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Research Papers

Improvement in Film Cooling Effectiveness Using Single and Double Rows of Holes With Adverse Compound Angle Orientations

[+] Author and Article Information
E. Kannan

Department of Mechanical Engineering,
Hindustan Institute of Technology and Science,
Chennai 603103, Tamil Nadu, India
e-mail: kannan2671@gmail.com

Seralathan Sivamani

Department of Mechanical Engineering,
Hindustan Institute of Technology and Science,
Chennai 603103, Tamil Nadu, India
e-mail: siva.seralathan@gmail.com

D. G. Roychowdhury

Department of Mechanical Engineering,
Hindustan Institute of Technology and Science,
Chennai 603103, Tamil Nadu, India;
Hindustan College of Science and Technology,
Farah,
Mathura 281122, Uttar Pradesh, India
e-mail: roychowdhury.dg@gmail.com

T. Micha Premkumar

Department of Mechanical Engineering,
Hindustan Institute of Technology and Science,
Chennai 603103, Tamil Nadu, India
e-mail: tmichamech@gmail.com

V. Hariram

Department of Mechanical Engineering,
Hindustan Institute of Technology and Science,
Chennai 603103, Tamil Nadu, India
e-mail: connect2hariram@gmail.com

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received March 12, 2018; final manuscript received November 1, 2018; published online December 6, 2018. Assoc. Editor: Nesrin Ozalp.

J. Thermal Sci. Eng. Appl 11(2), 021014 (Dec 06, 2018) (19 pages) Paper No: TSEA-18-1130; doi: 10.1115/1.4041937 History: Received March 12, 2018; Revised November 01, 2018

Three-dimensional Reynolds-averaged Navier–Stokes equations with shear stress transport turbulence model are used to analyze the film cooling effectiveness on a flat plate having single row of film hole involving cylindrical hole (CH) and laidback hole (LBH). The CH and LBH are inclined at 35 deg to the surface with a compound angle (β) orientation ranging from favorable to adverse inclination (i.e., β = 0–180 deg) and examined at high and low blowing ratios (M = 1.25 and 0.60). CH with an adverse compound angle of 135 deg gives the highest area-averaged film cooling effectiveness in comparison with LBH configuration. Also, CH β = 135 deg film hole shows a higher lateral coolant spread. Later, double jet film cooling (DJFC) concept is studied for this CH. In all the cases, the first hole compound angle is fixed as 135 deg, and the second hole angle is varied from 135 deg to 315 deg. At high blowing ratio, the dual jet cylindrical hole (DJCH) with β = 135 deg, 315 deg gives a higher area-averaged film cooling effectiveness by around 66.50% compared to baseline CH β = 0 deg. On comparing all CH, LBH, and DJCH cases, the highest area-averaged film cooling effectiveness is obtained by CH configuration with β = 135 deg. Hence, the CH with its adverse compound angle (β = 135 deg) orientation could be an appropriate film cooling configuration for gas turbine blade cooling.

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Figures

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Fig. 1

Computational domain details of CH and LBH: (a) computational domain dimensional details and (b)computational domain

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Fig. 2

Schematic arrangement of CH and LBH with its compound angle (β) from 0 deg to 180 deg

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Fig. 3

(a) DJCH computational domain and (b) schematic arrangement of DJCH holes

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Fig. 4

Structured mesh of the (a) CH, (b) LBH, and (c) DJCH computational domains

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Fig. 5

Computational domain with boundary conditions enforced

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Fig. 6

Validation with the experimental data [9] and turbulence model study

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Fig. 7

Grid independency study

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Fig. 8

Contours of adiabatic film cooling effectiveness for CH configuration (M = 0.6)

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Fig. 9

Contours of adiabatic film cooling effectiveness for CH configuration (M = 1.25)

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Fig. 10

Adiabatic film cooling effectiveness contours of LBH

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Fig. 11

Bottom plate effectiveness of CH: (a) cylindrical hole, M = 0.60 and (b) cylindrical hole, M = 1.25

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Fig. 12

Bottom plate effectiveness of LBH: (a) laidback hole, M = 0.60 and (b) laidback hole, M = 1.25

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Fig. 13

Spanwise-averaged film cooling effectiveness for CH at M = 0.60

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Fig. 14

Spanwise-averaged film cooling effectiveness for CH at M = 1.25

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Fig. 15

Spanwise-averaged film cooling effectiveness for LBH at M = 0.60

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Fig. 16

Spanwise-averaged film cooling effectiveness for LBH at M = 1.25

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Fig. 17

Centerline local η for CH; β = 0 deg–180 deg (M = 0.60)

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Fig. 18

Centerline local η for CH; β = 0– deg180 deg (M = 1.25)

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Fig. 19

Centerline local η for LBH; β = 0– deg180 deg (M = 0.60)

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Fig. 20

Centerline local η for LBH; β = 0– deg180 deg (M = 1.25)

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Fig. 21

Comparison of LBH at M = 0.60 and M = 1.25

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Fig. 22

Centerline local η comparison for CH and LBH (M = 0.60)

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Fig. 23

Area-averaged film cooling effectiveness of the bottom plate

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Fig. 24

Local lateral effectiveness M = 1.25, x/D = 10

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Fig. 25

Adiabatic film cooling effectiveness contours of DJCH at M = 0.60

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Fig. 26

Adiabatic film cooling effectiveness contours of DJCH at M = 1.25

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Fig. 27

Centerline local film cooling effectiveness of DJCH configurations

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Fig. 28

Bottom plate film cooling effectiveness of various DJCH cases

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Fig. 29

Spanwise-averaged film cooling effectiveness for DJCH holes at M = 0.60 and 1.25

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Fig. 30

Area-averaged film cooling effectiveness of various DJCH

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