JP2013515915A5 - - Google Patents

Download PDF

Info

Publication number
JP2013515915A5
JP2013515915A5 JP2012547273A JP2012547273A JP2013515915A5 JP 2013515915 A5 JP2013515915 A5 JP 2013515915A5 JP 2012547273 A JP2012547273 A JP 2012547273A JP 2012547273 A JP2012547273 A JP 2012547273A JP 2013515915 A5 JP2013515915 A5 JP 2013515915A5
Authority
JP
Japan
Prior art keywords
carbon
composite
flow path
wall
aircraft engine
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
JP2012547273A
Other languages
English (en)
Japanese (ja)
Other versions
JP5681728B2 (ja
JP2013515915A (ja
Filing date
Publication date
Priority claimed from US12/978,954 external-priority patent/US8850823B2/en
Application filed filed Critical
Publication of JP2013515915A publication Critical patent/JP2013515915A/ja
Publication of JP2013515915A5 publication Critical patent/JP2013515915A5/ja
Application granted granted Critical
Publication of JP5681728B2 publication Critical patent/JP5681728B2/ja
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

JP2012547273A 2009-12-29 2010-12-29 一体型航空機用エンジン流路構造 Expired - Fee Related JP5681728B2 (ja)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US29080709P 2009-12-29 2009-12-29
US61/290,807 2009-12-29
US12/978,954 2010-12-27
US12/978,954 US8850823B2 (en) 2009-12-29 2010-12-27 Integrated aero-engine flowpath structure
PCT/US2010/062388 WO2011136832A2 (en) 2009-12-29 2010-12-29 Integrated aero-engine flowpath structure

Publications (3)

Publication Number Publication Date
JP2013515915A JP2013515915A (ja) 2013-05-09
JP2013515915A5 true JP2013515915A5 (enExample) 2014-01-30
JP5681728B2 JP5681728B2 (ja) 2015-03-11

Family

ID=44862100

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2012547273A Expired - Fee Related JP5681728B2 (ja) 2009-12-29 2010-12-29 一体型航空機用エンジン流路構造

Country Status (4)

Country Link
US (1) US8850823B2 (enExample)
EP (1) EP2519720B1 (enExample)
JP (1) JP5681728B2 (enExample)
WO (1) WO2011136832A2 (enExample)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2972129B1 (fr) * 2011-03-03 2013-04-12 Snecma Piece en materiau composite comportant des elements de bossage
FR3009026B1 (fr) * 2013-07-24 2018-01-05 Safran Aircraft Engines Corps central d'echappement pour une turbomachine
US9587519B2 (en) * 2013-11-22 2017-03-07 Siemens Energy, Inc. Modular industrial gas turbine exhaust system
EP3265662B1 (en) 2015-03-04 2021-10-13 Sikorsky Aircraft Corporation Gas turbine exhaust assembly
US11313320B2 (en) 2020-02-27 2022-04-26 Rolls-Royce North American Technologies Inc. Exhaust nozzle with centerbody support structure for a gas turbine engine
US11274630B2 (en) * 2020-02-27 2022-03-15 Rolls-Royce North American Technologies Inc. Exhaust nozzle with vane support structure for a gas turbine engine
CN111594339A (zh) * 2020-05-26 2020-08-28 中国人民解放军国防科技大学 采用塞式喷管的冲压发动机

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3651661A (en) 1970-02-02 1972-03-28 United Aircraft Corp Composite shaft with integral end flange
GB8306543D0 (en) 1983-03-09 1983-04-13 Brd Co Ltd Composite shafts
US4535035A (en) 1984-01-17 1985-08-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Oxidation resistant slurry coating for carbon-based materials
GB2161110B (en) 1984-07-07 1988-03-23 Rolls Royce An annular bladed member having an integral shroud and a method of manufacture thereof
US4681261A (en) * 1985-10-01 1987-07-21 The United States Of America As Represented By The Secretary Of The Air Force Heat resistant short nozzle
JPH03119138A (ja) * 1989-09-29 1991-05-21 Shikishima Kanbasu Kk 繊維補強複合材
US5372005A (en) 1992-09-14 1994-12-13 Lawler; Shawn P. Method and apparatus for power generation
US5363643A (en) 1993-02-08 1994-11-15 General Electric Company Segmented combustor
US5780157A (en) 1994-06-06 1998-07-14 Ultramet Composite structure
US5939007A (en) 1994-08-31 1999-08-17 Sikorsky Aircraft Corporation Method for manufacture of a fiber reinforced composite spar for rotary wing aircraft
US5495978A (en) 1994-09-06 1996-03-05 Thermacore, Inc. Bonding diverse thermal expansion materials
US5972157A (en) 1995-11-20 1999-10-26 Alliedsignal Inc. Joining of rough carbon-carbon composites with high joint strength
US6174605B1 (en) 1996-08-20 2001-01-16 Alliedsignal Inc. Joining of rough carbon-carbon composites with high joint strength
JP4060981B2 (ja) 1998-04-08 2008-03-12 本田技研工業株式会社 ガスタービンの静翼構造体及びそのユニット
JP3138750B2 (ja) 1999-03-05 2001-02-26 株式会社先進材料利用ガスジェネレータ研究所 繊維プリフォーム成形法およびその装置
US6200092B1 (en) * 1999-09-24 2001-03-13 General Electric Company Ceramic turbine nozzle
WO2002040254A2 (en) 2000-11-15 2002-05-23 Toyota Motor Sales, U.S.A., Inc. One-piece closed-shape structure and method of forming same
FR2817192B1 (fr) 2000-11-28 2003-08-08 Snecma Moteurs Ensemble forme par au moins une pale et une plate-forme de fixation de la pale, pour une turbomachine, et procede pour sa fabrication
US6821087B2 (en) 2002-01-21 2004-11-23 Honda Giken Kogyo Kabushiki Kaisha Flow-rectifying member and its unit and method for producing flow-rectifying member
US6648597B1 (en) 2002-05-31 2003-11-18 Siemens Westinghouse Power Corporation Ceramic matrix composite turbine vane
DE10239416B4 (de) 2002-08-28 2005-03-03 Robert Bosch Gmbh Verfahren zur Herstellung eines aus Keramikschichten bestehenden Verbundkörpers
US6895757B2 (en) 2003-02-10 2005-05-24 General Electric Company Sealing assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor
US7204195B2 (en) 2004-12-08 2007-04-17 Korea Gas Corporation Ship with liquid tank
AT503840B1 (de) 2006-06-30 2010-09-15 Facc Ag Leitschaufelanordnung für ein triebwerk
GB2455785B (en) 2007-12-21 2009-11-11 Rolls Royce Plc Annular component

Similar Documents

Publication Publication Date Title
JP2013515915A5 (enExample)
JP2013164071A5 (enExample)
JP6491843B2 (ja) ドレインマスト
JP2012052547A5 (enExample)
CN102837818B (zh) 制备集成有使用热空气处理霜的功能的声处理面板的方法
JP2009519861A5 (enExample)
CN204493010U (zh) 一种固体火箭发动机尾喷管喉衬的复合背衬结构
JP2013523483A5 (enExample)
WO2014158284A3 (en) Bi-cast turbine vane
EP2111975A3 (en) Joined composite structures with a graded coefficient of thermal expansion for extreme environment applications
JP6956561B2 (ja) 多壁ブレード用冷却回路
JP2013245673A5 (enExample)
JP2014500185A5 (enExample)
JP2013521886A5 (enExample)
JP2012041918A5 (enExample)
JP2013511010A5 (enExample)
CN107989660A (zh) 具有压力侧碰撞的部分包覆后缘冷却回路
CN107989655B (zh) 用于多壁叶片的冷却回路
JP2011009216A5 (enExample)
JP6366225B2 (ja) 胴体の組立てに使用される方法及びシステム
WO2007126892A3 (en) Joint and joining method for multilayer composite tubing
CN205371271U (zh) 传动轴结构
CN103629469A (zh) 抗震、耐高温空冷系统专用补偿器
JP5681728B2 (ja) 一体型航空機用エンジン流路構造
CN107989658A (zh) 用于多壁叶片的冷却回路