Analysis of a topping-cycle, aircraft, gas-turbine-engine system which uses cryogenic fuel
George E. Turney, Laurence H. Fishbach, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1984 - Technology & Engineering - 20 pages
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area per unit assumed Aube baseline engine baseline turboshaft engine brake specific fuel bsfc burner Bl burner temperature combustion products Compressor C2 compressor pressure ratio computed consumption as function cryogenic fuel cycle analysis cycle conditions design point value efficiency and brake engine system weights engine thermal efficiency engine weight enthalpy entropy equation estimated finned tubes flow area flow rate flow station fuel-rich heat ex heat exchanger core heat exchanger pressure heat exchangers HX-1 heat transfer coefficient hydraulic diameter hydrogen flow hydrogen fuel kg lbm lbm/hr Lewis Research Center liquid hydrogen Mach main compressor mixture overall precooling pressure drop pressure loss psia rate of heat reference turboshaft engine shaft power delivered shaft power output shell side side of heat specific fuel consumption surface area temperature of 1667 thermodynamic performance topping cycle engine topping loop turbine topping-cycle engine performance total engine Turbine Tl turbopump values of burner