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Research Papers

Film Cooling Effectiveness Comparison on Full-Scale Turbine Vane Endwalls Using Pressure-Sensitive Paint Technique

[+] 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

Andrew F Chen

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

Je-Chin Han

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

Salam Azad

Siemens Energy, Inc.,
Orlando, FL 32826-2399
e-mail: salam.azad@siemens.com

Ching-Pang Lee

Siemens Energy, Inc.,
Orlando, FL 32826-2399
e-mail: ching-pang.lee@siemens.com

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 19, 2017; final manuscript received October 4, 2017; published online December 6, 2017. Editor: Kenneth Hall.

J. Turbomach 140(2), 021009 (Dec 06, 2017) (12 pages) Paper No: TURBO-17-1168; doi: 10.1115/1.4038278 History: Received September 19, 2017; Revised October 04, 2017

Turbine vane endwalls are highly susceptible to intensive heat load due to their large exposed area and complex flow field especially for the first stage of the vane. Therefore, a suitable film cooling design that properly distributes the given amount of coolant is critical to keep the vane endwall from failure at the same time to maintain a good balance between manufacturing cost, performance, and durability. This work is focused on film cooling effectiveness evaluation on full-scale heavy-duty turbine vane endwall and the performance comparison with different film cooling pattern designs in the literature. The area of interest (AOI) of this study is on the inner endwall (hub) of turbine vane. Tests were performed in a three-vane annular sector cascade under the mainstream Reynolds number 350,000; the related inlet Mach number is 0.09 and the freestream turbulence intensity is 12%. Two variables, coolant-to-mainstream mass flow ratios (MFR = 2–4%) and density ratios (DR = 1.0, 1.5), are investigated. The conduction-error free pressure-sensitive paint (PSP) technique is utilized to evaluate the local flow behavior as well as the film cooling performance. The presented results are expected to provide the gas turbine engine designer a direct comparison between two film-hole configurations on a full-scale vane endwall under the same amount of coolant usage.

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References

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Figures

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Fig. 1

Schematic of vane cascade and test facility: (a) annular sector cascade, (b) test facility view from upstream, and (c) test facility view from downstream

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Fig. 3

Flow deflector caps: (a) for inner plenum and (b) for outer plenum

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Fig. 4

Perforated plates: (a) for inner plenum and (b) for outer plenum

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Fig. 5

Planar projected cooling hole distribution on the AOI of vane test section

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Fig. 6

Test section in the camera-point-of-view: (a) downstream view and (b) upstream view

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Fig. 7

PSP working principle and calibration: (a) PSP system/working principle, (b) calibration results for operating temperature as reference temperature, and (c) calibration results for different camera view angles

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Fig. 8

Test section coated with PSP: (a) downstream view and (b) upstream view

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Fig. 9

Film cooling effectiveness distributions of design2 at DR = 1.0. Red bold arrows indicate mainstream direction: (a)MFR = 2%, (b) MFR = 3%, and (c) MFR = 4%.

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Fig. 10

Film cooling effectiveness distributions of design2 at DR = 1.5. Red bold arrows indicate mainstream direction: (a) MFR = 2%, (b) MFR = 3%, and (c) MFR = 4%.

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Fig. 11

Laterally (spanwise) averaged film cooling effectiveness of design2

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Fig. 12

Planar projected cooling hole distribution on the AOI of design1

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Fig. 13

Film cooling effectiveness distributions of design1 at DR = 1.0. Red bold arrows indicate mainstream direction: (a)MFR = 2%, (b) MFR = 3%, and (c) MFR = 4%.

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Fig. 14

Film cooling effectiveness distributions of design1 at DR = 1.5. Red bold arrows indicate mainstream direction: (a)MFR = 2%, (b) MFR = 3%, and (c) MFR = 4%.

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Fig. 15

Laterally (spanwise) averaged film cooling effectiveness of design1

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Fig. 16

Area-averaged film cooling effectiveness of design1 and design2

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