Research Papers

Recent Advances of Internal Cooling Techniques for Gas Turbine Airfoils

[+] Author and Article Information
Minking K. Chyu

e-mail: mkchyu@pitt.edu

Sin Chien Siw

Department of Mechanical Engineering and Materials Science,
University of Pittsburgh,
Pittsburgh, PA 15261

1Corresponding author.

Manuscript received November 5, 2012; final manuscript received February 5, 2013; published online May 17, 2013. Assoc. Editor: Srinath V. Ekkad.

J. Thermal Sci. Eng. Appl 5(2), 021008 (May 17, 2013) (12 pages) Paper No: TSEA-12-1197; doi: 10.1115/1.4023829 History: Received November 05, 2012; Revised February 05, 2013

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. Advanced and innovative cooling techniques become one of the crucial major elements supporting the development of modern gas turbines, both land-based and air-breathing engines with continual increment of turbine inlet temperature (TIT) in order to meet higher energy demand and efficiency. This paper discusses state-of-the-art airfoil cooling techniques that are mainly applicable in the mainbody and trailing edge section of turbine airfoil. Potential internal cooling designs for near-term applications based on current manufacturing capabilities are identified. A literature survey focusing primarily on the past four to five years has also been performed.

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Fig. 1

Projected coal-gas turbine operating parameters [2-4]

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Fig. 2

Schematic of typical gas turbine airfoil with common cooling techniques [6]

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Fig. 3

Airfoil with double-wall cooling [8-11]

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Fig. 4

Generic Lamilloy® cooling [12]

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Fig. 5

Durability map illustrating the path for higher cooling effectiveness [16]

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Fig. 6

Local heat transfer coefficient (W/m2-K) and CFD simulated streakline in a double-wall cooling channel, channel's Reynolds number = 8000 [17]

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Fig. 7

Rib-turbulators for internal cooling passages in turbine airfoil [21]

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Fig. 8

Local heat transfer coefficient distribution with diamond shaped pin-fins [44]

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Fig. 9

Top view of test plate with different pin-fin configurations

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Fig. 10

Local heat transfer coefficient distribution (case 1)

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Fig. 11

Endwall heat transfer enhancement versus Re

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Fig. 12

Total heat transfer enhancement versus Re

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Fig. 13

Different dimple geometries [60-62]

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Fig. 14

Heat transfer enhancement versus Re with dimples

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Fig. 15

Innovative cooling configurations with mesh and dimple [64]

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Fig. 16

Schematic layout of detached pin-fin with broken rib and full rib

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Fig. 17

Local heat transfer coefficient, h (W/m2-K) distribution for endwall and pin-fins [68]

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Fig. 18

Total heat transfer enhancement of detached pin-fins with broken rib and full rib [68]

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Fig. 19

Heat transfer enhancement of pin-fins with dimples and rib-turbulators

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Fig. 20

Zig-zag channel with different surface configuration [70]

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Fig. 21

Local heat transfer coefficient of smooth zig-zag channel [69]

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Fig. 22

Local heat transfer coefficient of rib-turbulated zig-zag channel [70]

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Fig. 23

Total heat transfer enhancement versus Re (zig-zag channel) [70]

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Fig. 24

Pressure loss versus Re (zig-zag channel) [70]



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