公开(公告)号：JPH09229025A

公开(公告)日：1997-09-02

申请号：JP6385496

申请日：1996-02-27

Applicant: NAT AEROSPACE LAB

Inventor： KARITA TAKESHI ,  ONO FUMIE ,  SAITO TOSHIHITO ,  WAKAMATSU YOSHIO ,  SUNAMI TETSUHARU

IPC: B64D33/04 ,  B64G1/00 ,  F02K9/62 ,  F02K9/97 ,  F15D1/08

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.