Aerodynamic And Cooling Structure Design Of Air Turbine For High-speed Aircraft

In high-speed aircraft, the small air turbine pump is an important auxiliaryequipment. It uses high-pressure air which is extracted from the inlet to drive a turbineto do work, then drive the pump. Low-pressure oil became high-pressure oil by thepump. High pressure oil can drive the control original or be injected into the combustionchamber. When the vehicle is flying at high speed, such as Mach7. Acquired the airfrom inlet will have a higher stagnation temperature, air turbine is in a temperature ofworking environment. The cooling must be considered in Aerodynamic design of theturbine. Because the air turbine is high load and small size, this brings a certain degreeof difficulty to the layout of the cooling structure. Therefore, in the limited space designcan afford a larger load and quickly achieve energy conversion units will be veryimportant.In this paper, we select Laval nozzle instead of stators single-stage turbine. Aone-dimensional design is conducted according to the design parameter, and this resultis determined by a one-dimensional detailed parameters. In order to increase the bladeheight, portion of the intake is used. According to the results of a one-dimensionaldesign of three-dimensional is designed. We conducted a three-dimensional geometricmodel of the establishment and meshed them with various related software.Aerodynamic program is to simulate. The results show that from the overallperformance parameters, aerodynamic program achieved the initial target. Rotationalspeed is48000r/min, mass flow is0.1818kg/s, a power output of about88kW isachieved. Meanwhile aerodynamic program gives the temperature field which hasplayed a guiding role on the subsequent cooling structure design.In the cooling structure of the design process, making full use of the space reservedfor early aerodynamic program, we conducted a cooling structure of the nozzle design.According to the distribution of temperature field of aerodynamic program, I conducteda targeted cooling design. Conjugate heat transfer simulation the entire program. TheCooling working fluid use C10H22. Analysis the results of numerical, it showed that thetemperature of the nozzle wall is effectively reduced, while the rotor blades are alsosignificantly lower temperature. They are within the scope of the material can withstand.Increase the cooling structure. For the performance of the entire unit is small, the outputpower flow and basically did not change significantly, This shows that the design ofeffective and feasible.