JP2005513322A5 - - Google Patents

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Publication number
JP2005513322A5
JP2005513322A5 JP2003553114A JP2003553114A JP2005513322A5 JP 2005513322 A5 JP2005513322 A5 JP 2005513322A5 JP 2003553114 A JP2003553114 A JP 2003553114A JP 2003553114 A JP2003553114 A JP 2003553114A JP 2005513322 A5 JP2005513322 A5 JP 2005513322A5
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JP
Japan
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
JP2003553114A
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JP4452919B2 (ja
JP2005513322A (ja
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Priority claimed from SE0104273A external-priority patent/SE520669C2/sv
Application filed filed Critical
Priority claimed from PCT/SE2002/002085 external-priority patent/WO2003052255A1/en
Publication of JP2005513322A publication Critical patent/JP2005513322A/ja
Publication of JP2005513322A5 publication Critical patent/JP2005513322A5/ja
Application granted granted Critical
Publication of JP4452919B2 publication Critical patent/JP4452919B2/ja
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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JP2003553114A 2001-12-18 2002-11-15 動作中に高い熱負荷を受ける構成部品及びそのような構成部品を製造する方法 Expired - Fee Related JP4452919B2 (ja)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US34049001P 2001-12-18 2001-12-18
SE0104273A SE520669C2 (sv) 2001-12-18 2001-12-18 En komponent avsedd att utsättas för hög termisk last vid drift, och ett förfarande för tillverkning av en sådan komponent
PCT/SE2002/002085 WO2003052255A1 (en) 2001-12-18 2002-11-15 A component for being subjected to high thermal load during operation and a method for manufacturing such a component

Publications (3)

Publication Number Publication Date
JP2005513322A JP2005513322A (ja) 2005-05-12
JP2005513322A5 true JP2005513322A5 (ja) 2005-12-22
JP4452919B2 JP4452919B2 (ja) 2010-04-21

Family

ID=26655628

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2003553114A Expired - Fee Related JP4452919B2 (ja) 2001-12-18 2002-11-15 動作中に高い熱負荷を受ける構成部品及びそのような構成部品を製造する方法

Country Status (9)

Country Link
US (1) US7299622B2 (ja)
EP (1) EP1458968B1 (ja)
JP (1) JP4452919B2 (ja)
AT (1) ATE367519T1 (ja)
AU (1) AU2002347745A1 (ja)
DE (1) DE60221284T2 (ja)
ES (1) ES2290344T3 (ja)
RU (1) RU2289035C2 (ja)
WO (1) WO2003052255A1 (ja)

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US7188417B2 (en) * 2002-06-28 2007-03-13 United Technologies Corporation Advanced L-channel welded nozzle design
EP1398569A1 (de) * 2002-09-13 2004-03-17 Siemens Aktiengesellschaft Gasturbine
DE10343049B3 (de) * 2003-09-16 2005-04-14 Eads Space Transportation Gmbh Brennkammer mit Kühleinrichtung und Verfahren zur Herstellung der Brennkammer
US7596940B2 (en) * 2005-03-22 2009-10-06 Pratt & Whitney Rocketdyne, Inc. Rocket engine nozzle and method of fabricating a rocket engine nozzle using pressure brazing
WO2007030038A1 (en) * 2005-09-06 2007-03-15 Volvo Aero Corporation An engine wall structure and a method of producing an engine wall structure
DE602005023223D1 (de) * 2005-09-06 2010-10-07 Volvo Aero Corp Verfahren zur herstellung einer motorwandstruktur
SE531857C2 (sv) * 2007-12-21 2009-08-25 Volvo Aero Corp En komponent avsedd att utsättas för hög termisk last vid drift
DE102008011502A1 (de) * 2008-02-25 2009-09-03 Deutsches Zentrum für Luft- und Raumfahrt e.V. Düsenerweiterung und Verfahren zur Herstellung einer Düsenerweiterung
FR2962493B1 (fr) * 2010-07-09 2014-05-16 Snecma Chambre de propulsion de moteur-fusee et procede de fabrication d'une telle chambre
RU2511942C1 (ru) * 2013-03-18 2014-04-10 Николай Борисович Болотин Система охлаждения камеры жидкостного ракетного двигателя
JP6481978B2 (ja) 2015-03-10 2019-03-13 三菱重工業株式会社 燃焼室の冷却機構、冷却機構を備えるロケットエンジン、及び、冷却機構の製造方法
FR3042542B1 (fr) * 2015-10-20 2017-12-01 Snecma Chambre propulsive et procede de fabrication
RU168808U1 (ru) * 2016-04-20 2017-02-21 Акционерное общество "НПО Энергомаш имени академика В.П. Глушко" Корпус газовода жидкостного ракетного двигателя с дожиганием генераторного газа
CN108060990A (zh) * 2016-11-07 2018-05-22 贾海亮 一种串联单机固体发动机
US10739001B2 (en) * 2017-02-14 2020-08-11 Raytheon Technologies Corporation Combustor liner panel shell interface for a gas turbine engine combustor
US10823411B2 (en) 2017-02-23 2020-11-03 Raytheon Technologies Corporation Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor
US10830434B2 (en) 2017-02-23 2020-11-10 Raytheon Technologies Corporation Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
US10677462B2 (en) 2017-02-23 2020-06-09 Raytheon Technologies Corporation Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor
US10718521B2 (en) 2017-02-23 2020-07-21 Raytheon Technologies Corporation Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor
US10941937B2 (en) 2017-03-20 2021-03-09 Raytheon Technologies Corporation Combustor liner with gasket for gas turbine engine
CN107023419B (zh) * 2017-05-03 2019-05-03 湖北航天技术研究院总体设计所 一种固体火箭发动机燃烧室壳体轻质接头
US20190329355A1 (en) * 2018-04-27 2019-10-31 United States Of America As Represented By The Administrator Of Nasa Method for Fabricating Seal-Free Multi-Metallic Thrust Chamber Liner
US11448163B1 (en) 2018-09-05 2022-09-20 Abl Space Systems Multi-part fluid chamber and method of manufacturing
CN110578619A (zh) * 2019-09-29 2019-12-17 上海空间推进研究所 液体火箭发动机再生冷却身部及其槽道结构
FR3110483B1 (fr) * 2020-05-20 2022-06-03 Arianegroup Sas Structure d’assemblage d’une pièce comprenant une première partie métallique et une deuxième partie en matériau composite à matrice organique
CN112462714B (zh) * 2020-12-01 2021-08-24 陕西蓝箭航天技术有限公司 航天器推力室双层结构的加工方法
JP2023065163A (ja) 2021-10-27 2023-05-12 インターステラテクノロジズ株式会社 ロケットエンジンの燃焼器及びその製造方法

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US4655044A (en) * 1983-12-21 1987-04-07 United Technologies Corporation Coated high temperature combustor liner
US4622821A (en) * 1985-01-07 1986-11-18 United Technologies Corporation Combustion liner for a gas turbine engine
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
GB2257781B (en) * 1991-04-30 1995-04-12 Rolls Royce Plc Combustion chamber assembly in a gas turbine engine
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RU2158666C2 (ru) * 1999-02-04 2000-11-10 Открытое акционерное общество НПО Энергомаш им. акад. В.П. Глушко Способ изготовления сварно-паяной конструкции
ATE393875T1 (de) * 2001-01-11 2008-05-15 Volvo Aero Corp Raketentriebwerksglied und ein verfahren zur herstellung eines raketentriebwerksglieds
US6701714B2 (en) * 2001-12-05 2004-03-09 United Technologies Corporation Gas turbine combustor

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