RU2001133736A - DEVICE FOR REGULATING TRANSMISSION OF HEAT TO THE WALL OF THE NOZZLE OF ROCKET ENGINES WITH AN EXTENSION CYCLE - Google Patents

DEVICE FOR REGULATING TRANSMISSION OF HEAT TO THE WALL OF THE NOZZLE OF ROCKET ENGINES WITH AN EXTENSION CYCLE

Info

Publication number
RU2001133736A
RU2001133736A RU2001133736/06A RU2001133736A RU2001133736A RU 2001133736 A RU2001133736 A RU 2001133736A RU 2001133736/06 A RU2001133736/06 A RU 2001133736/06A RU 2001133736 A RU2001133736 A RU 2001133736A RU 2001133736 A RU2001133736 A RU 2001133736A
Authority
RU
Russia
Prior art keywords
nozzle
wall
rocket engines
heat
extension cycle
Prior art date
Application number
RU2001133736/06A
Other languages
Russian (ru)
Other versions
RU2264555C2 (en
Inventor
Ян ЛУНДГРЕН
Арне БОМАН
Матс ОЛОФССОН
Original Assignee
Вольво Аэро Корпорэйшн
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
Priority claimed from SE0000895A external-priority patent/SE516046C2/en
Application filed by Вольво Аэро Корпорэйшн filed Critical Вольво Аэро Корпорэйшн
Publication of RU2001133736A publication Critical patent/RU2001133736A/en
Application granted granted Critical
Publication of RU2264555C2 publication Critical patent/RU2264555C2/en

Links

Claims (3)

1. Устройство для усиления передачи тепла хладагенту на внутренней стороне стенки (1) сопла, снабженного каналами охлаждения, ракетных двигателей с циклом расширения, отличающееся тем, что для возмущения пограничного слоя у стенки сопла и, таким образом, усиления передачи тепла внутренняя сторона стенки сопла, обращенная к пламени, имеет специально подобранную повышенную шероховатость поверхности, достигающую такой степени, что она проникает сквозь вязкий подслой пограничного слоя у стенки сопла.1. Device for enhancing heat transfer to the refrigerant on the inner side of the nozzle wall (1) provided with cooling channels for rocket engines with an expansion cycle, characterized in that for perturbing the boundary layer near the nozzle wall and, thus, enhancing heat transfer, the inner side of the nozzle wall facing the flame has a specially selected increased surface roughness, reaching such an extent that it penetrates the viscous sublayer of the boundary layer near the nozzle wall. 2. Устройство по п.1, отличающееся тем, что шероховатость поверхности постепенно повышается от входного отверстия до выходного отверстия сопла.2. The device according to claim 1, characterized in that the surface roughness gradually increases from the inlet to the outlet of the nozzle. 3. Устройство по п.2, отличающееся тем, что шероховатость поверхности варьируется от около 0,15 мм на входе сопла до около 1 мм на выходе сопла.3. The device according to claim 2, characterized in that the surface roughness varies from about 0.15 mm at the nozzle inlet to about 1 mm at the nozzle exit.
RU2001133736/06A 2000-03-17 2001-03-16 Device to control transfer of heat to wall of nozzle of rocket engines with expansion cycle RU2264555C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE0000895-3 2000-03-17
SE0000895A SE516046C2 (en) 2000-03-17 2000-03-17 Device for controlling the heat transfer to the nozzle wall of rocket-type rocket motors

Publications (2)

Publication Number Publication Date
RU2001133736A true RU2001133736A (en) 2003-08-10
RU2264555C2 RU2264555C2 (en) 2005-11-20

Family

ID=20278854

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2001133736/06A RU2264555C2 (en) 2000-03-17 2001-03-16 Device to control transfer of heat to wall of nozzle of rocket engines with expansion cycle

Country Status (11)

Country Link
US (1) US6675571B2 (en)
EP (1) EP1179132B1 (en)
JP (1) JP4570310B2 (en)
CN (1) CN1178000C (en)
AU (1) AU4294201A (en)
DE (1) DE60108016T2 (en)
ES (1) ES2233617T3 (en)
RU (1) RU2264555C2 (en)
SE (1) SE516046C2 (en)
UA (1) UA70364C2 (en)
WO (1) WO2001069070A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE512942C2 (en) * 1998-10-02 2000-06-12 Volvo Aero Corp Procedure for manufacturing rocket engine outlet nozzles
DE10054333B4 (en) 2000-11-02 2006-11-30 Eads Space Transportation Gmbh Combustion chamber with increased heat input into a cooling device
US20080264372A1 (en) * 2007-03-19 2008-10-30 Sisk David B Two-stage ignition system

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2022517A1 (en) * 1970-05-08 1971-11-25 Messerschmitt Boelkow Blohm Rocket engine nozzle with boundary layer suction
JPS62261652A (en) * 1986-05-07 1987-11-13 Natl Space Dev Agency Japan<Nasda> Liquid rocket engine
US4799543A (en) * 1987-11-12 1989-01-24 Arthur H. Iversen Means for temperature control of heated surfaces
US5410874A (en) * 1990-11-19 1995-05-02 United Technologies Corporation Method and apparatus for increasing combustion chamber pressure in a high pressure expander cycle rocket engine
DE4116396C2 (en) * 1991-05-18 1996-04-25 Grace Gmbh Modified amorphous silica, process for their preparation and antiblocking agents
US5267437A (en) * 1991-05-23 1993-12-07 United Technologies Corporation Dual mode rocket engine
FR2691209B1 (en) 1992-05-18 1995-09-01 Europ Propulsion ENCLOSURE CONTAINING HOT GASES COOLED BY BREATHING, IN PARTICULAR A PROPULSIVE CHAMBER OF A ROCKET ENGINE, AND A MANUFACTURING METHOD THEREOF.
JPH07243351A (en) * 1994-03-03 1995-09-19 Mitsubishi Heavy Ind Ltd Fluid heat exchanger
US5832719A (en) * 1995-12-18 1998-11-10 United Technologies Corporation Rocket thrust chamber
DE10054333B4 (en) * 2000-11-02 2006-11-30 Eads Space Transportation Gmbh Combustion chamber with increased heat input into a cooling device

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