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research-article

Aerodynamic Optimization of a Winglet-Shroud Tip Geometry For a Linear Turbine Cascade

[+] Author and Article Information
Zhang Min

Key Laboratory of Ocean Energy Utilization and Energy Conservation of Ministry of Education, School of energy and power engineering, Dalian University of Technology, No.2 Linggong Road, Ganjingzi District, Dalian 116024, China
modest_zm@126.com

Liu Yan

Key Laboratory of Ocean Energy Utilization and Energy Conservation of Ministry of Education, School of energy and power engineering, Dalian University of Technology, No.2 Linggong Road, Ganjingzi District, Dalian 116024, China
yanliu@dlut.edu.cn

Zhang Tianlong

School of energy and power engineering, Dalian University of Technology, No.2 Linggong Road, Ganjingzi District, Dalian 116024, China
zhtl369@163.com

Zhang Mengchao

School of energy and power engineering, Dalian University of Technology, No.2 Linggong Road, Ganjingzi District, Dalian 116024, China
mczdlut@163.com

Ying He

School of energy and power engineering, Dalian University of Technology, No.2 Linggong Road, Ganjingzi District, Dalian 116024, China
heying@dlut.edu.cn

1Corresponding author.

ASME doi:10.1115/1.4036647 History: Received June 23, 2016; Revised March 29, 2017

Abstract

This paper presents a continued study on a previously investigated winglet-shroud (WS) geometry for a linear turbine cascade. A plain tip and a full shroud tip are experimentally and numerically examined as the datum cases. Various width (w) of double-side winglets (DSW) involving 3%, 5%, 7% and 9% of the blade pitch (p) is numerically investigated. It is observed that the DSW cases do not alter the flow fields including the separation bubble and reattachment flow within the tip gap region, even for the case with the broadest width (w/p = 9%). Meanwhile, the horse-shoe vortex near the casing is not generated even for the case with the smallest width (w/p=3%). Larger width of the DSW geometry is indeed able to improve the aerodynamic performance, but in a slight degree. With the w/p increasing from 3% to 9%, the mass-averaged total pressure loss coefficient over an exit plane is just reduced by 2.61%. Therefore, a favorable width of w/p=5% is chosen to design the WS structure. Based on this, three locations of the partial shroud (linkage segment) are devised, which are located near the leading edge, the middle and close to the trailing edge respectively. Results illustrate that all three WS cases have advantages in lessening the aerodynamic loss over the DSW arrangement, but with the linkage segment located in the middle having optimal effect. This conclusion verifies the feasibility of the previously studied WS configuration.

Copyright (c) 2017 by ASME
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