The present study aims to simulate the unsteady flow structure induced by the relative motions of vanes and rotors in a transonic turbine stage with different spacings. Time‐dependent, two‐dimensional Reynolds‐averaged Navier‐Stokes equations were solved by a computer code based on the control volume method. To identify the turbulence model effect, three different two‐equation turbulence models (standard k‐ϵ, RNG k‐ϵ and k‐ω) were incorporated in the present code. The vane‐rotor spacings, 15 and 25 mm were varied to observe the characteristics of the rotating flow field. The predictions of surface pressure coefficient distribution on vanes and rotors are in good agreement with the experimental data from a short‐duration shock tunnel. Among the tested turbulence models the RNG k‐ϵ turbulence model seems most suitable to the current numerical method and grid system. The flow fields, including the development of boundary layer flow, the location of the separation bubble, the interaction of the wake with following rotor, even the flow structure multi‐shocks between vanes and rotors were well simulated in the present work. Unsteady results also showed that both the total pressure loss and turbine adiabatic efficiency were little influenced by spacings varying from 15 mm to 25 mm.
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Miao et al. (2004) studied this question.
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