The Structural Design,Simulation and Experimental Verification of Auxiliary Ejection Cold Edge Air Source at Turbine Outlet in Aircraft Fuel Inerting System
Aircraft fuel inerting system is generally composed of entrain subsystem,air conditioning subsystem and air separation and distribution subsystem.In order to improve the efficiency of downstream air separation,the air conditioning subsystem generally uses turbochargers(also useful electric compressors)to improve the air pressure before the separation film.From the perspective of improving the utilization rate of the bleed air capacity of the entire inerting system,air at the turbine outlet with lower relative pressure and temperature is generally used as a cold source to cool the bleed air at the hot edge.However,when the cold edge air of the system directly comes from outside air,the temperature of the air at the turbine outlet may be higher than that of the air at the cold edge.In this case,the air at the turbine outlet cannot be discharged into the cold edge inlet of the system as a cold source.It is often discharged into the cold edge outlet of the system to play the auxiliary ejection function of the cold edge air source of the system.On the one hand,the ejector structure will affect the performance of the turbocharger itself,and on the other hand,it will affect the ejector performance.Due to the large error in the theoretical calculation of ejection performance,the methods of simulation and physical test are generally adopted in the design of ejection structure.
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