In order to guide the design of the engine air system, a comprehensive CFD analysis has been carried out on the flow in a corotation radial inflow cavity between the turbine disk and the coverplate of a gas turbine engine. Nine different flow cases have been studied. The rotational Reynolds number ranges from 0.79×106 to 3.14×106, and the through flow number ranges from 7×103 to 194×103, which covers the whole envelope of engine operating conditions. The CFD results revealed the complicated source-sink flow physics, and provided detailed variation of pressure, temperature, swirl factor and moment coefficient, etc., which serve as the basis for engine air system modelling. It has been shown that the flow behaves more and more like a free vortex with increasing mass flow, but more and more like a forced vortex with increasing rotational speed. For a good engine air system design, it is preferred to introduce the air into the cavity in such a way that the inlet swirl factor is independent of the mass flow.
- International Gas Turbine Institute
Flow in a Corotation Radial Inflow Cavity Between Turbine Disk and Coverplate
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Liu, X. "Flow in a Corotation Radial Inflow Cavity Between Turbine Disk and Coverplate." Proceedings of the ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration. Orlando, Florida, USA. June 2–5, 1997. V003T09A024. ASME. https://doi.org/10.1115/97-GT-137
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