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Research Papers

Sweeping Jet Film Cooling on a Turbine Vane

[+] Author and Article Information
Mohammad A. Hossain

Aerospace Research Center,
Department of Mechanical and
Aerospace Engineering,
The Ohio State University,
Columbus, OH 43235
e-mail: hossain.49@osu.edu

Lucas Agricola, Ali Ameri, James W. Gregory, Jeffrey P. Bons

Aerospace Research Center,
Department of Mechanical and
Aerospace Engineering,
The Ohio State University,
Columbus, OH 43235

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 19, 2018; final manuscript received November 14, 2018; published online January 16, 2019. Editor: Kenneth Hall.

J. Turbomach 141(3), 031007 (Jan 16, 2019) (11 pages) Paper No: TURBO-18-1257; doi: 10.1115/1.4042070 History: Received September 19, 2018; Revised November 14, 2018

The cooling performance of sweeping jet film cooling was studied on a turbine vane suction surface in a low-speed linear cascade wind tunnel. The sweeping jet holes consist of fluidic oscillators with an aspect ratio (AR) of unity and a hole spacing of Pd/D = 6. Infrared (IR) thermography was used to estimate the adiabatic film effectiveness at several blowing ratios and two different freestream turbulence levels (Tu = 0.3% and 6.1%). Convective heat transfer coefficient was measured by a transient IR technique, and the net heat flux benefit was calculated. The total pressure loss due to sweeping jet film cooling was characterized by traversing a total pressure probe at the exit plane of the cascade. Tests were performed with a baseline shaped hole (SH) (777-shaped hole) for comparison. The sweeping jet hole showed higher adiabatic film effectiveness than the 777-shaped hole in the near hole region. Although the unsteady sweeping action of the jet augments heat transfer, the net positive cooling benefit is higher for sweeping jet holes compared to 777 hole at particular flow conditions. The total pressure loss measurement showed a 12% increase in total pressure loss at a blowing ratio of M = 1.5 for sweeping jet hole, while 777-shaped hole showed a 8% total pressure loss increase at the corresponding blowing ratio.

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Figures

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Fig. 1

Wind tunnel and cascade schematic

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Fig. 2

OSU vane schematic and internal cooling architecture

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Fig. 3

Measurement locations

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Fig. 4

Static pressure distribution at the midspan of the OSU vane

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Fig. 5

Contour of nondimensional frequency (St) response of the sweeping jet as a function of massflow rate and peak Strouhal number at different blowing ratios

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Fig. 6

Effect of conduction on laterally averaged film effectiveness for sweeping jet hole at M = 1.0

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Fig. 7

Contours of adiabatic film effectiveness for SJ hole and baseline 777-hole at Tu = 0.3%

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Fig. 8

Contours of adiabatic film effectiveness for SJ hole and baseline 777-hole at Tu = 6.1%

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Fig. 9

Span-averaged film effectiveness for SJ hole and baseline 777-hole at Tu = 0.3%

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Fig. 10

Span-averaged film effectiveness for SJ hole and baseline 777-hole at Tu = 6.1%

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Fig. 11

Lateral distribution of adiabatic film effectiveness for the SJ and 777-shaped holes at x/D = 10 and Tu = 0.3%

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Fig. 12

Area-averaged film effectiveness for the SJ and 777-shaped holes

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Fig. 13

Comparison of area-averaged film effectiveness for the SJ holes to data from Ramesh et al. [22]

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Fig. 14

Contours of convective heat transfer coefficient for the SJ and 777 holes at Tu = 0.3%

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Fig. 15

Area-averaged convective heat transfer coefficient and heat flux ratio for SJ and 777 holes as a function of blowing ratio (M) at Tu = 0.3%

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Fig. 16

Total pressure loss coefficient (γ) of SJ and 777-shaped holes at Tu = 0.3% and 6.1%

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Fig. 17

Span-averaged total pressure loss coefficient (γ¯) of SJ and 777-shaped holes at Tu = 0.3%

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Fig. 18

Area-averaged total pressure loss coefficient (γ¯¯) of SJ and 777-shaped holes at Tu = 0.3% and 6.1% and comparison with the baseline (no cooling) case (γo¯¯)

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