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WO2004053320A3 - Liaison entre fond arriere de chambre de combustion et tuyere de moteur fusee - Google Patents

Liaison entre fond arriere de chambre de combustion et tuyere de moteur fusee Download PDF

Info

Publication number
WO2004053320A3
WO2004053320A3 PCT/FR2003/003538 FR0303538W WO2004053320A3 WO 2004053320 A3 WO2004053320 A3 WO 2004053320A3 FR 0303538 W FR0303538 W FR 0303538W WO 2004053320 A3 WO2004053320 A3 WO 2004053320A3
Authority
WO
WIPO (PCT)
Prior art keywords
end wall
link
combustion chamber
nozzle
booster motor
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.)
Ceased
Application number
PCT/FR2003/003538
Other languages
English (en)
Other versions
WO2004053320A2 (fr
Inventor
Gilles Renoust
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 Ceramics SA
Original Assignee
SNECMA Propulsion Solide SA
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 Propulsion Solide SA filed Critical SNECMA Propulsion Solide SA
Priority to BR0316787-9A priority Critical patent/BR0316787A/pt
Priority to UAA200505240A priority patent/UA81643C2/ru
Priority to AU2003298377A priority patent/AU2003298377A1/en
Priority to JP2004558142A priority patent/JP2006508296A/ja
Priority to EP03796117A priority patent/EP1567761A2/fr
Publication of WO2004053320A2 publication Critical patent/WO2004053320A2/fr
Publication of WO2004053320A3 publication Critical patent/WO2004053320A3/fr
Priority to IL168861A priority patent/IL168861A/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
    • F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
    • F16J15/0806—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing characterised by material or surface treatment
    • F16J15/0812—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing characterised by material or surface treatment with a braided or knitted body
    • 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
    • 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
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
    • F16J15/064—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces the packing combining the sealing function with other functions
    • F16J15/065—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces the packing combining the sealing function with other functions fire resistant
    • 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
    • F05D2300/614—Fibres or filaments

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Gasket Seals (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Air Supply (AREA)

Abstract

La liaison entre le fond arrière (14) d'une chambre de combustion et la tuyère (20) d'un moteur fusée comprend des moyens (50) de liaison mécanique reliant la tuyère au fond au moins en direction axiale, ainsi qu'une barrière thermique (40) et au moins un joint d'étanchéité (32, 34) disposés dans l'interface (30) définie par les surfaces en regard adjacentes du fond et de la tuyère. La barrière thermique (40) comporte au moins une texture en fibres réfractaires formant un cordon (42) enroulé dans l'interface autour de l'axe longitudinal (A) de la chambre, le ou les cordons étant réalisés de manière à assurer une continuité circonférentielle de la barrière thermique (40).
PCT/FR2003/003538 2002-12-02 2003-12-01 Liaison entre fond arriere de chambre de combustion et tuyere de moteur fusee Ceased WO2004053320A2 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
BR0316787-9A BR0316787A (pt) 2002-12-02 2003-12-01 Ligação entre o fundo posterior da câmara de combustão e injetor de motor de propulsão
UAA200505240A UA81643C2 (ru) 2002-12-02 2003-12-01 Соединение между задней стенкой камеры сгорания и соплом ракетного двигателя
AU2003298377A AU2003298377A1 (en) 2002-12-02 2003-12-01 Link between combustion chamber end wall and booster motor propeller nozzle
JP2004558142A JP2006508296A (ja) 2002-12-02 2003-12-01 燃焼室の後方端壁とロケットエンジンのノズルとの間の接続体
EP03796117A EP1567761A2 (fr) 2002-12-02 2003-12-01 Liaison entre fond arriere de chambre de combustion et tuyere de moteur fusee
IL168861A IL168861A (en) 2002-12-02 2005-05-30 Connection between the rear end wall of a combustion chamber and the nozzle of a rocket engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR02/15158 2002-12-02
FR0215158A FR2847945B1 (fr) 2002-12-02 2002-12-02 Liaison entre fond arriere de chambre de combustion et tuyere de moteur fusee

Publications (2)

Publication Number Publication Date
WO2004053320A2 WO2004053320A2 (fr) 2004-06-24
WO2004053320A3 true WO2004053320A3 (fr) 2004-08-12

Family

ID=32309920

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2003/003538 Ceased WO2004053320A2 (fr) 2002-12-02 2003-12-01 Liaison entre fond arriere de chambre de combustion et tuyere de moteur fusee

Country Status (9)

Country Link
EP (1) EP1567761A2 (fr)
JP (1) JP2006508296A (fr)
AU (1) AU2003298377A1 (fr)
BR (1) BR0316787A (fr)
FR (1) FR2847945B1 (fr)
IL (1) IL168861A (fr)
RU (1) RU2330172C2 (fr)
UA (1) UA81643C2 (fr)
WO (1) WO2004053320A2 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2446307C1 (ru) * 2010-10-21 2012-03-27 Открытое акционерное общество Научно-производственное объединение "Искра" Ракетный двигатель твердого топлива
RU2480611C1 (ru) * 2012-01-11 2013-04-27 Открытое Акционерное Общество "Уральский научно-исследовательский институт композиционных материалов" Способ изготовления камеры жидкостного ракетного двигателя
RU2480610C1 (ru) * 2012-01-11 2013-04-27 Открытое Акционерное Общество "Уральский научно-исследовательский институт композиционных материалов" Камера жидкостного ракетного двигателя
RU2496017C1 (ru) * 2012-03-27 2013-10-20 Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор" Уплотнение внутреннего стыка камеры сгорания и соплового аппарата турбины газотурбинного двигателя
CN104696104B (zh) * 2013-12-10 2016-08-31 上海新力动力设备研究所 固体火箭发动机挡环连接结构
CN112594092A (zh) * 2020-12-20 2021-04-02 西安航天化学动力有限公司 固体火箭发动机喷管与燃烧室的连接套筒
CN114922741A (zh) * 2022-04-28 2022-08-19 北京星际荣耀空间科技股份有限公司 固体火箭发动机卡环连接结构、火箭发动机及火箭
CN115523056B (zh) * 2022-10-31 2024-06-04 北京中科宇航技术有限公司 一种卡环连接的固体火箭发动机

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1283721A (fr) * 1961-03-15 1962-02-02 Thiokol Chemical Corp Système de raccord séparable résistant à la pression
US5358262A (en) * 1992-10-09 1994-10-25 Rolls-Royce, Inc. Multi-layer seal member
US5570573A (en) * 1994-07-08 1996-11-05 Societe Europeene De Propulsion Combustion chamber for a thruster with a sealed connection between an end wall and a composite tubular structure
US5657998A (en) * 1994-09-19 1997-08-19 General Electric Company Gas-path leakage seal for a gas turbine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2084678C1 (ru) * 1994-11-22 1997-07-20 Научно-производственное объединение "Искра" Элемент тракта высокотемпературного потока
RU2183762C1 (ru) * 2000-12-07 2002-06-20 Государственное унитарное предприятие Машиностроительное конструкторское бюро "Факел" им. акад. П.Д. Грушина Двухрежимный сопловой блок для ракетного двигателя

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1283721A (fr) * 1961-03-15 1962-02-02 Thiokol Chemical Corp Système de raccord séparable résistant à la pression
US5358262A (en) * 1992-10-09 1994-10-25 Rolls-Royce, Inc. Multi-layer seal member
US5570573A (en) * 1994-07-08 1996-11-05 Societe Europeene De Propulsion Combustion chamber for a thruster with a sealed connection between an end wall and a composite tubular structure
US5657998A (en) * 1994-09-19 1997-08-19 General Electric Company Gas-path leakage seal for a gas turbine

Also Published As

Publication number Publication date
UA81643C2 (ru) 2008-01-25
IL168861A (en) 2008-11-26
AU2003298377A8 (en) 2004-06-30
RU2005116972A (ru) 2006-01-20
JP2006508296A (ja) 2006-03-09
WO2004053320A2 (fr) 2004-06-24
EP1567761A2 (fr) 2005-08-31
FR2847945B1 (fr) 2005-02-25
RU2330172C2 (ru) 2008-07-27
FR2847945A1 (fr) 2004-06-04
BR0316787A (pt) 2005-11-01
AU2003298377A1 (en) 2004-06-30

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