THE INVESTIGATION OF TURBINE AND EXHAUST INTERACTIONS IN ASYMMETRIC FLOWS Part 1 ― Blade-Row Models Applied

摘要

Part 1 of this paper describes the blade-row models applied to the asymmetric flow field coupling between turbine and exhaust system. Numerical actuator disc is applied to represent a turbine blade row around the whole annulus and flow properties across the disc can jump to achieve required flow turning and entropy rise. The derivation of disc boundary conditions and the implementation in CFD solvers are described in detail. Validation of the actuator disc model and sample application of the present numerical approach are presented.