This paper quantifies the changes in turbine performance due to manufacturing tolerances and profile degradation of the blade-tip region during engine operation. An extensive numerical study was conducted on a modern high-pressure turbine rotor, operating at high Reynolds and high subsonic outlet conditions. The stochastic collocation method was used to investigate the effects of the geometrical variability of a single squealer tip design. The variation of three geometrical characteristics was investigated: tip clearance size, squealer depth, and rim corner radius. Three-dimensional Reynolds-averaged Navier–Stokes simulations were performed to predict the aerodynamic and heat transfer characteristics. The results highlight the influence of the combined geometrical variability on the overtip flow structures, heat transfer signatures, loss development, and downstream flow characteristics. This study measures the robustness of squealer tip designs to changes in its geometry and demonstrates the necessity of anticipating the consequences of these unavoidable tip geometry variabilities in an early development stage of the turbine design optimization.
Performance Robustness of Turbine Squealer Tip Designs Due to Manufacturing and Engine Operation
Journal of Propulsion and Power ; 33 , 3 ; 740-749
2017-03-29
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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