국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Effect of Film Cooling/Regenerative Cooling on Scramjet Engine Performances
저자	Fumiei ONO, Takeshi KANDA, Goro MASUYA, Toshihito SAITO, Yoshio WAKAMATSU
Keyword	Scramjet engine; Film cooling; Regenerative cooling; Supersonic flow; Mixing layer; Turbulent boundary layer; Propellant feed system; Gas generator cycle
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr01242.pdf?id=NALTR0001242
보고서번호	NAL TR-1242
발행년도	1994.7
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	Film cooling was modeled to allow performance prediction of scramjet engine design.The model was based on experimental results of compressible mixing layers for the vicinity of the injection slot,and on analytical results of the turbulent boundary layer in the region far from the slot.The film cooling model was integrated to a quasi one-dimensional scramjet performance prediction model.In the engine employing a combination of film cooling and regenerative cooling,coolant flow rate of the engine slightly exceeded the stoichiometric flow rate,even at high flight Mach numbers,and had the best specific impulse and system pressure performances.,These advantages were achieved by increasing the volume flow rate and decreasing the velocity difference between the main flow and the coolant,both due to an incrase in the film coolant temperature.The effective cooling system with a combination of film cooling and regenerative cooling was also advantageous in that excess cooling of the engine wall could be avoided.The combination of film cooling and regenerative cooling was also effective from the viewpoint of the propellant feed system.The turbine exhaust gas was suitable for the coolant of film cooling.