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TECHNICAL PAPERS

On Flowfield Periodicity in the NASA Transonic Flutter Cascade

[+] Author and Article Information
J. Lepicovsky

QSS Group, Inc., Cleveland, OH 44135

R. V. Chima, E. R. McFarland, J. R. Wood

NASA Glenn Research Center, Cleveland, OH 44135

J. Turbomach 123(3), 501-509 (Feb 01, 2000) (9 pages) doi:10.1115/1.1378300 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Buffum,  D. H., Capece,  V. R., King,  A. J., and El-Aini,  Y. M., 1998, “Oscillating Cascade Aerodynamics at Large Mean Incidence,” ASME J. Turbomach., 120, pp. 122–130; also NASA TM-107247.
Buffum, D. H., Capece, V. R., King, A. J., and El-Aini, Y. M., 1996, “Experimental Investigation of Unsteady Flows at Large Incidence Angles in a Linear Oscillating Cascade,” AIAA Paper No. 96-2823; also NASA TM-107283.
Lepicovsky, J., McFarland, E. R., Chima, R. V., and Wood, J. R., “On Flowfield Periodicity in the NASA Transonic Flutter Cascade: Part I—Experimental Study,” ASME Paper No. 2000-GT-572.
Chima, R. V., McFarland, E. R., Wood, J. R., and Lepicovsky, J., 2000, “On Flowfield Periodicity in the NASA Transonic Flutter Cascade: Part II—Numerical Study,” ASME Paper No. 2000-GT-573.
Boldman, D. R., and Buggele, A. E., 1978, “Wind Tunnel Tests of a Blade Subjected to Midchord Torsional Oscillations at High Subsonic Stall Flutter Conditions,” NASA TM-78998.
Shaw,  L. M., Boldman,  D. R., Buggele,  A. E., and Buffum,  D. H., 1986, “Unsteady Pressure Measurements on a Biconvex Airfoil in a Transonic Oscillating Cascade,” ASME J. Eng. Gas Turbines Power, 108, pp. 53–59.
Buffum, D. H., and Fleeter, S., 1991, “Wind Tunnel Wall Effects in a Linear Oscillating Cascade,” NASA TM-103690.
Buffum, D. H., and Fleeter, S., 1988, “Investigation of Oscillating Cascade Aerodynamics by an Experimental Influence Coefficient Technique,” NASA TM-101313.
Ott, P., Norryd, M., and Bölcs, A., 1998, “The Influence of Tailboards on Unsteady Measurements in a Linear Cascade,” ASME Paper No. 98-GT-572.
Boldman, D. R., and Buggele, A. E., 1983, “Experimental Evaluation of Shockless Supercritical Airfoils in Cascade,” AIAA Paper No. 83-0003.
Bencic, T. J., 1995, “Experience Using Pressure Sensitive Paint in NASA Lewis Research Center Propulsion Test Facilities,” AIAA Paper No. 95-2831.
Lepicovsky, J., Bencic, T. C., and Bruckner, R. J., 1997, “Application of Pressure Sensitive Paint to Confined Flow at Mach Number 2.5,” AIAA Paper No. 97-3214.
McFarland, E. R., 1993, “An Integral Equation Solution for Multistage Turbomachinery Design Calculations,” ASME Paper No. 93-GT-41.
McFarland, E. R., 1994, “Use of Preliminary Design Methods in the Analysis of Multi-Stage Turbomachinery,” NASA CP 3282, Vol. 2.
Chima,  R. V., 1987, “Explicit Multigrid Algorithm for Quasi-Three-Dimensional Viscous Flows in Turbomachinery,” J. Propul. Power, 3, No. 5, pp. 397–405.
Chima, R. V., 1995, “A k–ω Turbulence Model for Quasi-Three-Dimensional Turbomachinery Flows,” AIAA Paper No. 96-0248; also NASA TM-107051.

Figures

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Boundary layer bleed system of the NASA transonic flutter cascade facility
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View of cascade test section
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Effect of incidence angle on pressure coefficient compute with RVCQ3D
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Cascade configuration C_20.0/30.0
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Effects of sidewall boundary layer bleed rate
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Effects of sidewall bleed on spanwise Mach number distribution at y/W=0.388 and x/C=−0.254
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Effects of sidewall bleed on spanwise distribution of flow incidence angles at y/W=0.388 and x/C=−0.254
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Effects of sidewall bleed on blade loading
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Cascade flowfield for Mach number 1.35
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Mach contours computed with PCSTAGE for original configuration C_20.0/30.0
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Cascade turning angle versus inlet Mach number computed with RVCQ3D
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Particle traces computed with RVCQ3D
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Cascade configuration C_20.0/24.0
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Mach contours computed with PCSTAGE for final configuration C_20.0/24.0
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Wall static distributions for cascade configuration C_20.0/24.0
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Blade loading diagrams for middle blade (B5) for cascade configuration C_20.0/24.0
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Blade loading periodicity for configuration C_20.0/24.0

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