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TECHNICAL PAPERS

Inverse Design of and Experimental Measurements in a Double-Passage Transonic Turbine Cascade Model

[+] Author and Article Information
G. M. Laskowski

Flow Physics and Computation Division & Thermosciences Division, Department of Mechanical Engineering,  Stanford University, Stanford, CA 94305gmlaska@sandia.gov

A. Vicharelli, G. Medic, C. J. Elkins, J. K. Eaton, P. A. Durbin

Flow Physics and Computation Division & Thermosciences Division, Department of Mechanical Engineering,  Stanford University, Stanford, CA 94305

J. Turbomach 127(3), 619-626 (Jan 12, 2005) (8 pages) doi:10.1115/1.1929810 History: Received September 09, 2003; Revised January 12, 2005

A new transonic turbine cascade model that accurately produces infinite cascade flow conditions with minimal compressor requirements is presented. An inverse design procedure using the Favre-averaged Navier-Stokes equations and kε turbulence model based on the method of steepest descent was applied to a geometry consisting of a single turbine blade in a passage. For a fixed blade geometry, the passage walls were designed such that the surface isentropic Mach number (SIMN) distribution on the blade in the passage matched the SIMN distribution on the blade in an infinite cascade, while maintaining attached flow along both passage walls. An experimental rig was built that produces realistic flow conditions, and also provides the extensive optical access needed to obtain detailed particle image velocimetry measurements around the blade. Excellent agreement was achieved between computational fluid dynamics (CFD) of the infinite cascade SIMN, CFD of the designed double passage SIMN, and the measured SIMN.

Copyright © 2005 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematic of double-passage nozzle and test section

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Figure 2

Initial geometry and definitions of terminology used (not to scale)

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Figure 3

Computational grid used in infinite cascade simulations (not to scale)

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Figure 4

Mach number contours for infinite cascade simulation (not to scale)

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Figure 5

SIMN corresponding to Fig. 4 plotted against the blade surface coordinate nondimensionalized by the blade axial chord where 0→+s∕cxl is the blade suction side from the stagnation point to the trailing edge and 0→−s∕cxl is the blade pressure side from the stagnation point to the trailing edge

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Figure 6

SIMN for the initial geometry using stagnation streamlines (refer to Fig. 5 for explanation of the abscissa axis)

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Figure 7

SIMN for the initial geometry with separation along pressure wall (refer to Fig. 5 for explanation of the abscissa axis)

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Figure 8

Separation along pressure wall (not to scale)

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Figure 9

Initial versus final wall geometries for the first design (not to scale)

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Figure 10

SIMN corresponding to Fig. 9, without separation along pressure wall (refer to Fig. 5 for explanation of the abscissa axis)

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Figure 11

Convergence history

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Figure 12

Initial versus final wall geometries for the final design (not to scale)

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Figure 13

SIMN corresponding to Fig. 1 (refer to Fig. 5 for explanation of the abscissa axis)

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Figure 14

Shear stress comparison for the final design (refer to Fig. 5 for explanation of the abscissa axis)

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Figure 15

Comparison between CFD-IC and CFD-DP for the final design: Mach number contour comparison (not to scale)

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