Abstract
A 3-D unsteady RANS simulation of the flow field of a supersonic impulse turbine stage designed for a rocket engine is presented using a commercial CFD software package. The nozzle employs a partial admission design, with 45% of nozzle flow passage blocked, which creates a complex supersonic flow field in the nozzle-rotor interface. The numerical results revealed a highly 3 dimensional feature in the interface region, exihibiting a large separated flow along the hub surface. The acceleration and deceleration of the circumferential flow as it enters and exits the blocked section of the nozzle also have a significant spanwise variation, which of course was not seen in the earlier 2-D studies.
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