FR2374519A1 - Procede de fabrication de chambres de combustion pour fusees et de tuyeres de poussee a refroidissement regeneratif - Google Patents

Procede de fabrication de chambres de combustion pour fusees et de tuyeres de poussee a refroidissement regeneratif

Info

Publication number
FR2374519A1
FR2374519A1 FR7737933A FR7737933A FR2374519A1 FR 2374519 A1 FR2374519 A1 FR 2374519A1 FR 7737933 A FR7737933 A FR 7737933A FR 7737933 A FR7737933 A FR 7737933A FR 2374519 A1 FR2374519 A1 FR 2374519A1
Authority
FR
France
Prior art keywords
rockets
combustion chambers
ducts
ribs
regenerative cooling
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
FR7737933A
Other languages
English (en)
Other versions
FR2374519B1 (fr
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of FR2374519A1 publication Critical patent/FR2374519A1/fr
Application granted granted Critical
Publication of FR2374519B1 publication Critical patent/FR2374519B1/fr
Granted legal-status Critical Current

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
    • F02K9/42—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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/291—Three-dimensional machined; miscellaneous hollowed
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4981—Utilizing transitory attached element or associated separate material

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Fabrication de chambres de combustion pour fusées et/ou de tuyères de poussée à refroidissement régénératif, qui comportent, entre une enveloppe intérieure et une enveloppe extérieure, des conduits de refroidissement longitudinaux délimités latéralement par des nervures radiales, la fabrication se faisant par voie galvanoplastique et laissant substituer, dans lesdites nervures, des fentes ouvertes vers le côté gaz chauds. La chambre de combustion 1 et/ou la tuyère d'éjection 2 sont ensuite glissées sur un mandrin 12, et les conduits 6 sont déformés sur ce mandrin 12, par application d'une pression à partir de la face interne des conduits, en vue de l'obturation des fentes 8 dans les nervures 5 des conduits.
FR7737933A 1976-12-18 1977-12-15 Procede de fabrication de chambres de combustion pour fusees et de tuyeres de poussee a refroidissement regeneratif Granted FR2374519A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19762657474 DE2657474A1 (de) 1976-12-18 1976-12-18 Verfahren zum herstellen von regenerativ gekuehlten raketenbrennkammern und/oder schubduesen

Publications (2)

Publication Number Publication Date
FR2374519A1 true FR2374519A1 (fr) 1978-07-13
FR2374519B1 FR2374519B1 (fr) 1984-09-14

Family

ID=5995879

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7737933A Granted FR2374519A1 (fr) 1976-12-18 1977-12-15 Procede de fabrication de chambres de combustion pour fusees et de tuyeres de poussee a refroidissement regeneratif

Country Status (3)

Country Link
US (1) US4156306A (fr)
DE (1) DE2657474A1 (fr)
FR (1) FR2374519A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2482278A1 (fr) * 1980-03-24 1981-11-13 Kernforschungsanlage Juelich Absorbeur de chaleur, en particulier absorbeur de rayonnement du plasma et procede pour sa fabrication
FR2519508A1 (fr) * 1981-12-31 1983-07-08 Thomson Csf Dispositif de refroidissement pour carte de circuit imprime et procede de fabrication d'un tel dispositif
EP0413983A1 (fr) * 1989-08-25 1991-02-27 Rockwell International Corporation Méthode de fabrication d'une paroi avec canaux de refroidissement pour une tuyère à réaction
FR2700583A1 (fr) * 1993-01-16 1994-07-22 Deutsche Aerospace Procédé de fabrication d'une paroi refroidie par fluide formée de petits tubes assemblés.

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4623087A (en) * 1983-05-26 1986-11-18 Rolls-Royce Limited Application of coatings to articles
US4535518A (en) * 1983-09-19 1985-08-20 Rockwell International Corporation Method of forming small-diameter channel within an object
US4586226A (en) * 1983-09-30 1986-05-06 Rockwell International Corporation Method for fabricating a small-orifice fuel injector
US4707225A (en) * 1986-01-06 1987-11-17 Rockwell International Corporation Fluid-cooled channel construction
JPH0659523B2 (ja) * 1988-09-09 1994-08-10 ノムラテクノリサーチ株式会社 連続鋳造用鋳型の製造方法
US5283020A (en) * 1989-09-28 1994-02-01 United Technologies Corporation Component protection from contaminants
US5908285A (en) * 1995-03-10 1999-06-01 United Technologies Corporation Electroformed sheath
US6998566B2 (en) * 2002-04-19 2006-02-14 Thermal Dynamics Corporation Plasma arc torch electrode
US7213392B2 (en) * 2003-06-10 2007-05-08 United Technologies Corporation Rocket engine combustion chamber
WO2007030038A1 (fr) * 2005-09-06 2007-03-15 Volvo Aero Corporation Structure de paroi du moteur et procedes pour produire une structure de paroi du moteur
ES2350847T3 (es) * 2005-09-06 2011-01-27 Volvo Aero Corporation Procedimiento para la fabricación de una estructura de pared de un motor.
US8286348B2 (en) * 2008-09-22 2012-10-16 Mtu Aero Engines Gmbh Method of manufacturing and refinishing integrally bladed rotors
US8672634B2 (en) 2010-08-30 2014-03-18 United Technologies Corporation Electroformed conforming rubstrip
DE102016212314B4 (de) * 2016-07-06 2022-05-12 Arianegroup Gmbh Verfahren zur Herstellung einer Brennkammer
US10697075B2 (en) 2018-03-29 2020-06-30 Unison Industries, Llc Duct assembly and method of forming
US10697076B2 (en) 2018-03-29 2020-06-30 Unison Industries, Llc Duct assembly and method of forming
US10975486B2 (en) 2018-03-29 2021-04-13 Unison Industries, Llc Duct assembly and method of forming
US10731486B2 (en) 2018-03-29 2020-08-04 Unison Industries, Llc Duct assembly and method of forming
US11391247B1 (en) * 2019-01-24 2022-07-19 Firefly Aerospace Inc. Liquid rocket engine cooling channels
US11008977B1 (en) 2019-09-26 2021-05-18 Firefly Aerospace Inc. Liquid rocket engine tap-off power source
US11846251B1 (en) 2020-04-24 2023-12-19 Firefly Aerospace Inc. Liquid rocket engine booster engine with combustion gas fuel source
CN113357054B (zh) * 2021-07-27 2022-11-11 中国人民解放军国防科技大学 一种高温燃气通道设计方法
CN115740965B (zh) * 2022-11-01 2023-05-16 北京智创联合科技股份有限公司 整体结构火箭发动机燃烧室的制造方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3235947A (en) * 1961-12-22 1966-02-22 Bolkow Gmbh Method for making a combustion chamber
FR2036219A5 (fr) * 1969-03-06 1970-12-24 Messerschmitt Boelkow Blohm
FR2147036A1 (fr) * 1971-07-24 1973-03-09 Messerschmitt Boelkow Blohm

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1264160B (de) * 1966-12-15 1968-03-21 Boelkow Gmbh Fluessigkeitsgekuehlte Bauteile, wie Raketenbrennkammern, und Verfahren zu deren Herstellung
FR2012723A1 (fr) * 1968-07-11 1970-03-20 Messerschmitt Boelkow Blohm
DE1941296B2 (de) * 1969-08-14 1971-09-30 Messerschmitt Bolkow Blohm GmbH, 8000 München Durch ein fluessiges medium regenerativ gekuehlte brenn kammer mit schubduese
US3692637A (en) * 1969-11-24 1972-09-19 Carl Helmut Dederra Method of fabricating a hollow structure having cooling channels
DE2015024B2 (de) * 1970-03-28 1971-10-14 Messerschmitt Bolkow Blohm GmbH, 8000 München Verfahren zur herstellung von regenerativ gekuehlten brenn kammern und oder schubduesen
US3897316A (en) * 1972-05-17 1975-07-29 Us Air Force Method for manufacturing a composite wall for a regeneratively cooled thrust chamber of a liquid propellant rocket engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3235947A (en) * 1961-12-22 1966-02-22 Bolkow Gmbh Method for making a combustion chamber
FR2036219A5 (fr) * 1969-03-06 1970-12-24 Messerschmitt Boelkow Blohm
FR2147036A1 (fr) * 1971-07-24 1973-03-09 Messerschmitt Boelkow Blohm

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2482278A1 (fr) * 1980-03-24 1981-11-13 Kernforschungsanlage Juelich Absorbeur de chaleur, en particulier absorbeur de rayonnement du plasma et procede pour sa fabrication
FR2519508A1 (fr) * 1981-12-31 1983-07-08 Thomson Csf Dispositif de refroidissement pour carte de circuit imprime et procede de fabrication d'un tel dispositif
EP0083538A1 (fr) * 1981-12-31 1983-07-13 Thomson-Csf Procédé de fabrication d'un dispositif de refroidissement pour carte de circuit imprimé, utilisation de ce procédé
EP0413983A1 (fr) * 1989-08-25 1991-02-27 Rockwell International Corporation Méthode de fabrication d'une paroi avec canaux de refroidissement pour une tuyère à réaction
FR2700583A1 (fr) * 1993-01-16 1994-07-22 Deutsche Aerospace Procédé de fabrication d'une paroi refroidie par fluide formée de petits tubes assemblés.

Also Published As

Publication number Publication date
US4156306A (en) 1979-05-29
DE2657474A1 (de) 1978-06-22
FR2374519B1 (fr) 1984-09-14

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Legal Events

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ST Notification of lapse