Performance and Operating Characteristics of a Turbine Engine Propulsion Simulator at Simulated Flight Conditions
Final rept. 8 Apr-18 Jun 1975
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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An investigation was conducted on an engine propulsion simulator SN 0022 to determine the compressor operating maps at compressor inlet pressures of 7, 12, and 16 psia at an inlet total temperature of 120 deg F with both dry and reheat mixernozzle configurations, to determine the dry and reheat nozzle entrance pressure and temperature distortion with the anti-distortion screens installed upstream of the nozzle, and to determine nozzle thrust and nozzle flow coefficients at simulated altitudeMach number flight conditions of 12,7000.6, 21,4000.8, 24,8000.9, 34,2001.2, and 43,7001.5 with both mixernozzle configurations. Compressor maps and nozzle performance are presented and compared with the predicted values. Nozzle entrance pressure and temperature distortions are presented. In addition, simulator operational experiences are discussed.
- Jet and Gas Turbine Engines