JP2016528428A5 - - Google Patents

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Publication number
JP2016528428A5
JP2016528428A5 JP2016526683A JP2016526683A JP2016528428A5 JP 2016528428 A5 JP2016528428 A5 JP 2016528428A5 JP 2016526683 A JP2016526683 A JP 2016526683A JP 2016526683 A JP2016526683 A JP 2016526683A JP 2016528428 A5 JP2016528428 A5 JP 2016528428A5
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JP
Japan
Prior art keywords
cover
centrifugal compressor
turbine engine
flange
upstream
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.)
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Application number
JP2016526683A
Other languages
English (en)
Japanese (ja)
Other versions
JP6475239B2 (ja
JP2016528428A (ja
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Publication date
Priority claimed from FR1357109A external-priority patent/FR3008750B1/fr
Application filed filed Critical
Publication of JP2016528428A publication Critical patent/JP2016528428A/ja
Publication of JP2016528428A5 publication Critical patent/JP2016528428A5/ja
Application granted granted Critical
Publication of JP6475239B2 publication Critical patent/JP6475239B2/ja
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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JP2016526683A 2013-07-18 2014-07-17 上流縁の近くでその下流側を通じてしっかりと接続されることが可能なターボ機械遠心圧縮機のカバー、およびこのカバーを備えるターボ機械 Active JP6475239B2 (ja)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1357109A FR3008750B1 (fr) 2013-07-18 2013-07-18 Couvercle de compresseur centrifuge de turbomachine apte a etre fixe par l'aval pres de son bord amont, turbomachine comportant ce couvercle.
FR1357109 2013-07-18
PCT/FR2014/051842 WO2015008000A2 (fr) 2013-07-18 2014-07-17 Couvercle de compresseur centrifuge de turbomachine apte à être fixé par l'aval près de son bord amont, turbomachine comportant ce couvercle

Publications (3)

Publication Number Publication Date
JP2016528428A JP2016528428A (ja) 2016-09-15
JP2016528428A5 true JP2016528428A5 (enExample) 2017-08-10
JP6475239B2 JP6475239B2 (ja) 2019-02-27

Family

ID=49620058

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2016526683A Active JP6475239B2 (ja) 2013-07-18 2014-07-17 上流縁の近くでその下流側を通じてしっかりと接続されることが可能なターボ機械遠心圧縮機のカバー、およびこのカバーを備えるターボ機械

Country Status (9)

Country Link
US (1) US10100842B2 (enExample)
EP (1) EP3022404B1 (enExample)
JP (1) JP6475239B2 (enExample)
CN (1) CN105452616B (enExample)
BR (1) BR112016000823B1 (enExample)
CA (1) CA2919596C (enExample)
FR (1) FR3008750B1 (enExample)
RU (1) RU2660718C2 (enExample)
WO (1) WO2015008000A2 (enExample)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3040077B1 (fr) * 2015-08-12 2017-08-11 Snecma Turbomachine, telle par exemple qu'un turboreacteur ou un turbopropulseur d'avion
FR3103240B1 (fr) 2019-11-15 2022-07-15 Safran Aircraft Engines Rouet pour un porte-satellites de reducteur de vitesse a train epicycloïdal de turbomachine
FR3103241B1 (fr) 2019-11-15 2021-12-17 Safran Trans Systems Rouet pour un porte-satellites de reducteur de vitesse a train epicycloïdal de turbomachine
FR3128753B1 (fr) 2021-11-03 2023-11-24 Safran Trans Systems Reducteur mecanique de vitesse pour une turbomachine d’aeronef
US12345162B2 (en) * 2023-11-17 2025-07-01 Rolls-Royce Corporation Adjustable position impeller shroud for centrifugal compressors

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4248566A (en) * 1978-10-06 1981-02-03 General Motors Corporation Dual function compressor bleed
US4264271A (en) * 1979-03-15 1981-04-28 Avco Corporation Impeller shroud of a centrifugal compressor
US4687412A (en) * 1985-07-03 1987-08-18 Pratt & Whitney Canada Inc. Impeller shroud
JPH03260336A (ja) 1990-03-12 1991-11-20 Mitsubishi Heavy Ind Ltd 遠心圧縮機の抽気装置
US6183195B1 (en) * 1999-02-04 2001-02-06 Pratt & Whitney Canada Corp. Single slot impeller bleed
US6585482B1 (en) * 2000-06-20 2003-07-01 General Electric Co. Methods and apparatus for delivering cooling air within gas turbines
US7094029B2 (en) * 2003-05-06 2006-08-22 General Electric Company Methods and apparatus for controlling gas turbine engine rotor tip clearances
US7435050B2 (en) * 2006-01-11 2008-10-14 United Technologies Corporation Split flange V-groove and anti-rotation mating system
US7824151B2 (en) * 2006-12-06 2010-11-02 United Technologies Corporation Zero running clearance centrifugal compressor
US8292592B2 (en) * 2008-04-02 2012-10-23 United Technologies Corporation Nosecone bolt access and aerodynamic leakage baffle
FR2930588B1 (fr) * 2008-04-24 2010-06-04 Snecma Rotor de compresseur d'une turbomachine comportant des moyens de prelevement d'air centripete
FR2931521B1 (fr) * 2008-05-26 2017-06-23 Turbomeca Couvercle de compresseur a butee axiale.
US8087880B2 (en) * 2008-12-03 2012-01-03 General Electric Company Active clearance control for a centrifugal compressor
US8147178B2 (en) * 2008-12-23 2012-04-03 General Electric Company Centrifugal compressor forward thrust and turbine cooling apparatus
US8616854B2 (en) * 2009-03-05 2013-12-31 Rolls-Royce Corporation Nose cone assembly
FR2976623B1 (fr) * 2011-06-20 2013-06-28 Snecma Dispositif de decouplage pour turbomoteur a double flux
US9353685B2 (en) * 2012-12-21 2016-05-31 United Technologies Corporation Turbine engine nosecone with deformation region
US9650916B2 (en) * 2014-04-09 2017-05-16 Honeywell International Inc. Turbomachine cooling systems

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