axial tongue 14 by anti-rotation pin 40. A same anti-rotation pin 40 can then be in radial abutment against an axial tongue 14 and in axial abutment against a radial tongue 16.
- the axial tongues 14 may be wider (along the circumference of the thermal protection plate 10) than the radial tongues 16.
- a circumferential width of an axial tongue 14 may correspond to the distance separating three anti-friction pins. rotation 40 adjacent.
- a given axial tongue 14 can therefore extend not only opposite the corresponding anti-rotation pin 40, but also on either side of this pin 40 to the adjacent anti-rotation pins 40, the adjacent anti-rotation pins 40 being each facing another tongue, preferably radial 16.
- This embodiment makes it possible to simplify the production of the thermal protection plate 10, to reinforce the resistance to the radial forces of the axial tongue 14 applied by the anti-rotation pin 40, and to prevent the sheet 10 from coming into contact with the turbine casing 3 despite the vibrations suffered by it, and also provides better protection against thermal radiation.
- the radial tongues 16 in turn have a width (along the circumference of the thermal protection plate 10) substantially corresponding to the width of the upstream face 46 facing the anti-rotation pin 40.
- the radial tongues 16 which are wider than the axial tongues 14, and extend between three adjacent anti-rotation pins 40, the axial tongues 14 then having a width substantially equal to the width of the lower face 44 opposite the anti-rotation pin 40.
- the axial tongues 14 and the radial tongues 16 are of equal width and extend on either side of each anti-rotation pin 40, over a width generally equal to the distance between two anti-rotation pins. rotation 40 adjacent.
- the radial tabs 16 may be introduced into a groove formed in the face facing the corresponding anti-rotation pin 40.
- the axial tongues 14 can extend opposite and away from the lower face 44 of the anti-rotation pins 40 corresponding, in order to allow a specific radial displacement of the thermal protection plate 10 in case of expansion thereof.
- This radial displacement is however limited, the axial tongue 14 forming a radial stop when it comes into contact with the lower face 44 of the anti-rotation pin.
- the radial tongues 16, on the other hand, are in contact with the upstream face 46 of the anti-rotation pins 40, that the turbomachine 1 is at rest or in operation, to maintain the thermal protection plate 10 in position relative to the distributor 2 and to the casing 3 turbine.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/427,723 US9835049B2 (en) | 2012-09-12 | 2013-09-09 | Turbomachine distributor comprising a thermal protection sheet with a radial stop, and associated thermal protection sheet |
GB1504391.2A GB2519925B (en) | 2012-09-12 | 2013-09-09 | Turbomachine distributor comprising a thermal protection sheet with a radial stop, and associated thermal protection sheet |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1258574 | 2012-09-12 | ||
FR1258574A FR2995340A1 (fr) | 2012-09-12 | 2012-09-12 | Tole de protection thermique avec butee radiale, notamment pour distributeur de turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014041290A1 true WO2014041290A1 (fr) | 2014-03-20 |
Family
ID=47425024
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2013/052068 WO2014041290A1 (fr) | 2012-09-12 | 2013-09-09 | Distributeur de turbomachine comprenant une tôle de protection thermique avec butée radiale, et tôle de protection thermique associée |
Country Status (4)
Country | Link |
---|---|
US (1) | US9835049B2 (fr) |
FR (1) | FR2995340A1 (fr) |
GB (1) | GB2519925B (fr) |
WO (1) | WO2014041290A1 (fr) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10184354B2 (en) * | 2013-06-19 | 2019-01-22 | United Technologies Corporation | Windback heat shield |
FR3011272B1 (fr) * | 2013-10-01 | 2018-01-19 | Safran Aircraft Engines | Dispositif de connexion d'une partie fixe de turbomachine et d'un pied de distributeur d'une turbine de turbomachine |
US9677427B2 (en) * | 2014-07-04 | 2017-06-13 | Pratt & Whitney Canada Corp. | Axial retaining ring for turbine vanes |
FR3039201B1 (fr) * | 2015-07-22 | 2017-07-21 | Snecma | Partie de turbomachine a tole de protection thermique pourvue d'epingles |
US10519811B2 (en) | 2016-10-04 | 2019-12-31 | United Technologies Corporation | Flange heat shield |
FR3061511B1 (fr) * | 2017-01-05 | 2020-12-25 | Safran Aircraft Engines | Turbine pour turbomachine |
US10865650B2 (en) * | 2017-09-12 | 2020-12-15 | Raytheon Technologies Corporation | Stator vane support with anti-rotation features |
US20210033283A1 (en) * | 2019-07-30 | 2021-02-04 | United Technologies Corporation | Diffuser case heatshields for gas turbine engines |
US11933226B2 (en) * | 2022-05-13 | 2024-03-19 | Rtx Corporation | Heat shield and method of installing the same |
US11939888B2 (en) * | 2022-06-17 | 2024-03-26 | Rtx Corporation | Airfoil anti-rotation ring and assembly |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10122464C1 (de) * | 2001-05-09 | 2002-03-07 | Mtu Aero Engines Gmbh | Mantelring |
DE10048156A1 (de) * | 2000-09-28 | 2002-04-11 | Rolls Royce Deutschland | Turbinendeckbandsegmentbefestigung |
FR2960591A1 (fr) * | 2010-06-01 | 2011-12-02 | Snecma | Dispositif pour caler en rotation un segment de distributeur dans un carter de turbomachine ; pion antirotation |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5188507A (en) * | 1991-11-27 | 1993-02-23 | General Electric Company | Low-pressure turbine shroud |
US5201846A (en) * | 1991-11-29 | 1993-04-13 | General Electric Company | Low-pressure turbine heat shield |
US5411369A (en) * | 1994-02-22 | 1995-05-02 | Pratt & Whitney Canada, Inc. | Gas turbine engine component retention |
FR2743603B1 (fr) * | 1996-01-11 | 1998-02-13 | Snecma | Dispositif de jonction de segments d'un distributeur circulaire a un carter de turbomachine |
US7334980B2 (en) * | 2005-03-28 | 2008-02-26 | United Technologies Corporation | Split ring retainer for turbine outer air seal |
FR2938872B1 (fr) * | 2008-11-26 | 2015-11-27 | Snecma | Dispositif anti-usure pour aubes d'un distributeur de turbine d'une turbomachine aeronautique |
US8870544B2 (en) * | 2010-07-29 | 2014-10-28 | United Technologies Corporation | Rotor cover plate retention method |
US9896971B2 (en) * | 2012-09-28 | 2018-02-20 | United Technologies Corporation | Lug for preventing rotation of a stator vane arrangement relative to a turbine engine case |
-
2012
- 2012-09-12 FR FR1258574A patent/FR2995340A1/fr active Pending
-
2013
- 2013-09-09 WO PCT/FR2013/052068 patent/WO2014041290A1/fr active Application Filing
- 2013-09-09 US US14/427,723 patent/US9835049B2/en active Active
- 2013-09-09 GB GB1504391.2A patent/GB2519925B/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10048156A1 (de) * | 2000-09-28 | 2002-04-11 | Rolls Royce Deutschland | Turbinendeckbandsegmentbefestigung |
DE10122464C1 (de) * | 2001-05-09 | 2002-03-07 | Mtu Aero Engines Gmbh | Mantelring |
FR2960591A1 (fr) * | 2010-06-01 | 2011-12-02 | Snecma | Dispositif pour caler en rotation un segment de distributeur dans un carter de turbomachine ; pion antirotation |
Also Published As
Publication number | Publication date |
---|---|
GB2519925A (en) | 2015-05-06 |
US20150252687A1 (en) | 2015-09-10 |
FR2995340A1 (fr) | 2014-03-14 |
GB2519925B (en) | 2017-03-29 |
GB201504391D0 (en) | 2015-04-29 |
US9835049B2 (en) | 2017-12-05 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2014041290A1 (fr) | Distributeur de turbomachine comprenant une tôle de protection thermique avec butée radiale, et tôle de protection thermique associée | |
EP2576991B1 (fr) | Turbomachine avec un dispositif pour caler en rotation un segment de distributeur dans un carter | |
EP1840339B1 (fr) | Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine dans une turbomachine | |
EP2839117B1 (fr) | Étage de turbine pour une turbomachine | |
FR2980235A1 (fr) | Anneau pour une turbine de turbomachine | |
FR2926604A1 (fr) | Centrage d'une piece a l'interieur d'un arbre de rotor dans une turbomachine | |
WO2013072605A1 (fr) | Roue a aubes pour une turbomachine | |
CA2831522C (fr) | Flasque d'etancheite pour etage de turbine de turbomachine d'aeronef, comprenant des tenons anti-rotation fendus | |
WO2016066932A1 (fr) | Aube de rotor a pilotage de jeu actif, ensemble tournant et son procede de fonctionnement | |
CA2920983C (fr) | Amelioration pour le verrouillage de pieces de support d'aubage | |
FR3020408A1 (fr) | Ensemble rotatif pour turbomachine | |
EP2601009B1 (fr) | Procédé de fabrication d'un tambour de turbomachine et tambour de turbomachine | |
FR3031136B1 (fr) | Rotor de turbomachine a surfaces d'appui optimisees | |
FR2993599A1 (fr) | Disque labyrinthe de turbomachine | |
FR2960589A1 (fr) | Roue a aubes pour une turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion | |
FR3085712A1 (fr) | Aube de roue mobile pour turbomachine d'aeronef, presentant un talon decouple de la pale de l'aube | |
FR2944554A1 (fr) | Turbine haute-pression de turbomachine | |
FR3085994A1 (fr) | Anneau de retention axiale d'aubes pour roue mobile de turbomachine, de preference pour aeronef | |
FR3001761A1 (fr) | Aubage fixe de distribution de flux muni d'une platine d'etancheite amelioree | |
FR3113923A1 (fr) | Turbine pour turbomachine comprenant des clinquants de protection thermique | |
FR3002586A1 (fr) | Reduction des echanges convectifs entre l'air et le rotor dans une turbine | |
FR3039201A1 (fr) | Partie de turbomachine a tole de protection thermique pourvue d'epingles | |
FR3069014A1 (fr) | Partie de turbomachine a tole ressort | |
WO2016034804A1 (fr) | Ensemble rotatif muni d'un dispositif de calage | |
FR3027353A1 (fr) | Roue de turbomachine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 13767039 Country of ref document: EP Kind code of ref document: A1 |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 14427723 Country of ref document: US |
|
ENP | Entry into the national phase |
Ref document number: 1504391 Country of ref document: GB Kind code of ref document: A Free format text: PCT FILING DATE = 20130909 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 1504391.2 Country of ref document: GB |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 13767039 Country of ref document: EP Kind code of ref document: A1 |