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Research Papers: Gas Turbines: Heat Transfer

Experimental Investigation of Endwall Heat Transfer With Film and Impingement Cooling

[+] Author and Article Information
Xueying Li

Department of Thermal Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: li_xy@mail.tsinghua.edu.cn

Jing Ren, Hongde Jiang

Department of Thermal Engineering,
Tsinghua University,
Beijing 100084, China

1Corresponding author.

Contributed by the Heat Transfer Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received March 17, 2017; final manuscript received March 21, 2017; published online April 25, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(10), 101901 (Apr 25, 2017) (9 pages) Paper No: GTP-17-1101; doi: 10.1115/1.4036361 History: Received March 17, 2017; Revised March 21, 2017

The switch from diffusive combustion to premixed combustion in a modern gas turbine changes the combustor exit temperature profile to a more uniform one. This will directly affect the cooling of the first stage vane especially the endwall region. A typical endwall configuration with matched nondimensional parameters to the engine condition was investigated experimentally in this study. Two endwall cooling arrangements at four different coolant to mainstream mass flow ratios (MFR) were tested in a linear cascade. Detailed measurements of pressure distribution, heat transfer coefficient, adiabatic film cooling effectiveness, and overall effectiveness of the endwall were performed. The temperature-sensitive paint (TSP) and pressure-sensitive paint (PSP) were used to acquire these parameters. The conjugate heat transfer characteristic of endwall with film cooling and impingement cooling was discussed. Moreover, the influence of coolant mass flow rate on conjugate heat transfer of endwall was analyzed. One- and two-dimensional methods for overall effectiveness prediction based on experimental data for separate parameters and correlations were also studied.

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References

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Figures

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Fig. 1

Wind tunnel of the experiment

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Fig. 2

Schematic diagram of the test section

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Fig. 3

View of the endwall and vane pressure taps

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Fig. 4

Endwall static pressure tap distribution

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Fig. 5

Endwall static pressure distribution: (a) measured and (b) CFD prediction

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Fig. 6

Endwall static pressure measurement results at different axial positions versus calculation

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Fig. 7

Excitation light source and the TSP surface

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Fig. 8

TSP calibration result

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Fig. 9

Cross section of the multilayer attached to the endwall surface

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Fig. 10

External Nusselt number

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Fig. 11

Result of adiabatic film cooling effectiveness

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Fig. 12

Schematic of cooling scheme

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Fig. 13

Schematic of the two cooling arrangements

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Fig. 14

Overall effectiveness distribution with film cooling only

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Fig. 15

Pitchwise-averaged overall effectiveness with film cooling only

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Fig. 16

Pitchwise distribution of overall effectiveness with film cooling only

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Fig. 17

Overall effectiveness distribution with film and impingement cooling

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Fig. 18

Pitchwise-averaged overall effectiveness with film and impingement cooling

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Fig. 19

Pitchwise distribution of overall effectiveness with film and impingement cooling

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Fig. 20

One-dimensional prediction of pitchwise-averaged overall effectiveness with film and impingement cooling: (a) MFR = 0.8%, (b) MFR = 1.0%, and (c) MFR = 1.5%

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Fig. 21

Two-dimensional prediction model

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Fig. 22

Two-dimensional prediction of overall effectiveness distribution at MFR = 1.0% with film cooling and impingement cooling

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Fig. 23

One- and two-dimensional prediction of pitchwise-averaged overall effectiveness at MFR = 1.0% with film cooling and impingement cooling

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