0
TECHNICAL PAPERS

High Lift and Aft-Loaded Profiles for Low-Pressure Turbines

[+] Author and Article Information
R. J. Howell, O. N. Ramesh, H. P. Hodson

Whittle Laboratory, University of Cambridge, Cambridge, United Kingdom

N. W. Harvey

Rolls Royce plc., Derby, United Kingdom

V. Schulte

BMW Rolls-Royce, GmbH, Dahlewitz, Germany

J. Turbomach 123(2), 181-188 (Feb 01, 2000) (8 pages) doi:10.1115/1.1350409 History: Received February 01, 2000
Copyright © 2001 by ASME
Your Session has timed out. Please sign back in to continue.

References

Wisler, D. C., 1998, “The Technical and Economic Relevance of Understanding Boundary Layer Transition in Gas Turbine Engines,” Minnowbrook II, 1998 Workshop on Boundary Layer Transition in Turbomachines, NASA/CP-1998-206958.
Curtis,  E. M., Hodson,  H. P., Banieghbal,  M. R., Denton,  J. D., Howell,  R. J., and Harvey,  N. W., 1997, “Development of Blade Profiles for Low-Pressure Turbine Applications,” ASME J. Turbomach., 119, pp. 531–538.
Hourmouziadis, J., 1989, “Aerodynamic Design of Low Pressure Turbines,” AGARD Conf. Proc. LS-167, June.
Schulte,  V., and Hodson,  H. P., 1998, “Unsteady Wake-Induced Boundary Layer Transition in Highly Loaded LP Turbines,” ASME J. Turbomach., 120, pp. 28–35.
Schubauer, G. B., and Klebanoff, P. S., 1955, “Contributions on the Mechanism of Boundary-Layer Transition,” NACA TN 3489.
Schulte, V., 1995, “Unsteady Wake Boundary Layer Interaction,” Ph.D. thesis, Cambridge University, England.
Banieghbal, M. R., Curtis, E. M., Denton, J. D., Hodson, H. P., Huntsman, I., Schulte, V. S., and Harvey, N. W., 1995, “Wake Passing in LP Turbines,” AGARD Conf. Proc. No. 23.
Hodson,  H. P., 1985, “An Inviscid Blade-to-Blade Prediction of a Wake-Generated Unsteady Flow,” ASME J. Eng. Gas Turbines Power, 107, pp. 337–344.
Bearman, P. W., 1971, “Correction for the Effect of Ambient Temperature Drift on Hot-Wire Measurements in Incompressible Flow,” DISA Inf. No. 11, pp. 25, 30.
Bellhouse,  B. L., and Schultz,  D. L., 1966, “Determination of Mean and Dynamic Skin Friction Separation and Transition in Low-Speed Flow With a Thin-Film Heated Element,” J. Fluid Mech., 24, No. 2.
Hodson,  H. P., 1984, “Boundary Layer and Loss Measurements on the Rotor of an Axial-Flow Turbine,” ASME J. Eng. Gas Turbines Power, 106, pp. 391–399.
Davies, M. R. D., and Duffy, J. T., 1995, “A Semi-empirical Theory for Surface Mounted Aerodynamic Wall Shear Stress Gages,” ASME Paper No. 95-GT-193.
Denton, J. D., 1993, “Entropy Generation in Turbomachinery Flows,” 7th Cliff Garrett Turbomachinery Award Lecture, SAE Paper No. 902011.
Howell, R. J., 1999, “Wake Separation Bubble Interaction on Low Reynolds Number Turbomachinery,” Ph.D. thesis, Cambridge University, England.
Arndt,  N., 1993, “Blade Row Interaction in a Multistage Low-Pressure Turbine,” ASME J. Turbomach., 115, pp. 137–146.

Figures

Grahic Jump Location
Schematic of moving bar rig and cascade
Grahic Jump Location
Schematic of flap and inserts used in the cascade
Grahic Jump Location
Pressure distributions of datum profile and others with increased lift measured at a Reynolds number of 130,000, with unsteady airflow
Grahic Jump Location
Relative trailing edge suction side boundary layer momentum thickness variation with Reynolds number for datum profile
Grahic Jump Location
Variation in loss with increased lift, with and without wakes, at a Reynolds number of 130,000
Grahic Jump Location
ST diagram of wake-induced transition showing two different reduced frequencies
Grahic Jump Location
Aft-loaded and datum pressure distributions; all measurements carried out at Re=130,000 and with wakes present
Grahic Jump Location
Variation of losses with position of peak suction
Grahic Jump Location
ST diagram of nondimensional ensemble mean quasi-shear stress data from profiles H and C at a Reynolds number of 130,000, and flow coefficient of 0.7
Grahic Jump Location
Relative suction side boundary losses for aft-loaded profiles measured with and without wakes present; Re=130,000
Grahic Jump Location
Velocity distributions for the ultrahigh lift profiles, U1 and U2, and the datum profile H; all distributions measured with unsteady inflow; velocities are made nondimensional using the cascade exit velocity; Re=130,000
Grahic Jump Location
Nondimensional total pressure loss variation versus Reynolds number for the datum and ultrahigh lift cascades

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In