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Title:
METHOD AND DEVICE FOR RESTRAINING PRESSURE INCREASE AT WALL SURFACE BY SHOCK WAVE
Document Type and Number:
Japanese Patent JP3127241
Kind Code:
B2
Abstract:

PROBLEM TO BE SOLVED: To restrain pressure from increasing after reflection of shock wave by forming a secondary flow layer through application of injection or the like of secondary flow along a wall surface onto a part where the shock wave generated in a supersonic flow field reaches the wall surface.
SOLUTION: A rocket engine 1 is provided with a secondary flow injection port 3 formed circularly which injects a secondary flow along the upstream to the downstream wall surface so that a secondary flow layer is formed, at a part where shock wave 6 of nozzle skirt 2 is reflected. A downstrem stage is formed at a circumferential wall and the port 3 is made open at the stepped wall. In the Fig. numerals 5, 7 denote a combustion unit and swelling wave, respectively. The engine 1 is so constituted in this way. Pressure increase after the reaction is restrained and the shock wave 6 after the reaction can be weakened by making a secondary flow layer reflect the shock wave 6, the secondary flow layer being formed by injecting the secondary flow, especially subsonic gas, along the wall surface, to a part where the shock wave 6 is incident to the wall surface.


Inventors:
Takeshi Kanda
Fumie Ono
Toshihito Saito
Yoshio Wakamatsu
Tetsuji Sunami
Application Number:
JP6385496A
Publication Date:
January 22, 2001
Filing Date:
February 27, 1996
Export Citation:
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Assignee:
Director, Aerospace Research Institute, Science and Technology Agency
International Classes:
B64D33/04; B64G1/00; F02K9/62; F02K9/97; F15D1/08; (IPC1-7): F15D1/08; B64D33/04; B64G1/00; F02K9/62; F02K9/97
Domestic Patent References:
JP840397A
JP6280679A
JP5187320A
JP8219094A
JP6441651A
Other References:
「日本航空宇宙学会中部・関西支部合同秋期大会講演集」vol.32 p37−38「境界層中の音速線上での衝撃波の反射について」
Attorney, Agent or Firm:
Shigenobu Oshiro (2 outside)