Session: 13-11 Advanced Methods (II)

Paper Number: 124545

124545 - Effects of Combustor Residual Swirl and Hot Spot on Aerothermal Characteristics and Cooling Performance of Gas Turbine Blade 

The swirling flow and the hot spot generated in the aero-engine combustor have significant impacts on the downstream turbine components. This paper numerically investigates the influence of the residual swirl clocking position, direction and the hot spot on the aero-thermal characteristics of the turbine stage cascades and the cooling performance of the rotor blades. Computational results show that the hot spot slightly decreases the total pressure loss of the stage cascades. And the negative residual swirl increases the total pressure loss by about 3-5%. The aero-thermal characteristics and the cooling performance of the rotor blade are scarcely influenced by the residual swirl clocking positions. The hot spot decreases the mass flow of the blade tip holes by 2%, compared to the cases with uniform temperature inlet. The negative residual swirl makes the coolants at the pressure surface develop further downstream, reduces the differences in the leading edge holes mass flow at different spanwise positions and brings more intense heat transfer at the tip and better cooling performance at the blade surface. The flow capacity and the working performance of the turbine stage are also almost unaffected by the residual swirl and hot spot. This article presents a numerical method for turbine stage cascades with the residual swirl and the hot spot, analyzes the impact of combustor outflow conditions on turbine stage performance, and provides reference for CFD aided design of turbine aerodynamic and cooling configurations.

Presenting Author: Tianyi Sun Institute of Turbomachinery, Xi'an Jiaotong University

Presenting Author Biography: Tianyu Sun is a Ph. D. candidate of the Institute of Turbomachinery of Xi'an Jiaotong University in China.
His research topics is the aerothermal characteristics of turbine vane and blade in actual gas turbine operating flow conditions.

Authors:

Tianyi Sun Institute of Turbomachinery, Xi'an Jiaotong University
Zhiyu Li Institute of Turbomachinery, Xi'an Jiaotong Universitry
Zhigang Li Institute of Turbomachinery, Xi'an Jiaotong University
Jun Li Institute of Turbomachinery, Xi'an Jiaotong Univ.
Qingzong Xu Institute of Engineering Thermophysics, Chinese Academy of Sciences
Qiang Du Institute of Engineering Thermophysics, Chinese Academy of Sciences