Accession Number:

AD0856225

Title:

Propulsion System Flow Stability Program (Dynamic). Part XIII. Numerical Definition of Engine Face Distortion.

Descriptive Note:

Final technical rept. on Phase 1,

Corporate Author:

NORTH AMERICAN ROCKWELL CORP LOS ANGELES CA LOS ANGELES DIV

Personal Author(s):

• Martin, Arnold W.

Report Date:

1968-12-01

Pagination or Media Count:

35.0

Abstract:

Those steady-state and dynamic distortion factors which, through test or analysis, have been found to reduce compressor surge margin have been listed and the probable mechanisms by which they influence the compressor have been discussed. A multi-termed format has been derived for a numerical definition of distortion. Its definition and use are described. Recommendations for further analytic and experimental investigations into the mechanisms of compressor surge are presented. Author

Descriptors:

• (*TURBOJET ENGINES
• AXIAL FLOW COMPRESSORS)
• (*AXIAL FLOW COMPRESSORS
• STALLING)
• DISTORTION
• TURBULENCE
• OSCILLATION
• ACOUSTICS
• TURBOJET INLETS
• TURBULENT BOUNDARY LAYER
• INTERACTIONS
• RESPONSE

Subject Categories:

• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE