A study of engine simulation methods for operational flight trainers, Volume 2
Analog Computer Laboratory, Institute of Science and Technology, Unmiversity of Michigan - Fancher, P. S.
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List of Figures
3 Conclusions and Recommendations
8 other sections not shown
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adiabatic process ANALOG COMPUTER assumed axial compressor axial velocity Blade angle blade row burner calculated component compressor equations compressor map compressor rotor compressor stator constant continuity equation derivation divergent duct element energy equation engine control system engine simulation enthalpy equation between stations equation for Figure Equations 80 equations which describe error tolerance exhaust nozzle fictitious duct Figure 12 force-balance equation function function-factoring process gas flow gas turbine engine gas velocity Guide Vane inlet diffuser inlet duct inlet guide input isentropic process Mach number mass flow rates mathematical analysis MERGING FLOW momentum equation operation output parabolas parameters perfect gas quadratic equation rearranging rotor blade rotor-blade row shock waves shown in Figure solution solving for Pg stator-blade row subsonic Substituting supersonic tan2B tangential component tangential force tangential velocity theoretical thrust torque total temperatures turbine rotor written