Guoqiang Yue

TL;DR: Aero-thermal optimizations on multi-rows film cooling of a realistic marine high pressure turbine vane are performed in this article, and the results show that the film cooling effectiveness of multi-objective optimization is increased by 11.4%, and average temperature of the blade surface is reduced by 75 K.

TL;DR: In this paper, the authors investigated the sensitivity of aerothermal performance of transonic tip flows to tip clearances in a RT27a turbine cascade, and they used the ANSYS CFX 14.5 numerical prediction code, adopting the SST k-ω turbulence model.

TL;DR: In this article, the effect of various parameters including mist concentration, mist diameter, different particle wall interactions conditions, and different forces on the improvement of cooling performance is investigated in a numerical simulation.

TL;DR: In this article, a multi-step optimization of leading edge and downstream film cooling configurations on a high pressure turbine vane is conducted using full three-dimensional optimization method, which consists of parametric modeling, automatic mesh generation, the CFD numerical calculation and the optimization strategy.

TL;DR: In this article, three different kinds of coolant chamber configuration for film cooling are proposed to develop the swirling coolant flow at blowing ratios ranging from 0.5 to 2.0.