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research-article

Investigation on the Shock Control Using Grooved Surface in a Linear Turbine Nozzle

[+] Author and Article Information
Xinguo Lei

School of Mechanical Engineering, Beijing Institute of Technology, Beijing, CHINA, 100081
lei_xinguo@126.com

Mingxu QI

School of Mechanical Engineering, Beijing Institute of Technology, Beijing, CHINA, 100081
qimx@bit.edu.cn

Harold Sun

Research & Innovation Center, Ford Motor Company, Dearborn, MI, USA, 48124
harold.sun@sbcglobal.net

Liangjun Hu

Research & Innovation Center, Ford Motor Company, Dearborn, MI, USA, 48124
lhu4@ford.com

1Corresponding author.

ASME doi:10.1115/1.4037860 History: Received August 19, 2017; Revised August 25, 2017

Abstract

Radial flow Variable Nozzle Turbine (VNT) enables better matching between a turbocharger and engine, and can improve the engine performance as well as decrease the engine emissions, especially when the engine works at low-end operation points. With increased nozzle loading, stronger shock wave and clearance leakage flow may be generated and consequently introduces strong rotor-stator interaction between turbine nozzle and rotor, which is a key concern of rotor HCF failure. With the purpose of developing a low shock wave intensity turbine nozzle, the influence of grooved vane on the shock wave characteristics is investigated in present paper. A Schlieren visualization experiment was first carried out on a linear turbine nozzle with smooth surface and the behavior of the shock wave was studied. Numerical simulations were also performed on the turbine nozzle. Guided by the visualization and numerical simulation, grooves were designed on the nozzle surface where the shock wave was originated and numerical simulations were performed to investigate the influence of grooves on the shock wave characteristics. Results indicate that for a smooth nozzle configuration, the intensity of the shock wave increases as the expansion ratios increase, while the onset position is shifted downstream to the nozzle trailing edge. For a nozzle configuration with grooved vane, the position of the shock wave onset is shifted upstream compared to the one with a smooth surface configuration, and the intensity of the shock wave as well as the static pressure distortion at the nozzle vane exit plane are significantly depressed.

Copyright (c) 2017 by ASME
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