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Research Papers: Jets, Wakes, and Impingment Cooling

Stress-Blended Eddy Simulation of Coherent Unsteadiness in Pressure Side Film Cooling Applied to a First Stage Turbine Vane

[+] Author and Article Information
Silvia Ravelli

Department of Engineering and
Applied Sciences,
University of Bergamo,
Marconi Street 5,
Dalmine 24044, Italy
e-mail: silvia.ravelli@unibg.it

Giovanna Barigozzi

Department of Engineering and
Applied Sciences,
University of Bergamo,
Marconi Street 5,
Dalmine 24044, Italy
e-mail: giovanna.barigozzi@unibg.it

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received August 10, 2017; final manuscript received March 19, 2018; published online May 22, 2018. Assoc. Editor: Danesh K. Tafti.

J. Heat Transfer 140(9), 092201 (May 22, 2018) (14 pages) Paper No: HT-17-1461; doi: 10.1115/1.4039763 History: Received August 10, 2017; Revised March 19, 2018

Within the framework of scale resolving simulation techniques, this paper considers the application of the stress-blended eddy simulation (SBES) model to pressure side (PS) film cooling in a high-pressure turbine nozzle guide vane. The cooling geometry exhibits two rows of film cooling holes and a trailing edge cutback, fed by the same plenum chamber. The blowing conditions investigated were in the range of coolant-to-mainstream mass flow ratio (MFR) from 1% to 2%. The flow regime resembles that in a real engine (exit isentropic Mach number of Ma2is = 0.6), but also low speed conditions (Ma2is = 0.2) were considered for comparison purposes. The predicted results were validated with measurements of surface adiabatic effectiveness and instantaneous off-wall visualizations of the flow field downstream of cooling holes and cutback slot. The focus is on SBES ability of developing shear layer structures, because of their strong influence on velocity field, entrainment mechanisms and, thus, vane surface temperature. Special attention has been paid to the development and dynamics of coherent unsteadiness, since measured values of shedding frequency were also available for validation. SBES provided significant improvement in capturing the unsteady physics of cooling jet-mainstream interaction. The effects of changes in flow regime and blowing conditions on vortex structures were well predicted along the cutback surface. As regards the cooling holes, the high speed condition made it difficult to match the experimental Kelvin–Helmholtz breakdown in the shear layer, in the case of high velocity jets.

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Figures

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Fig. 1

Views of the vane with pressure side film cooling (size in mm) [34]

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Fig. 2

Three-dimensional computational domain and boundary conditions

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Fig. 3

Midspan distribution of (a) adiabatic wall temperature Taw and (b) y+ for different levels of grids—Ma2is = 0.6, MFR = 1.79%

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Fig. 4

Contours of the shielding function fSBES (left) and CFL number (right) at Z/Zspan = 0.33 and 0.5—Ma2is = 0.6, MFR = 1.79%

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Fig. 5

Case I (Ma2is = 0.6, MFR = 1.79%): flow visualizations (top) and SBES instantaneous predictions of normalized temperature contours θ and spanwise vorticity at Z/Zspan = 0.33 (left) and Z/Zspan = 0.5 (right)

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Fig. 6

Case I (Ma2is = 0.6, MFR = 1.79%): flow visualization (top) and SBES instantaneous predictions of normalized temperature contours θ and spanwise vorticity at Z/Zspan = 0.5, downstream of the slot exit

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Fig. 7

Case II (Ma2is = 0.6, MFR = 1.25%): flow visualizations (top) and SBES instantaneous predictions of normalized temperature contours θ and spanwise vorticity at Z/Zspan = 0.33 (left) and Z/Zspan = 0.5 (right)

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Fig. 8

Case II (Ma2is = 0.6, MFR = 1.25%): flow visualization (top) and SBES instantaneous predictions of normalized temperature contours θ and spanwise vorticity at Z/Zspan = 0.5, downstream of the slot exit

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Fig. 9

Measurements (exp.) and predictions (SBES versus RANS) of the laterally averaged adiabatic effectiveness ηav downstream of the cooling holes (left) and along the cutback surface (right), at Ma2is = 0.6, for various MFR values

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Fig. 10

Case III (Ma2is = 0.2, MFR = 1.95%): flow visualizations (top) and SBES instantaneous predictions of normalized temperature contours θ and spanwise vorticity at Z/Zspan = 0.33 (left) and Z/Zspan = 0.5 (right)

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Fig. 11

Case III (Ma2is = 0.2, MFR = 1.95%): flow visualization (top) and SBES instantaneous predictions of normalized temperature contours θ and spanwise vorticity at Z/Zspan = 0.5, downstream of the slot exit

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Fig. 12

Case IV (Ma2is = 0.2, MFR = 1.10%): flow visualizations (top) and SBES instantaneous predictions of normalized temperature contours θ and spanwise vorticity at Z/Zspan = 0.33 (left) and Z/Zspan = 0.5 (right)

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Fig. 13

Case IV (Ma2is = 0.2, MFR = 1.10%): flow visualization (top) and SBES instantaneous predictions of normalized temperature contours θ and spanwise vorticity at Z/Zspan = 0.5, downstream of the slot exit

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Fig. 14

Measurements (exp.) and predictions (SBES versus RANS) of the laterally averaged adiabatic effectiveness ηav downstream of the cooling holes (left) and along the cutback surface (right), at Ma2is = 0.2, for various MFR values

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Fig. 15

Measurements (exp.) and predictions (SBES, URANS, SAS, and DDES) of the laterally averaged adiabatic effectiveness ηav along the cutback surface at Ma2is = 0.2, for lower (left) and higher (right) MFR

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