Research Papers

Recent Advances in Turbine Heat Transfer—With A View of Transition to Coal-Gas Based Systems

[+] Author and Article Information
Minking K. Chyu

Leighton and Mary Orr Chair Professor and Chairman Department of Mechanical Engineering and Materials Science,  University of Pittsburgh, Pittsburgh, PA 15261mkchyu@pitt.edu

J. Heat Transfer 134(3), 031006 (Jan 11, 2012) (9 pages) doi:10.1115/1.4005148 History: Received August 20, 2010; Revised February 28, 2011; Accepted September 08, 2011; Published January 11, 2012; Online January 11, 2012

The performance goal of modern gas turbine engines, both land-base and air-breathing engines, can be achieved by increasing the turbine inlet temperature (TIT). The level of TIT in the near future can reach as high as 1700 °C for utility turbines and over 1900 °C for advanced military engines. To ensure the turbine airfoil component integrity operated under such a condition, advanced cooling capacity by both external and internal means was necessary to remove the excessive heat load from the turbine airfoil. This paper discusses state-of-the-art airfoil cooling technologies along with the associated thermal transport issues. Discussion is given based on five key regions on and around an airfoil: leading edge, main body, trailing edge, endwall, and near-tip. Potential implications and challenges of near-term developments in coal-gas based turbines on the cooling technologies are identified. A literature survey focusing primarily on the past 4–5years since the last International Heat Transfer Conference has also been performed.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Regions of turbine airfoil heat transfer and surrounding flow characteristics (from Simoneau and Simon, 1993 [5])

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Figure 2

Evolution of film cooling technology (from Bunker, 2009 [17])

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Figure 3

Internal cooling passage in serpentine form

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Figure 4

Double-wall cooling with pin-fins—European patent specification, EP 1 617 043 B1, 2008

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Figure 5

Local heat transfer coefficient (W/m2 K) and CFD simulated streakline in a double-wall cooling channel, channel’s Reynolds number = 8,000

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Figure 6

Turbine airfoil trailing edge with pressure-side cutback

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Figure 7

Secondary flows in gas path of axial turbine [39-40]




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