Numerical Study on the Biomimetic Trailing Edge of a Turbine Blade Under a Wide Range of Outlet Mach Numbers

Abstract

This study was carried out to investigate the loss mechanism of a blade with a harbor seal whisker structure on the trailing edge under different Mach numbers. The loss of high-pressure turbine blades with four different trailing edge geometries, including a prototype, an elliptical trailing edge (ETE), a sinusoidal trailing edge (STE), and a biomimetic trailing edge (BTE) at Mach numbers of 0.38–1.21 is studied. The delayed detached-eddy simulation method is used to predict the detailed flow of the four cascades. The result shows that, when the Mach number is less than 0.9, the BTE can effectively reduce the energy loss coefficient compared with the other three cases. As the Mach number increases, the three-dimensional characteristics of the wake behind the BTE weaken. The energy loss coefficient of the blade with the BTE is close to that of the blade with the ETE and STE when the Mach number is greater than 0.9. Besides this, by controlling the wake, the BTE can effectively suppress the dynamic movement of shock waves in the cascade at high Mach numbers.

Numerical investigation of elliptical trailing edge on cascade loss of transonic turbine airfoils

“…However, there are few studies on transonic wake and shock waves. Wen et al [9] studied the loss of high-pressure turbine blades with four different trailing edge geometries and proposed a biomimetic trailing edge to control the wake and shock waves. Zhou et al [10] gave a detailed flow picture of the TE shock wave system and emphasized the important role of the TE separation shock wave.…”

Film-cooling hole optimization and experimental validation considering the lateral pressure gradient

“…Among various turbine structures, the endwall of turbine blades suffers from high thermal load, and the flow environment is extremely complex (as depicted in Wang et al (1997)), making the analysis of cooling performance more challenging. The endwall secondary flow and lateral pressure gradient have been studied in Friedrichs et al (1996), and it has been shown that the cooling jets are affected significantly by the secondary flow structures and pressure gradients (Wen et al, 2021;Ding et al, 2022). The film cooling performance is further studied with the rotational endwall environment in Barigozzi et al (2006) and Suryanarayanan et al (2010).…”