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research-article

Experimental and Numerical Investigation of the Flow in a Trailing Edge Ribbed Internal Cooling Passage

[+] Author and Article Information
Seungchan Baek

Department of Mechanical & Aerospace Engineering, Seoul National University, Seoul, Republic of Korea
dkjdjdj195@snu.ac.kr

Sangjoon Lee

Department of Mechanical & Aerospace Engineering, Seoul National University, Seoul, Republic of Korea
jun9303@snu.ac.kr

Wontae Hwang

Institute of Advanced, Machines and Design, Department of Mechanical & Aerospace Engineering, Seoul National University, Seoul, Republic of Korea
wthwang@snu.ac.kr

Jung Shin Park

Thermal and Fluid Research Team, Doosan Heavy Industries & Co., LTD, Yongin, Republic of Korea
jungshin.park@doosan.com

1Corresponding author.

ASME doi:10.1115/1.4041868 History: Received September 22, 2018; Revised October 24, 2018

Abstract

The flow field in a ribbed triangular channel representing the trailing edge internal cooling passage of a gas turbine high pressure turbine blade is investigated via Magnetic Resonance Velocimetry (MRV) and Large Eddy Simulation (LES). Results are compared to a baseline channel with no ribs. LES predictions of the mean velocity fields are validated by the MRV results. In the case of the baseline triangular channel with no ribs, the mean flow and turbulence level at the sharp corner are small, which would correspond to poor heat transfer in an actual trailing edge. For the staggered ribbed channel, turbulent mixing is enhanced, and flow velocity and turbulence intensity at the sharp edge increase. This is due to secondary flow induced by the ribs moving toward the sharp edge in the center of the channel. This effect is expected to enhance internal convective heat transfer for the turbine blade trailing edge.

Copyright (c) 2018 by ASME
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