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Research Papers

Turbine Vane Endwall Film Cooling Comparison From Five Film-Hole Design Patterns and Three Upstream Injection Angles

[+] Author and Article Information
Chao-Cheng Shiau

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: joeshiau@tamu.edu

Izzet Sahin

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: izzetsahin@tamu.edu

Nian Wang

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: wangnian@tamu.edu

Je-Chin Han

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: jc-han@tamu.edu

Hongzhou Xu

Solar Turbines Incorporated,
2200 Pacific Highway,
San Diego, CA 92186
e-mail: xu_hongzhou@solarturbines.com

Michael Fox

Solar Turbines Incorporated,
2200 Pacific Highway,
San Diego, CA 92186
e-mail: mikefox@solarturbines.com

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received July 3, 2018; final manuscript received November 15, 2018; published online February 6, 2019. Assoc. Editor: Ting Wang.

J. Thermal Sci. Eng. Appl 11(3), 031012 (Feb 06, 2019) (10 pages) Paper No: TSEA-18-1344; doi: 10.1115/1.4042057 History: Received July 03, 2019; Revised November 15, 2019

The effects of upstream injection angle on film cooling effectiveness of a turbine vane end wall with various endwall film-hole designs were examined by applying pressure-sensitive paint (PSP) measurement technique. As the leakage flow from the slot between the combustor and the turbine vane is not considered an active source to protect the vane endwall in certain engine designs, discrete cylindrical holes are implemented near the slot to create an additional controllable upstream film to cool the vane end wall. Three potential injection angles were studied: 30 deg, 40 deg, and 50 deg. To explore the optimum endwall cooling design, five different film-hole patterns were tested: axial row, cross row, cluster, midchord row, and downstream row. Experiments were conducted in a four-passage linear cascade facility in a blowdown wind tunnel at the exit isentropic Mach number of 0.5 corresponding to inlet Reynolds number of 380,000 based on turbine vane axial chord length. A freestream turbulence intensity of 19% with an integral length scale of 1.7 cm was generated at the cascade inlet plane. Detailed film cooling effectiveness for each design was analyzed and compared at the design operation conditions (coolant mass flow ratio (MFR) 1% and density ratio 1.5). The results are presented in terms of high-fidelity film effectiveness contours and laterally (spanwise) averaged effectiveness. This paper will provide the gas turbine designers valuable information on how to select the best endwall cooling pattern with minimum cooling air consumption over a range of upstream injection angle.

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References

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Figures

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Fig. 5

Pressure-sensitive paint system and working principle

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Fig. 4

Schematic of different film-hole pattern design on the end wall: (a) axial row, (b) cross row, (c) cluster, (d) mid-chord row, and (e) downstream row

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Fig. 3

Schematic of different injection angle for two-row upstream injection: (a) 30 deg, (b) 40 deg, and (c) 50 deg

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Fig. 2

Schematic of the endwall test section

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Fig. 1

Flow loop of the test section and cascade facility

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Fig. 6

Pressure-sensitive paint calibration curves [27]

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Fig. 7

Cross flow visualization on different endwall configuration (upstream angle is 30 deg): (a) axial row, (b) cross row, (c) cluster, (d) midchord row, and (e) downstream row

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Fig. 8

Film cooling effectiveness of axial row configuration under different upstream injection angle: (a) no upstream, (b) 30 deg, (c) 40 deg, and (d) 50 deg

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Fig. 9

Film cooling effectiveness of cross row configuration under different upstream injection angle: (a) no upstream, (b) 30 deg, (c) 40 deg, and (d) 50 deg

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Fig. 10

Film cooling effectiveness of cluster configuration under different upstream injection angle: (a) no upstream, (b) 30 deg, (c) 40 deg, and (d) 50 deg

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Fig. 11

Film cooling effectiveness of midchord row configuration under different upstream injection angle: (a) no upstream, (b) 30 deg, (c) 40 deg, and (d) 50 deg

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Fig. 12

Film cooling effectiveness of downstream row configuration under different upstream injection angle: (a) no upstream, (b) 30 deg, (c) 40 deg, and (d) 50 deg

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Fig. 13

Laterally (spanwise) averaged film cooling effectiveness under different injection angle: (a) axial row; (b) cross row; and (c) cluster configuration

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Fig. 14

Laterally (spanwise) averaged film cooling effectiveness under different injection angle: (a) midchord row; and (b) downstream row configuration

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Fig. 16

Area-averaged film cooling effectiveness for all the design combinations

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Fig. 15

Laterally (spanwise) averaged film cooling effectiveness for different endwall film-hole pattern: (a) upstream angle is 30 deg; (b) upstream angle is 40 deg; and (c) upstream angle is 50 deg

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