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http://dx.doi.org/10.6108/KSPE.2013.17.1.097

Prestudy on Expendable Turbine Engine for High-Speed Vehicle  

Kim, YouIl (국방과학연구소 4기술연구본부 미래추진기술센터)
Hwang, KiYoung (국방과학연구소 4기술연구본부 미래추진기술센터)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.17, no.1, 2013 , pp. 97-102 More about this Journal
Abstract
A prestudy on expendable turbine engine for high-speed vehicle was conducted. After two possible mission profiles were established to decide the engine requirements, design point analysis was performed with the values of design parameter which were obtained from similar class engines, references, etc. The results showed that specific net thrust and specific fuel consumption with turbine inlet temperature of 3,600 R are 2,599.4 ft/s and 1.483 lb/(lb*h) respectively at the flight condition of sea level, Mach 1.2. It was also found that major design parameters for determining maximum net thrust were turbine inlet temperature for low supersonic and transonic flight speed and compressor exit temperature for high supersonic flight speed from the results of performance analysis on the two possible mission profiles. In addition, simple turbojet engine with an axial compressor, a straight annular combustor, an one stage axial turbine and a fixed throat area converge-diverge exhaust nozzle was proposed as the configuration of simple low cost lightweight turbine engine.
Keywords
Expendable Turbine Engine; High-speed Vehicle; Mission Profile; Design Point; Turbine Inlet Temperature;
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