Session: 13-06 - Internal and External Flows

Paper Number: 126204

126204 - Effect of Film Hole Configuration on the Impingement-Film Composite Cooling Performance of a Simulated Turbine Blade Leading Edge 

Shaped holes have been extensively utilized in the film cooling design of turbine blade surface, with empirical evidence demonstrating their significant potential for optimizing the local film cooling performance. However, limited researches have focused on the effect of shaped holes on the composite cooling design of turbine blade leading edge. In this paper, adiabatic and conjugate heat transfer analyses were conducted to compare the flow resistance, heat transfer characteristics and cooling performance of the leading edge with different shaped holes. Specifically, eight configurations comprising seven types of film holes including cylindrical holes, expansion holes, and novel holes were numerically investigated, and the influence of coolant mass flowrate was also considered. The findings suggest that, compared to the referenced cylindrical hole, the amplified cylindrical hole exhibited a noticeable decrease in overall cooling effectiveness of the leading edge at low coolant mass flowrates; however, it also significantly enhanced the cooling performance at high coolant mass flowrates. Based on the cooling characteristics, the four expansion holes can be classified into two groups. One group exclusively comprises the laidback hole, which optimized the cooling performance of the leading edge across all coolant mass flowrates, but the improvement is somewhat limited. The other group consists of the fan hole, laidback cone hole and laidback fan hole, which demonstrated similar cooling characteristics to those observed in amplified cylindrical hole. The distinction lies in the fact that this group of expansion holes only marginally compromised the overall cooling effectiveness of the leading edge at low coolant mass flowrates, while the enhancements in cooling performance at high coolant mass flowrates are also slightly inferior to the amplified cylindrical hole. In comparison, both the novel holes exhibited exceptional cooling performance, particularly at high coolant mass flowrates, thereby offering a potential optimization of up to 40% in overall cooling effectiveness.

Presenting Author: Xinnan Chen Institute of Turbomachinery, Xi'an Jiaotong University

Presenting Author Biography: Mr. Xinnan Chen is a Ph. D. candidate of the Institute of Turbomachinery of Xi'an Jiaotong University in China.
His research topics is the aerothermal performance of turbine blade.

Authors:

Xinnan Chen Institute of Turbomachinery, Xi'an Jiaotong University
Bo Bai Institute of Turbomachinery, Xi'an Jiaotong University
Zhigang Li Institute of Turbomachinery, Xi'an Jiaotong University
Jun Li Institute of Turbomachinery, Xi'an Jiaotong Univ.