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Research Papers

A Novel Method for Designing Fan-Shaped Holes With Short Length-to-Diameter Ratio in Producing High Film Cooling Performance for Thin-Wall Turbine Airfoil

[+] Author and Article Information
Weihong Li

Systems, Power & Energy Research Division,
School of Engineering,
University of Glasgow,
Glasgow G12 8QQ, UK
e-mail: Liwh13@mails.tsinghua.edu.cn

Xueying Li

Institute of Gas Turbine,
Department of Energy and Power Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: lixueying@mail.tsinghua.edu.cn

Jing Ren

Institute of Gas Turbine,
Department of Energy and Power Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: renj@tsinghua.edu.cn

Hongde Jiang

Institute of Gas Turbine,
Department of Energy and Power Engineering,
Tsinghua University,
Beijing 100084, China

1Corresponding author.

Manuscript received September 24, 2017; final manuscript received July 27, 2018; published online August 28, 2018. Assoc. Editor: Kenichiro Takeishi.

J. Turbomach 140(9), 091004 (Aug 28, 2018) (15 pages) Paper No: TURBO-17-1175; doi: 10.1115/1.4041035 History: Received September 24, 2017; Revised July 27, 2018

An experimental investigation of the geometrical parameter effects on the film cooling performance of a fan-shaped hole was conducted on a low speed flat-plate facility. The pressure sensitive paint (PSP) technique and steady liquid crystal (SLC) technique were employed to determine the adiabatic film cooling effectiveness and heat transfer coefficients, respectively, for a blowing ratio ranging from 0.3 to 3 and a density ratio of DR = 1.5. Several geometrical parameters were investigated, including lateral expansion angle, length-to-diameter ratio, and hole entrance shape. Local, laterally averaged, and area-averaged adiabatic film cooling effectiveness, heat transfer coefficients, and net heat flux reduction (NHFR) were shown to provide a comprehensive understanding on the geometrical parameter effects on the thermal performance. A novel method was proposed for designing a fan-shaped hole with short length-to-diameter ratio to design to achieve high film cooling performance. The original and optimized fan-shaped holes were compared in terms of adiabatic film cooling effectiveness, heat transfer coefficients, and NHFR. Results showed that the optimized fan-shaped hole with short length-to-diameter ratio, large lateral diffusion angle, and slot hole entrance shape obtained highest overall thermal performance. It demonstrated the feasibility of adopting the proposed design method to design fan-shaped holes applied in thin wall gas turbine blades.

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Figures

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Fig. 1

Double wall cooling vane with short film cooling holes

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Fig. 2

Schematic view of the low speed wind tunnel

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Fig. 3

Approach boundary layers measured at x/D = −10 for film cooling measurements

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Fig. 4

Schematic drawing of three different fan-shape holes: (a) baseline long hole, (b) optimized short hole 1, and (c) slotlike entrance hole

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Fig. 5

Geometrical configurations of fan-shaped holes: (a) L/D = 5, (b) L/D = 3.5, and (c) L/D = 2

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Fig. 6

Pressure sensitive paint calibration curves under different temperature conditions

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Fig. 7

Diagram of constant heat flux multilayer setup

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Fig. 8

Calibration curve of SLC with different thickness

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Fig. 9

Laterally averaged film cooling effectiveness and heat transfer coefficient comparison with published data: (a) film cooling effectiveness and (b) heat transfer coefficient

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Fig. 10

Film cooling effectiveness distribution with varied lateral expansion angle under three blowing ratios: (a) Config A, γ = 10 deg, (b) Config B, γ = 14 deg, and (c) Config C, γ = 18 deg

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Fig. 11

Laterally averaged film cooling effectiveness and heat transfer coefficient with varied lateral expansion angle: (a) film cooling effectiveness and (b) heat transfer coefficient

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Fig. 12

Area-averaged film cooling effectiveness and heat transfer coefficient with varied lateral expansion angle: (a) film cooling effectiveness and (b) heat transfer coefficient

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Fig. 13

Film cooling effectiveness distributions with varied L/D under three blowing ratios: (a) Config G, L/D = 2, (b) Config D, L/D = 3.5, and (c) Config A, L/D = 5

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Fig. 14

Heat transfer coefficient distributions with varied L/D under two blowing ratios: (a) Config G, L/D = 2, (b) Config D, L/D = 3.5, and (c) Config A, L/D = 5

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Fig. 15

Laterally averaged film cooling effectiveness and heat transfer coefficient with varied L/D: (a) film cooling effectiveness and (b) heat transfer coefficient

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Fig. 16

Area-averaged film cooling effectiveness and heat transfer coefficient with varied L/D: (a) film cooling effectiveness and (b) heat transfer coefficient

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Fig. 17

Film cooling effectiveness distribution with varied L/D and lateral expansion angle under three blowing ratios: (a) Config H, L/D = 2, (b) Config E, L/D = 3.5, and (c) Config A, L/D = 5

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Fig. 18

Laterally averaged film cooling effectiveness with varied L/D and lateral expansion angle

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Fig. 19

Area-averaged film cooling effectiveness and heat transfer coefficient with varied L/D and lateral expansion angle: (a) film cooling effectiveness and (b) heat transfer coefficient

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Fig. 20

Film cooling effectiveness distribution with varied L/D and hole entrance shape under three blowing ratios: (a) Config I, L/D = 2, (b) Config F, L/D = 3.5, and (c) Config A, L/D = 5

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Fig. 21

Nondimensional velocity distributions of three holes at (a) hole exit, and (b) middle plane of the hole, M = 1.5

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Fig. 22

Heat transfer distributions with varied L/D and hole entrance shape under three blowing ratios: (a) Config I, L/D = 2, (b) Config F, L/D = 3.5

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Fig. 23

Nondimensional turbulent kinetic energy distributions of three holes at x/D = 1, M = 1.5

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Fig. 24

Area-averaged film cooling effectiveness and heat transfer coefficient with varied L/D and hole entrance shape: (a) film cooling effectiveness and (b) heat transfer coefficient

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Fig. 25

Overall evaluation of area-averaged film cooling effectiveness and heat transfer coefficient: (a) film cooling effectiveness and (b) heat transfer coefficient

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Fig. 26

Area-averaged NHFR

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