Session: 12-09: Film Cooling Optimization and Novel Design

Paper Number: 151362

Optimization of Effusion Cooling Pitch With Non-Zero Compound Angle 

Our previous work suggests that 45-degree could be the optimal compound angle for effusion cooling. However, the existing optimization of effusion cooling pitch was targeted for co-linear effusion cooling holes where the compound angle is zero. Therefore, the objective of this study is to experimentally determine the optimal pitch for effusion cooling holes when the compound angle is non-zero, with a focus on the 45° compound angle case. Special test coupons with effusion cooling holes far apart from adjacent ones were design and fabricated to evaluate the trajectories of individual effusion cooling jets and their evolutions along the trajectories at a range of blowing ratios (BR). The evolutions of individual effusion cooling jets are used to infer the optimal separations of adjacent effusion cooling holes both in the streamwise and spanwise directions. In addition, the study was designed to investigate effects of upstream jets as well as changing boundary layer thickness on the
evolutions of effusion jets are also conducted to decide if a universal pitch is adequate. It was found that upstream jets have strong influences on effusion jet evolution while the impact of boundary layer thickness remains insignificant. The evolutions of effusion jets are experimentally inferred from adiabatic film cooling effectiveness (AFE) measurements using a binary Pressure Sensitive Paint (PSP).

Presenting Author: Zekai Hong Aerospace Research Center, National Research Council of Canada

Presenting Author Biography: Dr. Zekai Hong is a Senior Research Officer at the Aerospace Research Centre of the National Research Council of Canada (NRC) and an Adjunct Professor in the Department of Mechanical Engineering at the University of Ottawa. Dr. Hong's research expertise spans a wide range of areas, including combustion, laser diagnostics, chemical kinetics, combustion instability, and shock waves. Dr. Hong’s recent work focuses on thermal management for gas turbine engines, with particular emphasis on effusion and transpiration cooling techniques.

Authors:

Boyuan Song Aerospace Research Center, National Research Council of Canada
Juchan Son University of Ottawa
Yeongmin Pyo University of Ottawa
Zekai Hong Aerospace Research Center, National Research Council of Canada