Characterization of Stall Inception in High-Speed Single-Stage Compressors.

Abstract

All aircraft gas turbine engines currently compromise compression system performance at some point(s) in their operating envelope to obtain 'adequate' stall margin. This work pursues the concept of active stall control to minirnize or eliminate this penalty, thereby improving the performance of any aircraft gas turbine engine.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1994
Accession Number
ADA291275

Entities

People

  • Keith Boyer

Organizations

  • Wright Laboratory

Tags

Communities of Interest

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

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Boundary Layer
  • Compressors
  • Computational Science
  • Engines
  • Fluid Mechanics
  • Fourier Analysis
  • Gas Turbines
  • Literature Surveys
  • Measurement
  • Pressure Measurement
  • Steady State
  • Test Facilities
  • Three Dimensional
  • Turbine Components
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering