Session: 12-02 Film Cooled Rotor Blades

Paper Number: 82189

82189 - Effect of Location and Rotational Reynolds Number on Film Cooling of Rotating Blade Pressure Side 

The film cooling performance on the pressure side of turbine blades with a single-row film holes is experimentally investigated. Three blade models with different locations (x/S = 10%, 29%, and 48%) of the pressure-side hole row are studied at three rotating speeds (400 rpm, 600 rpm, and 800 rpm) corresponding to the rotational Reynolds number of 3.6 × 10⁵, 5.4 × 10⁵, and 7.2 × 10⁵. The film cooling effectiveness (η) is measured for each test by using the pressure sensitive paint (PSP) technique at six blowing ratios (M = 0.50, 0.75, 1.00, 1.25, 1.50, and 2.00). The results indicate that the film cooling performance varies considerably at different locations on the pressure side due to the influence of mainstream. Upstream of the pressure side, the film cooling performance is poor, with the film trajectories deflecting mainly upward. Downstream of the pressure side, the film cooling effectiveness is higher, with the film trajectories deflecting upward and downward. Simultaneously, the downstream film trajectories are longer than the upstream film trajectories, and are more prone to detach from the wall at high blowing ratios. When at low blowing ratios, no coolant is ejected near the hub due to insufficient internal pressure of R1 and R2. Moreover, with the increase of rotational Reynolds number, the film cooling effectiveness slightly improves.

Presenting Author: Long Meng Beihang University

Presenting Author Biography: Long Meng, male, born in 1991, is a Ph.D. student of Beihang University, class of 2019, majoring in engineering thermal physics. His main research interests are the cooling of turbine blade. Currently, he is mainly engaged in the research of film cooling on the pressure side of rotating blades.

Authors:

Long Meng Beihang University
Haiwang Li Beihang University
Gang Xie Beihang University
Zhiyu Zhou Beihang University