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Research Papers

Turbine Vane Endwall Film Cooling With Slashface Leakage and Discrete Hole Configuration

[+] Author and Article Information
Nafiz H. K. Chowdhury

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

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

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

Luzeng Zhang

Solar Turbines Inc.,
2200 Pacific Highway,
San Diego, CA 92186
e-mail: luzengz@yahoo.com

Hee-Koo Moon

Solar Turbines Inc.,
2200 Pacific Highway,
San Diego, CA 92186
e-mail: heekoomoon@gmail.com

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 14, 2016; final manuscript received September 21, 2016; published online February 1, 2017. Editor: Kenneth Hall.

J. Turbomach 139(6), 061003 (Feb 01, 2017) (11 pages) Paper No: TURBO-16-1240; doi: 10.1115/1.4035162 History: Received September 14, 2016; Revised September 21, 2016

Turbine vanes are typically assembled as a section containing single or double airfoil units in an annular pattern. First stage guide vane assembly results in two common mating interfaces: a gap between combustor and vane endwall and another resulted from the adjacent sections, called slashface. High pressure coolant could leak through these gaps to reduce the ingestion of hot gas and achieve certain cooling benefit. As vane endwall region flow field is already very complicated due to highly three-dimensional secondary flows, then a significant influence on endwall cooling can be expected due to the gap leakage flows. To determine the effect of leakage flows from those gaps, film cooling effectiveness distributions were measured using pressure sensitive paint (PSP) technique on the endwall of a scaled up, midrange industrial turbine vane geometry with the multiple rows of discrete film cooling (DFC) holes inside the passages. Experiments were performed in a blow-down wind tunnel cascade facility at the exit Mach number of 0.5 corresponding to Reynolds number of 3.8 × 105 based on inlet conditions and axial chord length. Passive turbulence grid was used to generate free-stream turbulence (FST) level about 19% with an integral length scale of 1.7 cm. Two parameters, coolant-to-mainstream mass flow ratio (MFR) and density ratio (DR), were studied. The results are presented as two-dimensional film cooling effectiveness distribution on the vane endwall surface with the corresponding spanwise averaged values along the axial direction.

Copyright © 2017 by ASME
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References

Figures

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Fig. 1

Conceptual view of leakage flows over vane endwall

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Fig. 2

Vane assembly unit

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Fig. 3

Schematic of inlet leakage simulation

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Fig. 4

Slashface geometry

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Fig. 5

Discrete film-cooling hole pattern

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Fig. 6

Schematic of experimental facility

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Fig. 7

Pitchwise pressure distribution

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Fig. 8

Top view of plenum designs

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Fig. 9

PSP working principle

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Fig. 10

PSP calibration results: (a) Tref = 22 °C and (b) Tref is same as the operating temperature

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Fig. 11

Static pressure distribution by PSP

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Fig. 12

Endwall film effectiveness contours for inlet leakage MFR of (a) 0.0%, (b) 0.5%, (c) 1.0%, and (d) 1.5%

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Fig. 13

Spanwise average endwall film cooling effectiveness for varying inlet leakage MFR

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Fig. 14

Endwall film effectiveness contours for slashface MFR of (a) 0.0%, (b) 0.5%, and (c) 1.0%

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Fig. 15

Spanwise average endwall film cooling effectiveness for varying slashface MFR

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Fig. 16

Endwall film effectiveness contours for discrete hole injection MFR of (a) DFC (with slashface) = 0.4%, DFC (w/o slashface) = 0.5%; (b) DFC (with slashface) = 0.8%, DFC (w/o slashface) = 1.0%; and (c) DFC (with slashface) = 1.2%, DFC (w/o slashface) = 1.5%

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Fig. 17

Spanwise average endwall film cooling effectiveness for varying discrete hole MFR

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Fig. 18

Endwall film effectiveness contours for density ration of (a) 1.0, (b) 1.5, and (c) 2.0

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Fig. 19

Spanwise average endwall film cooling effectiveness for varying density ratio

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