WO2021091613A3 - Staged combustion liquid rocket engine cycle with the turbopump unit and preburner integrated into the structure of the combustion chamber - Google Patents

Staged combustion liquid rocket engine cycle with the turbopump unit and preburner integrated into the structure of the combustion chamber Download PDF

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Publication number
WO2021091613A3
WO2021091613A3 PCT/US2020/049588 US2020049588W WO2021091613A3 WO 2021091613 A3 WO2021091613 A3 WO 2021091613A3 US 2020049588 W US2020049588 W US 2020049588W WO 2021091613 A3 WO2021091613 A3 WO 2021091613A3
Authority
WO
WIPO (PCT)
Prior art keywords
combustion chamber
preburner
integrated
main combustion
engine
Prior art date
Application number
PCT/US2020/049588
Other languages
French (fr)
Other versions
WO2021091613A2 (en
Inventor
Timothy Bulk
Christopher Hayes
Original Assignee
Special Aerospace Services, LLC
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 Special Aerospace Services, LLC filed Critical Special Aerospace Services, LLC
Publication of WO2021091613A2 publication Critical patent/WO2021091613A2/en
Publication of WO2021091613A3 publication Critical patent/WO2021091613A3/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
    • F02K9/972—Fluid cooling arrangements for 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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with prebumer and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber. Liquid propellants supplied to the engine are utilized for regenerative cooling of the combustion chamber and preburner, where the liquid propellants are gasified in cooling manifolds before injection into the preburner and main combustion chamber.
PCT/US2020/049588 2019-09-06 2020-09-05 Staged combustion liquid rocket engine cycle with the turbopump unit and preburner integrated into the structure of the combustion chamber WO2021091613A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201962897044P 2019-09-06 2019-09-06
US62/897,044 2019-09-06

Publications (2)

Publication Number Publication Date
WO2021091613A2 WO2021091613A2 (en) 2021-05-14
WO2021091613A3 true WO2021091613A3 (en) 2021-07-22

Family

ID=75848346

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2020/049588 WO2021091613A2 (en) 2019-09-06 2020-09-05 Staged combustion liquid rocket engine cycle with the turbopump unit and preburner integrated into the structure of the combustion chamber

Country Status (1)

Country Link
WO (1) WO2021091613A2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114060170B (en) * 2021-10-22 2023-05-23 陕西天回航天技术有限公司 Open staged combustion air-extracting circulation liquid rocket engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2190964A (en) * 1986-05-28 1987-12-02 Messerschmitt Boelkow Blohm Combined turbojet, ramjet, rocket propulsion unit
US6226980B1 (en) * 1999-01-21 2001-05-08 Otkrytoe Aktsionernoe Obschestvo Nauchno-Proizvodstvennoe Obiedinenie “Energomash” Imeni Akademika V.P. Glushko Liquid-propellant rocket engine with turbine gas afterburning
US20100024386A1 (en) * 2007-07-20 2010-02-04 Greene William D Gas-Generator Augmented Expander Cycle Rocket Engine
US20200400102A1 (en) * 2018-08-29 2020-12-24 Special Aerospace Services, LLC Staged combustion liquid rocket engine cycle with the turbopump unit and preburner integrated into the structure of the combustion chamber

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2190964A (en) * 1986-05-28 1987-12-02 Messerschmitt Boelkow Blohm Combined turbojet, ramjet, rocket propulsion unit
US6226980B1 (en) * 1999-01-21 2001-05-08 Otkrytoe Aktsionernoe Obschestvo Nauchno-Proizvodstvennoe Obiedinenie “Energomash” Imeni Akademika V.P. Glushko Liquid-propellant rocket engine with turbine gas afterburning
US20100024386A1 (en) * 2007-07-20 2010-02-04 Greene William D Gas-Generator Augmented Expander Cycle Rocket Engine
US20200400102A1 (en) * 2018-08-29 2020-12-24 Special Aerospace Services, LLC Staged combustion liquid rocket engine cycle with the turbopump unit and preburner integrated into the structure of the combustion chamber

Also Published As

Publication number Publication date
WO2021091613A2 (en) 2021-05-14

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