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Research Papers

Influence of Turbine Blade Leading Edge Profile on Film Cooling With Shaped Holes

[+] Author and Article Information
Mingjie Zhang

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

Nian Wang, Andrew F. Chen, Je-Chin Han

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received April 3, 2017; final manuscript received February 6, 2018; published online May 21, 2018. Assoc. Editor: Ting Wang.

J. Thermal Sci. Eng. Appl 10(5), 051006 (May 21, 2018) (12 pages) Paper No: TSEA-17-1103; doi: 10.1115/1.4039703 History: Received April 03, 2017; Revised February 06, 2018

This paper presents the turbine blade leading edge model film cooling effectiveness with shaped holes, using the pressure sensitive paint (PSP) mass transfer analogy method. The effects of leading edge profile, coolant to mainstream density ratio, and blowing ratio are studied. Computational simulations are performed using the realizable k–ɛ (RKE) turbulence model. Effectiveness obtained by computational fluid dynamics (CFD) simulations is compared with experiments. Three leading edge profiles, including one semicylinder and two semi-elliptical cylinders with an after body, are investigated. The ratios of major to minor axis of two semi-elliptical cylinders are 1.5 and 2.0, respectively. The leading edge has three rows of shaped holes. For the semicylinder model, shaped holes are located at 0 deg (stagnation line) and ±30 deg. Row spacing between cooling holes and the distance between impingement plate and stagnation line are the same for three leading edge models. The coolant to mainstream density ratio varies from 1.0 to 1.5 and 2.0, and the blowing ratio varies from 0.5 to 1.0 and 1.5. Mainstream Reynolds number is about 100,000 based on the diameter of the leading edge cylinder, and the mainstream turbulence intensity is about 7%. The results provide an understanding of the effects of leading edge profile on turbine blade leading edge region film cooling with shaped hole designs.

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References

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Figures

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Fig. 3

PSP calibration curves. (a) Power fitting curve and (b) intensity ratio taken under 20 deg to 90 deg viewing angles (Shiau et al. [22]) (Reprinted with permission from ASME copyright 2016).

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Fig. 2

Leading edge models and shaped holes configuration (a) top view, (b) front view, and (c) shaped hole geometry

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Fig. 1

Schematic diagram of the test facility and test section (a) test facility and (b) test section

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Fig. 4

Film cooling effectiveness contour plot for 1.0R

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Fig. 5

Film cooling effectiveness contour plot for 1.0R, 1.5R, and 2.0R at DR = 1.5

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Fig. 6

Effect of blowing ratio on spanwise averaged film cooling effectiveness for three profiles

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Fig. 7

Effect of density ratio on spanwise averaged film cooling effectiveness for three profiles

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Fig. 8

Effect of leading edge profile on spanwise averaged film cooling effectiveness

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Fig. 9

Area-averaged film cooling effectiveness

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Fig. 10

Schematic of computational domain and grid

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Fig. 13

Velocity magnitude (m/s) contours and streamlines for three leading edge profiles (DR = 1.5 and M = 1.0)

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Fig. 14

Coolant path lines and dimensionless temperature for three leading edge profiles (DR = 1.5 and M = 1.0)

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Fig. 15

Mass flow rates (10−4 kg/s) for DR = 1.5

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Fig. 16

Local blowing ratios for DR = 1.5

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Fig. 17

CFD predicted and PSP measured spanwise averaged film cooling effectiveness for three leading edge profiles

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Fig. 18

CFD predicted spanwise averaged effectiveness for 1.0R and 2.0R profiles

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Fig. 19

Mass flow rates (10−4 kg/s) for 1.0R profile

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Fig. 20

Local blowing ratios for 1.0R profile

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Fig. 11

Leading edge spanwise averaged static pressure distributions for three profiles (DR = 1.5 and M = 1.0)

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Fig. 12

Static pressure (Pa) contours for three leading edge profiles (DR = 1.5 and M = 1.0)

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Fig. 21

Film cooling effectiveness contour plot for 1.0R and M = 1.5

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Fig. 22

CFD predicted and PSP measured spanwise averaged film cooling effectiveness for 1.0R profile

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