SE0202460L - Closed-engine rocket engine with modular turbine exhaust gas supply - Google Patents
Closed-engine rocket engine with modular turbine exhaust gas supplyInfo
- 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
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.
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)
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)
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 |
-
2001
- 2001-08-22 DE DE2001141108 patent/DE10141108B4/en not_active Expired - Fee Related
-
2002
- 2002-08-13 FR FR0210267A patent/FR2828911B1/en not_active Expired - Lifetime
- 2002-08-19 SE SE0202460A patent/SE523632C2/en not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
SE0202460D0 (en) | 2002-08-19 |
SE523632C2 (en) | 2004-05-04 |
FR2828911B1 (en) | 2007-04-13 |
DE10141108A1 (en) | 2003-03-20 |
FR2828911A1 (en) | 2003-02-28 |
DE10141108B4 (en) | 2005-06-30 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
NUG | Patent has lapsed |