FR3059362B1 - Carter de turbomachine comportant une structure acoustique et un element abradable - Google Patents
Carter de turbomachine comportant une structure acoustique et un element abradable Download PDFInfo
- Publication number
- FR3059362B1 FR3059362B1 FR1661682A FR1661682A FR3059362B1 FR 3059362 B1 FR3059362 B1 FR 3059362B1 FR 1661682 A FR1661682 A FR 1661682A FR 1661682 A FR1661682 A FR 1661682A FR 3059362 B1 FR3059362 B1 FR 3059362B1
- Authority
- FR
- France
- Prior art keywords
- turbomachine
- abradable
- internal
- acoustic structure
- abradable element
- 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
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
- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
-
- 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
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
L'invention concerne un carter (24) de turbomachine (10) comprenant une paroi interne de révolution (26) coaxiale à un axe principal longitudinal de la turbomachine, une structure d'isolation acoustique (20) montée à l'intérieur de la paroi interne de révolution (26), qui est de forme principale annulaire centrée sur ledit axe longitudinal, et un élément annulaire abradable (22), caractérisé en ce que l'élément abradable (22) est fixé sur une face annulaire interne (30a) de la structure d'isolation acoustique (20).
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1661682A FR3059362B1 (fr) | 2016-11-30 | 2016-11-30 | Carter de turbomachine comportant une structure acoustique et un element abradable |
US15/825,855 US10584606B2 (en) | 2016-11-30 | 2017-11-29 | Turbomachine case comprising an acoustic structure and an abradable element |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1661682 | 2016-11-30 | ||
FR1661682A FR3059362B1 (fr) | 2016-11-30 | 2016-11-30 | Carter de turbomachine comportant une structure acoustique et un element abradable |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3059362A1 FR3059362A1 (fr) | 2018-06-01 |
FR3059362B1 true FR3059362B1 (fr) | 2021-01-01 |
Family
ID=57963346
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1661682A Active FR3059362B1 (fr) | 2016-11-30 | 2016-11-30 | Carter de turbomachine comportant une structure acoustique et un element abradable |
Country Status (2)
Country | Link |
---|---|
US (1) | US10584606B2 (fr) |
FR (1) | FR3059362B1 (fr) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3100561B1 (fr) | 2019-09-10 | 2023-01-20 | Safran Aircraft Engines | Fixation d’une virole acoustique a une enveloppe de carter pour une turbomachine d’aeronef |
FR3115315A1 (fr) * | 2020-10-15 | 2022-04-22 | Safran Aircraft Engines | Fixation d’un abradable sur une virole externe de turbomachine |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2767560B1 (fr) * | 1997-08-19 | 1999-11-12 | Aerospatiale | Ensemble reducteur de bruit pour turboreacteur d'aeronef |
US6382905B1 (en) * | 2000-04-28 | 2002-05-07 | General Electric Company | Fan casing liner support |
FR2979385A1 (fr) * | 2011-08-22 | 2013-03-01 | Snecma | Panneau d'isolation acoustique pour turbomachine et turbomachine comportant un tel panneau |
FR2997726B1 (fr) * | 2012-11-05 | 2018-03-02 | Safran Aircraft Engines | Carter de turbomachine |
FR3003303B1 (fr) * | 2013-03-15 | 2017-06-30 | Snecma | Turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion |
FR3005100B1 (fr) * | 2013-04-26 | 2015-05-01 | Snecma | Carter de turbomachine |
US9915168B2 (en) * | 2014-06-03 | 2018-03-13 | United Technologies Corporation | Flowpath cartridge liner and gas turbine engine including same |
-
2016
- 2016-11-30 FR FR1661682A patent/FR3059362B1/fr active Active
-
2017
- 2017-11-29 US US15/825,855 patent/US10584606B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US20180149033A1 (en) | 2018-05-31 |
US10584606B2 (en) | 2020-03-10 |
FR3059362A1 (fr) | 2018-06-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2014193515A3 (fr) | Bloc réacteur inverse à inverseur de poussée | |
CL2019002091A1 (es) | Acoplamiento mecanico para tuberia mecanica y estructural. | |
EP2495400A3 (fr) | Ensemble de carter de turbomachine | |
FR3045715B1 (fr) | Ensemble d'anneau de turbine avec maintien a froid et a chaud | |
WO2013160655A9 (fr) | Module de sortie pour un module de purification d'émissions | |
FR3002590B1 (fr) | Dispositif de refroidissement pour carter de turboreacteur d'aeronef comportant un dispositif de maintien | |
FR3059362B1 (fr) | Carter de turbomachine comportant une structure acoustique et un element abradable | |
BR112015020829A2 (pt) | sistemas de escape de difusor radial para uso com um motor de turbina a gás | |
FR2928181B1 (fr) | Ensemble moteur pour aeronef comprenant un turboreacteur avec des structures de renfort reliant le carter de soufflante au carter central. | |
PL406855A1 (pl) | Zespół unieruchamiający łożysko i sposób jego montażu | |
FR3084694B1 (fr) | Fixation d'un distributeur a un carter d'une turbomachine | |
WO2015116277A3 (fr) | Soulagement de bride pour carter divisé | |
FR3000522B1 (fr) | Dispositif de liaison a double tube | |
FR3081494B1 (fr) | Module de combustion de turbomachine a gaz avec butee de fond de chambre | |
EA202190924A1 (ru) | Система и способ вихревого газогенератора | |
FR3092148B1 (fr) | Carter de soufflante pour une turbomachine d’aeronef | |
FR2932227B1 (fr) | Turboreacteur double flux | |
FR3045233B1 (fr) | Rotor d'un moteur electromagnetique a flux axial a au moins un aimant de forme ondulee | |
EA201890464A1 (ru) | Двусоставной держатель отражателей для ультразвукового датчика расхода | |
FR3026137B1 (fr) | Element pour une turbomachine, telle par exemple qu'un turboreacteur ou un turbopropulseur d'avion | |
FR3068732B1 (fr) | Dispositif de refroidissement | |
FR3030633B1 (fr) | Tuyere d'echappement d'un turbomoteur dont la sortie est perpendiculaire a l'axe de rotation du turbomoteur | |
FR3086392B1 (fr) | Ensemble de test | |
FR3056556B1 (fr) | Aeronef a turbomachine integree au fuselage arriere comportant une helice entourant un carter d'echappement | |
FR3097260B1 (fr) | Carter de soufflante de turboréacteur |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20180601 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
|
PLFP | Fee payment |
Year of fee payment: 4 |
|
PLFP | Fee payment |
Year of fee payment: 5 |
|
PLFP | Fee payment |
Year of fee payment: 6 |
|
PLFP | Fee payment |
Year of fee payment: 7 |
|
PLFP | Fee payment |
Year of fee payment: 8 |