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Research Papers

Heat Transfer Coefficient and Film Cooling Effectiveness on the Partial Cavity Tip of a Gas Turbine Blade

[+] Author and Article Information
Jin Young Jeong

School of Aerospace and Mechanical Engineering,
Korea Aerospace University,
76, Hanggongdaehang-ro, Deogyang-gu,
Goyang-si, Gyeonggi-do 10540,
Republic of Korea
e-mail: jyjeong1220@kau.kr

Woobin Kim

School of Aerospace and Mechanical Engineering,
Korea Aerospace University,
76, Hanggongdaehang-ro, Deogyang-gu,
Goyang-si, Gyeonggi-do 10540,
Republic of Korea
e-mail: iab00@naver.com

Jae Su Kwak

School of Aerospace and Mechanical Engineering,
Korea Aerospace University,
76, Hanggongdaehang-ro, Deogyang-gu,
Goyang-si, Gyeonggi-do 10540,
Republic of Korea
e-mail: jskwak@kau.ac.kr
Mem. ASME

Jung Shin Park

Doosan Heavy Industries and Construction,
10, Suji-ro 112beon-gil, Suji-gu, Yongin-si,
Gyeonggi-do 16858, Republic of Korea
e-mail: jungshin.park@doosan.com

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received December 6, 2018; final manuscript received January 11, 2019; published online February 22, 2019. Assoc. Editor: Kenneth Hall.

J. Turbomach 141(7), 071007 (Feb 22, 2019) (9 pages) Paper No: TURBO-18-1349; doi: 10.1115/1.4042647 History: Received December 06, 2018; Revised January 11, 2019; Accepted January 14, 2019

Leakage flow between the rotating turbine blade tip and the fixed casing causes high heat loads and thermal stress on the tip and near the tip region. For this study, new squealer tips called partial cavity tips, which combine the advantages of plane and squealer tips, were suggested, and the effects of the cavity shape on the tip heat transfer coefficient and film cooling effectiveness were investigated experimentally in a low-speed linear cascade. The suggested blade tips had a flat surface near the leading edge and a squealer cavity from the mid-chord to trailing edge region to achieve the advantages of both blade tip types. The heat transfer coefficient was measured via the 1-D transient heat transfer technique using an IR camera, and the film cooling effectiveness was obtained via the pressure-sensitive paint (PSP) technique. Results showed that the heat transfer coefficient and film cooling effectiveness on the partial cavity tips strongly depended on the cavity shape. Near the leading edge, the heat transfer coefficients for the partial cavity tip cases were lower than that for the squealer tip case. However, the heat transfer coefficient on the cavity surface was higher for the partial cavity tip cases. The D10 tip showed a similar distribution of film cooling effectiveness to that of the plane (PLN) tip near the leading edge and the double side squealer (DSS) tip near the mid-chord region. However, the overall average film cooling effectiveness of the DSS tip was higher than that of the D10 tip.

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References

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Figures

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Fig. 1

Experimental setup for the heat transfer measurements: (a) experimental setup and (b) heat transfer measurement blade

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Fig. 2

Measured and compensated mainstream temperature

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Fig. 3

Shapes of conventional and partial cavity tips: (a) PLN, (b) DSS, (c) D10, (d) D30, (e) D 50, (f) D30-60, and (g) D30-120

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Fig. 4

Schematic of the test section for the film cooling effectiveness measurements

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Fig. 5

Schematic of film cooling blade (PLN tip)

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Fig. 6

Film cooling blade tip shapes: (a) PLN, (b) DSS, and (c) D10

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Fig. 7

PSP calibration curve

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Fig. 8

Heat transfer coefficient for each blade tip shape: (a) PLN, (b) DSS, (c) D10, (d) D30, (e) D50, (f) D30-60, and (g) D30-120

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Fig. 9

Average heat transfer coefficient along blade chord: (a) effect of cavity size and (b) effect of cavity angle

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Fig. 10

Overall average heat transfer coefficient

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Fig. 11

Film cooling effectiveness of the PLN tip: (a) DR = 1.0, M = 0.5; (b) DR = 1.0, M = 1.0; (c) DR = 1.0, M = 1.5; (d) DR = 1.0, M = 2.0; (e) DR = 1.5, M = 0.5; (f) DR = 1.5, M = 1.0; (g) DR = 1.5, M = 1.5; and (h) DR = 1.0, M = 2.0

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Fig. 12

Film cooling effectiveness of the DSS tip: (a) DR = 1.0, M = 0.5; (b) DR = 1.0, M = 1.0; (c) DR = 1.0, M = 1.5; (d) DR = 1.0, M = 2.0; (e) DR = 1.5, M = 0.5; (f) DR = 1.5, M = 1.0; (g) DR = 1.5, M = 1.5; and (h) DR = 1.0, M = 2.0

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Fig. 13

Film cooling effectiveness of the D10 tip: (a) DR = 1.0, M = 0.5; (b) DR = 1.0, M = 1.0; (c) DR = 1.0, M = 1.5; (d) DR = 1.0, M = 2.0; (e) DR = 1.5, M = 0.5; (f) DR = 1.5, M = 1.0; (g) DR = 1.5, M = 1.5; and (h) DR = 1.0, M = 2.0

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Fig. 14

Average film cooling effectiveness along blade chord

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Fig. 15

Overall average film cooling effectiveness: (a) PLN, (b) DSS, and (c) D10

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Fig. 16

Overall average film cooling effectiveness at the same density ratio: (a) DR = 1.0 and (b) DR = 1.5

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