SE0202460L - Closed-engine rocket engine with modular turbine exhaust gas supply - Google Patents

Closed-engine rocket engine with modular turbine exhaust gas supply

Info

Publication number
SE0202460L
SE0202460L SE0202460A SE0202460A SE0202460L SE 0202460 L SE0202460 L SE 0202460L SE 0202460 A SE0202460 A SE 0202460A SE 0202460 A SE0202460 A SE 0202460A SE 0202460 L SE0202460 L SE 0202460L
Authority
SE
Sweden
Prior art keywords
engine
closed
exhaust gas
gas supply
turbine exhaust
Prior art date
Application number
SE0202460A
Other languages
Unknown language ( )
Swedish (sv)
Other versions
SE523632C2 (en
SE0202460D0 (en
Inventor
Herbert Linner
Stefan Menne
Original Assignee
Astrium Gmbh
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 Astrium Gmbh filed Critical Astrium Gmbh
Publication of SE0202460D0 publication Critical patent/SE0202460D0/en
Publication of SE0202460L publication Critical patent/SE0202460L/en
Publication of SE523632C2 publication Critical patent/SE523632C2/en

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
    • F02K9/97—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
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

The closed circuit rocket motor has the propergol feed pumps driven by turbines with closed circuit operation. The exhaust from the turbines is fed to an inlet for parallel flow to the expansion nozzle (3) with the main exhaust. The inlet has an injection nozzle (2) with a connection for the turbine gases into the expansion section of the nozzle. An inlet turbine (1) is mechanically connected to the injector.
SE0202460A 2001-08-22 2002-08-19 Closed-engine rocket engine with modular turbine exhaust gas supply SE523632C2 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2001141108 DE10141108B4 (en) 2001-08-22 2001-08-22 Rocket engine with closed engine cycle with modular supply of turbine exhaust

Publications (3)

Publication Number Publication Date
SE0202460D0 SE0202460D0 (en) 2002-08-19
SE0202460L true SE0202460L (en) 2003-02-23
SE523632C2 SE523632C2 (en) 2004-05-04

Family

ID=7696227

Family Applications (1)

Application Number Title Priority Date Filing Date
SE0202460A SE523632C2 (en) 2001-08-22 2002-08-19 Closed-engine rocket engine with modular turbine exhaust gas supply

Country Status (3)

Country Link
DE (1) DE10141108B4 (en)
FR (1) FR2828911B1 (en)
SE (1) SE523632C2 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2326259C1 (en) * 2007-04-24 2008-06-10 Московский авиационный институт (государственный технический университет) High-altitude laval nozzle
FR2923269B1 (en) * 2007-11-06 2011-06-17 Centre Nat Etd Spatiales PROPULSIVE TUYERE FOR RELAXING A SUPERSONIC GAS JET
FR3094414B1 (en) * 2019-03-27 2021-04-09 Arianegroup Sas Nozzle equipped with a thermo-regulated crown

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB724004A (en) * 1952-04-29 1955-02-16 Rolls Royce Improvements in or relating to fuel supply arrangements for gas-turbine engines
US3093963A (en) * 1959-07-17 1963-06-18 North American Aviation Inc Manifolded exhaust duct
US3134224A (en) * 1961-05-26 1964-05-26 United Aircraft Corp Gas bleed from rocket chamber
US3267664A (en) * 1963-03-19 1966-08-23 North American Aviation Inc Method of and device for cooling
US3481543A (en) * 1967-12-18 1969-12-02 Thiokol Chemical Corp Rocket thrust nozzle
DE2356572C3 (en) * 1973-11-13 1979-03-29 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Liquid-cooled rocket combustion chamber with thrust nozzle
US4007586A (en) * 1975-11-10 1977-02-15 The United States Of America As Represented By The Secretary Of The Army Spin nozzle and thrust augmentor mechanism
US4220001A (en) * 1977-08-17 1980-09-02 Aerojet-General Corporation Dual expander rocket engine
DE3506826A1 (en) * 1985-02-27 1986-08-28 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Method for the operation of a liquid-fuelled rocket engine and rocket engine for implementing the method
FR2618488B1 (en) * 1987-07-20 1989-12-15 Europ Propulsion DIVERGENT WITH BREAKING GALBE FOR NOZZLE OF MOTOR-ROCKET
FR2698914B1 (en) * 1992-12-09 1995-03-03 Europ Propulsion Rocket motor with liquid propellants with derivative flow and integrated gas generator.
RU2158839C2 (en) * 1999-01-21 2000-11-10 Открытое акционерное общество "НПО Энергомаш им. акад. В.П. Глушко" Liquid-propellant rocket reheat engine

Also Published As

Publication number Publication date
DE10141108A1 (en) 2003-03-20
SE523632C2 (en) 2004-05-04
DE10141108B4 (en) 2005-06-30
SE0202460D0 (en) 2002-08-19
FR2828911B1 (en) 2007-04-13
FR2828911A1 (en) 2003-02-28

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