Analysis of a Topping-cycle, Aircraft, Gas-turbine-engine System which Uses Cryogenic FuelNational Aeronautics and Space Administration, Scientific and Technical Information Branch, 1984 - Aircraft gas-turbines - 20 pages |
Common terms and phrases
analysis area per unit assumed baseline engine baseline turboshaft engine bleed air Brake specific fuel bsfc burner B1 burner temperature combustion products compressor pressure ratio computed consumption as function cryogenic fuel cycle analysis cycle conditions cycle operating conditions design point value efficiency and brake engine system weights engine thermal efficiency engine weight enthalpy equation estimated finned tubes flow area flow rate flow station fuel-rich Gtube header thickness heat ex heat exchanger core heat exchanger pressure heat exchangers HX-1 heat release heat transfer coefficient hydraulic diameter hydrogen flow hydrogen fuel kg lbm kg/hr kg/kW-hr lbm/hr liquid hydrogen Mach main turboshaft engine mixture overall precooling pressure drop pressure loss psia rate of heat reference turboshaft engine Reynolds number shaft power output shell side side of heat specific fuel consumption surface area thermodynamic performance Topping cycle engine topping loop turbine total engine Turbine T2 turbopump values of burner