WO2011107090A3 - Method for operating a rocket engine and rocket engine - Google Patents

Method for operating a rocket engine and rocket engine Download PDF

Info

Publication number
WO2011107090A3
WO2011107090A3 PCT/DE2011/075019 DE2011075019W WO2011107090A3 WO 2011107090 A3 WO2011107090 A3 WO 2011107090A3 DE 2011075019 W DE2011075019 W DE 2011075019W WO 2011107090 A3 WO2011107090 A3 WO 2011107090A3
Authority
WO
WIPO (PCT)
Prior art keywords
rocket engine
combustion chamber
engine
hydrocarbon
hydrogen
Prior art date
Application number
PCT/DE2011/075019
Other languages
German (de)
French (fr)
Other versions
WO2011107090A2 (en
Inventor
Olaf Przybilski
Original Assignee
Technische Universität Dresden
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 Technische Universität Dresden filed Critical Technische Universität Dresden
Publication of WO2011107090A2 publication Critical patent/WO2011107090A2/en
Publication of WO2011107090A3 publication Critical patent/WO2011107090A3/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
    • 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
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
    • F02K9/766—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with liquid propellant
    • 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
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • F05D2240/1281—Plug nozzles
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in line

Abstract

The invention relates to a method for operating a rocket engine, which method makes it possible to provide single-stage carrier rockets that achieve an optimal thrust and a maximum specific impulse over the combustion duration of the engine. The invention further relates to a rocket engine that allows the method according to the invention to be carried out. In the method according to the invention, at least one hydrocarbon is reacted with oxygen in a first combustion chamber of the rocket engine and hydrogen is reacted with oxygen in a second combustion chamber of the rocket engine. The reaction in the first combustion chamber is maintained until the hydrocarbon is consumed; the reaction in the second combustion chamber is continued until the hydrogen is consumed. The fuel amounts are selected so that the hydrocarbon is consumed earlier than the hydrogen. The rocket engine, designed as a plug nozzle engine, for carrying out the method comprises a main body (1), at the lower end of which a central cone (2) (plug nozzle/spike) is connected, wherein the main body (1) is surrounded by a first annular combustion chamber (3.1), which has a first annular throat nozzle (6.1), and a second annular combustion chamber (3.2) having a second annular throat nozzle (6.2) is located in the central cone (2).
PCT/DE2011/075019 2010-03-05 2011-02-10 Method for operating a rocket engine and rocket engine WO2011107090A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010010265.2 2010-03-05
DE201010010265 DE102010010265B4 (en) 2010-03-05 2010-03-05 Method of operating a rocket engine and rocket engine

Publications (2)

Publication Number Publication Date
WO2011107090A2 WO2011107090A2 (en) 2011-09-09
WO2011107090A3 true WO2011107090A3 (en) 2012-02-02

Family

ID=44502898

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2011/075019 WO2011107090A2 (en) 2010-03-05 2011-02-10 Method for operating a rocket engine and rocket engine

Country Status (2)

Country Link
DE (1) DE102010010265B4 (en)
WO (1) WO2011107090A2 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102635464A (en) * 2012-04-05 2012-08-15 北京航空航天大学 Double-unit symmetric distribution linear plug nozzle cold-flow tester
CN102828851A (en) * 2012-08-16 2012-12-19 北京航空航天大学 Cold flow test device for scaling linear plug type spray pipe carrier
CN102817745B (en) * 2012-08-16 2014-06-18 北京航空航天大学 Low-cost and simple unit round-to-square plug nozzle test device
DE102021109484A1 (en) 2021-04-15 2022-10-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Rocket propulsion unit and combustor assembly

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3806064A (en) * 1968-10-03 1974-04-23 A Parilla Missile configurations, controls and utilization techniques
US5282359A (en) * 1991-10-17 1994-02-01 Chester Robert G Impulse jet engine
US20040079072A1 (en) * 2002-10-28 2004-04-29 James Shumate Method and apparatus for thrust augmentation for rocket nozzles
US20090211225A1 (en) * 2007-01-29 2009-08-27 Ghkn Engineering, Llc Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5572864A (en) * 1994-09-16 1996-11-12 Martin Marietta Corporation Solid-fuel, liquid oxidizer hybrid rocket turbopump auxiliary engine
US7565797B2 (en) * 2004-02-27 2009-07-28 Ghkn Engineering Llc Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles
US7155898B2 (en) 2004-04-13 2007-01-02 Aerojet-General Corporation Thrust vector control system for a plug nozzle rocket engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3806064A (en) * 1968-10-03 1974-04-23 A Parilla Missile configurations, controls and utilization techniques
US5282359A (en) * 1991-10-17 1994-02-01 Chester Robert G Impulse jet engine
US20040079072A1 (en) * 2002-10-28 2004-04-29 James Shumate Method and apparatus for thrust augmentation for rocket nozzles
US20090211225A1 (en) * 2007-01-29 2009-08-27 Ghkn Engineering, Llc Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles

Also Published As

Publication number Publication date
WO2011107090A2 (en) 2011-09-09
DE102010010265A1 (en) 2011-09-08
DE102010010265B4 (en) 2011-10-20

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