FR2963063B1 - Chambre de combustion munie d'un element tubulaire - Google Patents

Chambre de combustion munie d'un element tubulaire

Info

Publication number
FR2963063B1
FR2963063B1 FR1056104A FR1056104A FR2963063B1 FR 2963063 B1 FR2963063 B1 FR 2963063B1 FR 1056104 A FR1056104 A FR 1056104A FR 1056104 A FR1056104 A FR 1056104A FR 2963063 B1 FR2963063 B1 FR 2963063B1
Authority
FR
France
Prior art keywords
combustion chamber
tubular element
tubular
combustion
chamber
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
Application number
FR1056104A
Other languages
English (en)
Other versions
FR2963063A1 (fr
Inventor
Dominique Indersie
Didier Guichard
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Priority to FR1056104A priority Critical patent/FR2963063B1/fr
Priority to US13/812,261 priority patent/US9759163B2/en
Priority to PCT/FR2011/051792 priority patent/WO2012022889A1/fr
Priority to DE112011102511T priority patent/DE112011102511T5/de
Publication of FR2963063A1 publication Critical patent/FR2963063A1/fr
Application granted granted Critical
Publication of FR2963063B1 publication Critical patent/FR2963063B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • F02K9/343—Joints, connections, seals therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/40—Cooling arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/64—Combustion or thrust chambers having cooling arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F02K9/972—Fluid cooling arrangements for nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F02K9/974—Nozzle- linings; Ablative coatings
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
FR1056104A 2010-07-26 2010-07-26 Chambre de combustion munie d'un element tubulaire Active FR2963063B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR1056104A FR2963063B1 (fr) 2010-07-26 2010-07-26 Chambre de combustion munie d'un element tubulaire
US13/812,261 US9759163B2 (en) 2010-07-26 2011-07-26 Combustion chamber provided with a tubular element
PCT/FR2011/051792 WO2012022889A1 (fr) 2010-07-26 2011-07-26 Chambre de combustion munie d'un element tubulaire
DE112011102511T DE112011102511T5 (de) 2010-07-26 2011-07-26 Mit einem rohrförmigen Element ausgestattete Brennkammer

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1056104A FR2963063B1 (fr) 2010-07-26 2010-07-26 Chambre de combustion munie d'un element tubulaire

Publications (2)

Publication Number Publication Date
FR2963063A1 FR2963063A1 (fr) 2012-01-27
FR2963063B1 true FR2963063B1 (fr) 2015-11-27

Family

ID=43806802

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1056104A Active FR2963063B1 (fr) 2010-07-26 2010-07-26 Chambre de combustion munie d'un element tubulaire

Country Status (4)

Country Link
US (1) US9759163B2 (fr)
DE (1) DE112011102511T5 (fr)
FR (1) FR2963063B1 (fr)
WO (1) WO2012022889A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3042542B1 (fr) * 2015-10-20 2017-12-01 Snecma Chambre propulsive et procede de fabrication
WO2017222908A1 (fr) * 2016-06-21 2017-12-28 Aerojet Rocketdyne, Inc. Moteur-fusée à propergol liquide ayant un refroidissement passif du condensat
DE102016215244A1 (de) * 2016-08-16 2018-02-22 Airbus Ds Gmbh Brennkammerstruktur, insbesondere für ein raketentriebwerk
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
RU2755848C1 (ru) * 2020-06-23 2021-09-22 Федеральное государственное бюджетное образовательное учреждение высшего образования "Воронежский государственный технический университет" Криогенный жидкостный ракетный двигатель комбинированной схемы (варианты)
CN114233516B (zh) * 2021-12-23 2023-05-09 南京航空航天大学 一种具有再生冷却功能的复合材料爆震发动机燃烧室结构

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2714286A (en) * 1944-07-14 1955-08-02 Aerojet General Co Liquid propellant injection system for jet motors
US2686400A (en) * 1948-07-12 1954-08-17 Us Air Force Regenerative liquid fuel rocket motor
US2958183A (en) * 1949-02-24 1960-11-01 Singelmann Dietrich Rocket combustion chamber
GB759901A (en) * 1951-12-06 1956-10-24 Armstrong Siddeley Motors Ltd Combustion chambers
GB793300A (en) * 1953-06-19 1958-04-16 Havilland Engine Co Ltd Rocket motors
US3863443A (en) * 1963-10-25 1975-02-04 United Aircraft Corp High pressure rocket and cooling means
US4779799A (en) * 1987-03-16 1988-10-25 Rockwell International Corporation Extendible nozzle
US5701670A (en) * 1994-06-23 1997-12-30 Boeing North American, Inc. Method of making rocket engine combustion chamber utilizing "slide in" port liner
FR2733581B1 (fr) 1995-04-27 1997-07-18 Europ Propulsion Enceinte de combustion avec refroidissement par transpiration
US5832719A (en) * 1995-12-18 1998-11-10 United Technologies Corporation Rocket thrust chamber
US6134782A (en) * 1998-11-30 2000-10-24 United Technologies Corporation Method of forming a rocket thrust chamber
US6325108B1 (en) * 1999-06-21 2001-12-04 David S. Bettinger Prestressed composite cryogenic piping
JP4446135B2 (ja) * 2000-01-25 2010-04-07 株式会社Ｉｈｉ 繊維強化複合部材の製造方法およびその装置
US6783824B2 (en) * 2001-01-25 2004-08-31 Hyper-Therm High-Temperature Composites, Inc. Actively-cooled fiber-reinforced ceramic matrix composite rocket propulsion thrust chamber and method of producing the same
DE10126923B4 (de) * 2001-06-01 2006-11-23 Eads Space Transportation Gmbh Raketentriebwerk mit Trennung von Innenmantel und Außenmantel
US6688100B1 (en) * 2002-07-16 2004-02-10 The Boeing Company Combustion chamber having a multiple-piece liner and associated assembly method
US6829884B2 (en) 2002-11-19 2004-12-14 The Boeing Company Rocket engine combustion chamber having multiple conformal throat supports
DE10312776B4 (de) * 2003-03-21 2008-10-02 Eads Space Transportation Gmbh Ausfahrbare Schubdüsenglocke für ein Raketentriebwerk
US20090235636A1 (en) * 2008-03-21 2009-09-24 Robert Oehrlein Reinforced, regeneratively cooled uni-body rocket engine
US20100031626A1 (en) * 2008-03-21 2010-02-11 Robert Oehrlein Carbon-Kevlar uni-body rocket engine and method of making same

Also Published As

Publication number Publication date
WO2012022889A1 (fr) 2012-02-23
US20130219901A1 (en) 2013-08-29
FR2963063A1 (fr) 2012-01-27
DE112011102511T5 (de) 2013-05-29
US9759163B2 (en) 2017-09-12

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