This paper describes the blade-row models applied to the asymmetric flow-field coupling between turbine and exhaust system. Numerical actuator disk is applied to represent a turbine blade row around the whole annulus and flow properties across the disk can jump to achieve required flow turning and entropy rise. The derivation of disk boundary conditions and the implementation in CFD solvers are described in detail. Validation of the actuator disk model and sample application of the present numerical approach are presented.

Issue Section:
Technical Papers
Keywords:
gas turbines, steam turbines, flow simulation, actuators, pressure
Topics:
Actuators, Boundary-value problems, Disks, Flow (Dynamics), Blades, Turbines, Exhaust systems
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Copyright © 2003
 by ASME
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