论文信息 - Design and Performance of Advanced Blading for a High-Speed HP Compressor

Design and Performance of Advanced Blading for a High-Speed HP Compressor

A set of advanced blading has been designed for a 5-stage high-speed research core compressor. The blade profiles were aerodynamically-tailored using a sophisticated quasi-3D S1-S2 flow calculation system which was developed at RAE Pyestock. This system involves iteration between blade-to-blade calculations using an inviscid-viscous code, and a streamline-curvature calculation for the pitchwise-averaged throughflow. The design and measured performance of the new compressor are compared with an initial conventionally-bladed 4-stage version. The new design achieved a peak level of poly tropic efficiency approaching 91%, a substantial improvement on the initial version, but showed a shortfall in pressure ratio compared with design intent. Post-test analyses based on measured performance data are used to give further insight into this result and indicate possible improvements in the design approach.Copyright © 1991 by ASME

R. B. Ginder

[1] J. Denton. Loss Mechanisms in Turbomachines , 1993 .

[2] William N. Dawes,et al. A Comparison of Zero and One Equation Turbulence Modelling for Turbomachinery Calculations , 1990 .

[3] R. B. Ginder,et al. Performance of a Highly-Loaded HP Compressor , 1989 .

[4] William N. Dawes,et al. Development of a 3D Navier Stokes Solver for Application to all Types of Turbomachinery , 1988 .

[5] W. J. Calvert. An Inviscid-Viscous Interaction Treatment to Predict the Blade-to-Blade Performance of Axial Compressors With Leading Edge Normal Shock Waves , 1982 .