Research Papers

An Experimental and Numerical Investigation on the Effects of Aerothermal Mixing in a Confined Oblique Jet Impingement Configuration

[+] Author and Article Information
Sebastian Schulz

Institute of Aerospace Thermodynamics,
University of Stuttgart,
Pfaffenwaldring 31,
Stuttgart 70569, Germany
e-mail: sebastian.schulz@itlr.uni-stuttgart.de

Alexander Schindler

Institute of Aerospace Thermodynamics,
University of Stuttgart,
Pfaffenwaldring 31,
Stuttgart 70569, Germany
e-mail: alexander.schindler@itlr.uni-stuttgart.de

Jens von Wolfersdorf

Institute of Aerospace Thermodynamics,
University of Stuttgart,
Pfaffenwaldring 31,
Stuttgart 70569, Germany
e-mail: itljvw@itlr.uni-stuttgart.de

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 30, 2015; final manuscript received October 29, 2015; published online January 5, 2016. Editor: Kenneth C. Hall.

J. Turbomach 138(4), 041007 (Jan 05, 2016) (10 pages) Paper No: TURBO-15-1216; doi: 10.1115/1.4032022 History: Received September 30, 2015; Revised October 29, 2015

An investigation to characterize the effect of entrainment in a confined jet impingement arrangement is presented. The investigated configuration shows an impingement-cooled turbine blade passage and holds two staggered rows of inclined impingement jets. In order to distinctly promote thermal entrainment phenomena, the jets were heated separately. A steady-state liquid crystal technique was used to obtain near-wall fluid temperature distributions for the impingement surfaces under adiabatic conditions. Additionally, flow field measurements were undertaken using particle image velocimetry (PIV). Furthermore, compressible Reynolds-averaged Navier–Stokes (RANS) simulations carried out with ansys cfx using Menter's shear stress transport (SST) turbulence model accompany the experiments. Distributions of effectiveness, velocity, and turbulent kinetic energy detail the complexity of the aerothermal situation. The study was conducted for a jet Reynolds number range from 10,000 to 45,000. The experimental and numerical results are generally in good agreement. Nevertheless, the simulations predict flow features in particular regions of the geometry that are not as prominent in the experiments. These affect the effectiveness distributions, locally. The investigations reveal that the effectiveness is independent of the temperature difference between the heated and cold jet as well as the jet Reynolds number.

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Fig. 1

Concept for an impingement-cooled, midchord passage of a turbine blade, adapted from Ref. [20]

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Fig. 2

Schematics of the test rig (a) and the experimental facility (b)

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Fig. 7

Illustration of streamlines (a) experiment and (b) CFD simulation

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Fig. 6

Computational domain with boundary conditions: inlet/outlet (red), symmetry (yellow), and adiabatic walls (blue)

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Fig. 5

Example of the TLC's green color isotherms at specific jet total temperatures for ReD = 45,000 for (a) wall D and (b) wallC

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Fig. 4

Illustration of the AOI in the PIV and TLC measurements

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Fig. 3

Schematic of the test geometry

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Fig. 8

Local distributions of (a) time-averaged velocity, (b) vorticity magnitude, and (c) turbulent kinetic energy for ReD = 10,000, from experiments

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Fig. 9

Local distributions of (a) time-averaged velocity, (b) vorticity magnitude, and (c) turbulent kinetic energy for ReD = 10,000, from CFD

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Fig. 10

Adiabatic effectiveness distributions for ReD = 10,000 (top) and ReD = 45,000 (bottom), from experiments

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Fig. 11

Adiabatic effectiveness distributions for ReD = 10,000 (top) and ReD = 45,000 (bottom), from CFD

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Fig. 12

Laterally averaged ηaw-distributions for walls (a) C and (b) D, (c) local ηaw-distribution for wall C

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Fig. 13

Laterally averaged ηaw-distributions for impingement wall C for different liquid crystal temperatures (Tlc)



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