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TECHNICAL PAPERS

A Detailed Analysis of Film Cooling Physics: Part IV— Compound-Angle Injection With Shaped Holes

[+] Author and Article Information
R. A. Brittingham, J. H. Leylek

Department of Mechanical Engineering, Clemson University, Clemson, SC 29634

J. Turbomach 122(1), 133-145 (Feb 01, 1997) (13 pages) doi:10.1115/1.555419 History: Received February 01, 1997
Copyright © 2000 by ASME
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References

Figures

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Histogram of cell skewness for 450,000 cell initial grid for FIFF60 case shows high grid quality
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Terminology definitions to be used in the present paper, consistent with the companion papers in Parts I, II, and III
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Schematic of computational model utilized in the present study, showing the plenum, film hole, and crossflow regions with the domain extents and boundary conditions
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Definition of (a) FDIFF60 and (b) LDIFF45 geometries investigated in the present study
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(a) Centerline (z/D=0) adiabatic effectiveness comparison for REF case at M=1.25 demonstrates the consistency of experiments and computations. (b, c) Lateral adiabatic effectiveness distributions for REF case at (b) x/D=3 and (c) x/D=15,M=1.25, show good agreement with experimental data in the near and far fields.
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(a) Lateral averaged adiabatic effectiveness comparison for FDIFF60 case at M=1.25 demonstrates excellent agreement in the near field. (b, c) Lateral adiabatic effectiveness distributions for FDIFF60 case at (b) x/D=3 and (c) x/d=15,M=1.25, shows consistent agreement between experiments and computations.
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Exit-plane VR contours for the (a) REF, (b) FDIFF60, and (c) LDIFF45 cases (M=1.25) show increased complexity for CASH geometries
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Exit-plane discharge α contours for the (a) REF, (b) FDIFF60, and (c) LDIFF45 cases (M=1.25) show the impact of the crossflow on jet trajectory, with actual crossflow ingestion in the FDIFF60 case
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Exit-plane pressure coefficient contours for the (a) REF, (b) FDIFF60, and (c) LDIFF45 cases (M=1.25) show the high-pressure stagnation region on the upstream edge and the low-pressure region on the downstream edge
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Exit-plane discharge Φ contours for the (a) REF, (b) FDIFF60, and (c) LDIFF45 cases (M=1.25) show wide variations in Φ over the exit plane for CASH configurations
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Exit-plane discharge Θ contours for the (a) REF, (b) FDIFF60, and (c) LDIFF45 cases (M=1.25) show the shielding of the low-momentum fluid from the crossflow by the high-momentum jetting fluid in the REF and LDIFF45 cases
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Aft-looking-forward view of TL contours percent on a y–z plane at point O for the (a) REF, (b) FDIFF60, and (c) LDIFF45 cases (M=1.25) show similar turbulence fields for all cases, with a slight increase for the FDIFF60 case due to separation at the start of the film hole diffusing section
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Aft-looking-forward view of x-vorticity contours on a y–z plane located over the hole for the (a) REF, (b) FDIFF60, and (c) LDIFF45 cases (M=1.25) show the negative ξx arch seen in the two CASH cases and the ingestion vortex vorticity for the FDIFF60 case
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Aft-looking-forward view of in-plane velocity vectors on a y–z plane at x/D=2 for the (a) REF, (b) FDIFF60, and (c) LDIFF45 cases (M=1.25) show the collapse of one half of the downstream vortex pair (scale equal on all parts)
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Aft-looking-forward view of pathlines around a constant T=205 K surface for the (a) FDIFF60 and (b) LDIFF45 cases (M=1.25) demonstrate the complex flowfield for both CASH configurations
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Adiabatic effectiveness footprints for the (a) REF, (b) FDIFF60, and (c) LDIFF45 cases (M=1.25) show the excellent lateral distribution for the FDIFF60 case but wide variations for the REF and LDIFF45 cases
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Lateral adiabatic effectiveness distribution for the FDIFF60 case for M=1.25 shows consistent coolant coverage across the pitch
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Lateral adiabatic effectiveness distribution for the LDIFF45 case for M=1.25 shows wide variations in coolant coverage across the pitch
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Lateral averaged adiabatic effectiveness comparison of the REF, FDIFF60, and LDIFF45 cases shows the superior downstream performance of the FDIFF60 configuration
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Lateral averaged heat transfer coefficients for the REF and LDIFF45 cases show an increase in heat transfer coefficient with the increased geometric complexity for both blowing ratios
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Lateral averaged adiabatic effectiveness comparison for different geometry types at M=1.25 highlights the effects of compound-angle injection and hole shaping

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