32th Congress of the International Council of the Aeronautical Sciences

03.1 - Aerodynamics – CFD Methods and Validation

DESIGN AND TEST OF A HIGH SLOPE ANGLE INTERMEDIATE DUCT BETWEEN LOW-PRESSURE COMPRESSOR AND HIGH-PRESSURE COMPRESSOR

H.-L. Jin¹, J. Zhang¹, J.-F. Wu¹, D.-B. Qiu¹, Y.-Q. Yin¹; ¹AECC Hunan Aviation Powerplant Research Institute, China

Flowpath and strut airfoil aerodynamic design were completed for a high slope angle intermediate duct between an axial-centrifugal low pressure and high pressure compressor. Three dimensional CFD computations were used to simulate the flow field of the intermediate duct. Flow test rig design, instrumentation and flow test were conducted to obtain the performance of the intermediate duct. The CFD results show that the average flow accelerated slightly from the inlet to the outlet of the intermediate. The flow along the hub firstly accelerates and then decelerates whereas the flow along the shroud firstly accelerates then keeps approximately uniform velocity. The corner separation between the end-wall and strut surface near trailing edge contributes the main loss in the intermediate duct. The test results indicate that the test value of total pressure recovery coefficient of the intermediate duct is 0.3 percent lower than the numerical result.


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