Session: Research Posters

Paper Number: 113225

113225 - Squealer Tip Application and Aerodynamic Performance Prediction for Industrial Gas Turbine Axial Compressor 

Axial compressors are used in many industries. For axial compressor, aerodynamic performances are evaluated through efficiency, total pressure ratio, operation range, and stall margin. For axial compressor it is important to improve aerodynamic performance, because of operation range, stall margin, and efficiency. Many studies have been conducted to improve the aerodynamic performance of axial compressors by adjusting the aspect ratio of blades, changing the shape of blade like squealer tip, and applying plasma actuators. Giuseppe et al. studied the influence of squealer tip by adjusting the location of squealer tip; applying suction side squealer tip, pressure side squealer tip, and SuPr(Suction side at leading edge and pressure side at trailing edge). Ma et al. studied the effect of suction side squealer tip on the flow field by experimentally. In this study, the aerodynamic performance of the rotor and stator was investigated by adjusting the depth of squealer tip. The rotor and vane blades used in this study are the rotor and stator of an axial compressor of a power generation gas turbine. The study was divided into putting the squealer tip on the pressure side and the suction side of the blades, and the depth was adjusted to 1.25mm, 2.5mm, 3.75mm, and 5.0mm for the rotor, and 1.0mm, 2.0mm, 3.0mm, and 4.0mm for the stator. In the case of rotor, the aerodynamic performance will be compared through isentropic efficiency, total pressure ratio, and stall margin, and through observation of streamline, eddy viscosity, and vortex core region flow stability will be evaluated. For stator, aerodynamic performance will be compared through static pressure recovery and loss coefficient. Also, through streamline, eddy viscosity, and vortex core region observation flow stability will be evaluated. The study was conducted through numerical analysis using ANSYS CFX, for the turbulence model, shear stress transport model was used, and for meshing tool NUMECA Autogrid was used. Aerodynamic performance of the squealer tip applied to the pressure side and the suction side of each rotor and stator will be compared through isentropic efficiency, stall margin, loss coefficient, total pressure ratio, static pressure recovery and internal flow analysis, and the aerodynamic performance according to the depth of the squealer tip will also be compared through isentropic efficiency, stall margin, loss coefficient, total pressure ratio, static pressure recovery, and internal flow analysis. Through this study, it will suggest position of squealer tip and depth of squealer tip for rotor and stator through comparison of each case.

Presenting Author: Hyeon-Jun Yang Sungkyunkwan University

Presenting Author Biography: Hyeon-Jun Yang is a master student at Sungkyunkwan university in Republic of Korea.
His research interests are fluid engineering and turbomachinery.

Authors:

Hyeon-Jun Yang Sungkyunkwan University
Hyun-Su Kang Sungkyunkwan University
Youn-Jea Kim Sungkyunkwan University