COMPARISON OF PRESSURE-LOSS CHARACTERISTICS OF SEVERALnTAIL-CONE AIR-INDUCTION SYSTEMS FOR AIR-COOLED GAS-TURBINE ROTORS

摘要

Three scale models and a full-scale configuration of systems for ducting cooling air through a turbojet engine tail cone to a cooled turbine rotor were investigated in order to determine the pressure-loss characteristics of such systems and to evaluate the effects of these pressure losses on the performance of an air-cooled turbojet engine. The full-scale system and one similar model system were designed primarily on the basis of mechanical simplicity with no regard for the totalpressure losses; the second model was designed to reduce the extreme turbulence of the flow in the discharge duct, which should reduce the pressure losses and improve the reliability of pressure measurements at the entrance to the cooled turbine rotor; and the third made a substantial sacrifice of mechanical simplicity in order to reduce the over-all total-pressure losses.