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.
The Investigation of Turbine and Exhaust Interactions in Asymmetric Flows— Blade-Row Models Applied
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Amsterdam, The Netherlands, June 3–6, 2002. Manuscript received by the IGTI, revised manuscript received October 2, 2001. Paper No. 2002-GT-30342. Review Chair: E. Benvenuti.
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Liu, J. J., and Hynes, T. P. (January 23, 2003). "The Investigation of Turbine and Exhaust Interactions in Asymmetric Flows— Blade-Row Models Applied ." ASME. J. Turbomach. January 2003; 125(1): 121–127. https://doi.org/10.1115/1.1516812
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