Design of Advanced Blading for a High-Speed HP Compressor Using an S1-S2 Flow Calculation System.

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 S1-S2 flow calculation system, developed at RAE Pyestock, which incorporates an inviscid viscour blade to blade code. The design and measured performance of the 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.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1990
Accession Number
ADA235355

Entities

People

  • A. J. Britton
  • I. R. Mckenzie
  • Judith M. Parker
  • R. B. Ginder
  • W. J. Calvert

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Loading
  • Axial Flow
  • Boundary Layer
  • Compressors
  • Computational Science
  • Flow
  • Flow Fields
  • Instrumentation
  • Layers
  • Mach Number
  • Mass Flow
  • Measurement
  • Pressure Gradients
  • Shape
  • Three Dimensional
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Quantum Chemistry