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Research Papers

Experimental and Numerical Investigation of Sweeping Jet Film Cooling

[+] Author and Article Information
Mohammad A. Hossain

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

Robin Prenter

Department of Mechanical and
Aerospace Engineering,
Aerospace Research Center,
The Ohio State University,
Columbus, OH 43235
e-mail: prenter.1@osu.edu

Ryan K. Lundgreen

Department of Mechanical and
Aerospace Engineering,
Aerospace Research Center,
The Ohio State University,
Columbus, OH 43235
e-mail: ryanlundgreen@gmail.com

Ali Ameri

Department of Mechanical and
Aerospace Engineering,
Aerospace Research Center,
The Ohio State University,
Columbus, OH 43235
e-mail: ameri.1@osu.edu

James W. Gregory

Department of Mechanical and
Aerospace Engineering,
Aerospace Research Center,
The Ohio State University,
Columbus, OH 43235
e-mail: gregory.234@osu.edu

Jeffrey P. Bons

Department of Mechanical and
Aerospace Engineering,
Aerospace Research Center,
The Ohio State University,
Columbus, OH 43235
e-mail: bons.2@osu.edu

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 29, 2017; final manuscript received November 11, 2017; published online December 28, 2017. Editor: Kenneth Hall.

J. Turbomach 140(3), 031009 (Dec 28, 2017) (13 pages) Paper No: TURBO-17-1202; doi: 10.1115/1.4038690 History: Received October 29, 2017; Revised November 11, 2017

A companion experimental and numerical study was conducted for the performance of a row of five sweeping jet (SJ) film cooling holes consisting of conventional curved fluidic oscillators with an aspect ratio (AR) of unity and a hole spacing of P/D = 8.5. Adiabatic film effectiveness (η), thermal field (θ), convective heat transfer coefficient (h), and discharge coefficient (CD) were measured at two different freestream turbulence levels (Tu = 0.4% and 10.1%) and four blowing ratios (M = 0.98, 1.97, 2.94, and 3.96) at a density ratio of 1.04 and hole Reynolds number of ReD = 2800. Adiabatic film effectiveness and thermal field data were also acquired for a baseline 777-shaped hole. The SJ film cooling hole showed significant improvement in cooling effectiveness in the lateral direction due to the sweeping action of the fluidic oscillator. An unsteady Reynolds-averaged Navier–Stokes (URANS) simulation was performed to evaluate the flow field at the exit of the hole. Time-resolved flow fields revealed two alternating streamwise vortices at all blowing ratios. The sense of rotation of these alternating vortices is opposite to the traditional counter-rotating vortex pair (CRVP) found in a “jet in crossflow” and serves to spread the film coolant laterally.

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Figures

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Fig. 2

Wind tunnel schematic

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Fig. 1

Fluidic oscillator schematic and sequence of switching mechanism [21]

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Fig. 3

Test-plate configuration

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Fig. 4

Schematic of the fluidic oscillator test module

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Fig. 5

Baseline 777-shaped hole geometry

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Fig. 6

Surface temperature and thermal field measurement locations

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Fig. 7

(a) Frequency response as a function of massflow without freestream flow and (b) time-averaged spreading angle without freestream flow (massflow = 0.39 g/s)

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Fig. 8

Contour of adiabatic film effectiveness for the SJ hole and baseline 777-hole at Tu = 0.4%

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Fig. 9

Contour of adiabatic film effectiveness for the SJ hole and baseline 777-hole at Tu = 10.1%

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Fig. 10

Span-averaged adiabatic film effectiveness for the SJ hole and 777-shaped hole at Tu = 0.4%

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Fig. 11

Span-averaged adiabatic film effectiveness for the SJ hole and 777-shaped hole at Tu = 10.1%

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Fig. 12

Spanwise adiabatic film effectiveness for the SJ hole and 777-shaped hole at x/D = 10 and Tu = 0.4%

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Fig. 13

Spanwise adiabatic film effectiveness for the SJ hole and 777-shaped hole at x/D = 10 and Tu = 10.1%

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Fig. 14

Area-averaged effectiveness for the SJ and 777-hole as a function of blowing ratio

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Fig. 15

Thermal field at Tu = 0.4% and x/D = 6 for the SJ and 777-hole

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Fig. 16

Thermal field for the SJ hole at x/D = 10 for Tu = 0.4% and 10.1%

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Fig. 17

Area-averaged convective heat transfer coefficient and heat flux ratio for the SJ hole and the 777-shaped hole as a function of blowing ratio (M) at Tu = 10.1%

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Fig. 18

Discharge coefficient (CD) of the SJ and 777-shaped holes as a function of blowing ratio

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Fig. 21

CFD prediction of the streamwise vorticity at x/D = 6 at a range of blowing ratios (0.97<M<2.94) for the SJ and 777-shaped holes

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Fig. 19

Computational domain and grid

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Fig. 20

Oscillation frequency as a function of blowing ratio (and massflow) from computational fluid dynamics (CFD) and experiment

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Fig. 22

CFD prediction of time-accurate streamwise vorticity over a half-oscillation of the SJ hole at x/D = 6 for a blowing ratio of 1.97

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