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

Abstract

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 polytropic 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.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1991
Accession Number
ADA236450

Entities

People

  • R. B. Ginder

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Accuracy
  • Boundaries
  • Boundary Layer
  • Boundary Layer Transition
  • Computational Science
  • Flow
  • Flow Fields
  • Gas Turbines
  • Layers
  • Leading Edges
  • Mach Number
  • Measurement
  • Reynolds Number
  • Three Dimensional
  • Trailing Edges
  • Turbines
  • Turbomachinery

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Systems Analysis and Design