Over the past few years, interest in manned hypersonic flight has increased significantly. The disadvantages of a three mode propulsion system (turbojet/ramjet/scramjet) are the complexity, weight, and costs which accompany it. Inlet and exhaust geometry variations required for proper integration play a major role. The utilization is explored of the turbine engine for aircraft propulsion up to the scramjet transition. Examination of the uninstalled cycle performance is presented as well as an assessment of installed engine operation in a hydrogen fueled aircraft. Both non-afterburning and afterburning turbine engines are compared to turboramjet and air turboramjet (ATR) engines for a Mach 5 long duration cruise mission along with a pure acceleration mission, i.e., the turbomachinery is used to accelerate the vehicle to a Mach number where the scramjet can take over. From this assessment, a baseline engine configuration/cycle is defined for feasibility studies and critical technology identification. A discussion of the feasibility of the perferred concept from an engine component by component standpoint is provided as well as a discussion of technology risk compared to the state of the art.
Turbojet Potential for Hypersonic Flight
1990
11 pages
Report
Keine Angabe
Englisch
Jet & Gas Turbine Engines , Aircraft , Manned Spacecraft , Hypersonic flight , Propulsion system performance , Turbojet engines , Afterburning , Low thrust propulsion , Propulsion system configurations , Engine parts , Hydrogen fuels , Hypersonic speed , Mach number , Supersonic combustion ramjet engines , Turboramjet engines
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