Accession Number : ADA137483

Title :   Experimental Determination of the Relative Flow at the Tip of a Transonic Axial Compressor Rotor.

Descriptive Note : Engineers thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : Cornell,D W

PDF Url : ADA137483

Report Date : Sep 1983

Pagination or Media Count : 224

Abstract : The goal in the present work was to examine the flow through the tip section of a transonic compressor rotor in three different ways: (1) using high response instrumentation in the compressor itself, (2) using a blow-down wind tunnel model of the relative flow at the rotor tip, and (3) using a new computer analysis code. Toward that goal, the present study reports the results of extensive measurements made in the compressor and software developed to acquire and reduce high response transducer data. Modifications made to the cascade and first results of applying S. Eidelman's Godunov code to the compressor rotor tip section are also included. It was concluded that a valid comparison of computed and measured results required both an improvement of the compressor in-flow and an extension of the analysis code to include three dimensional effects. (Author)

Descriptors :   *Compressor rotors, Axial flow compressors, Rotor blades(turbomachinery), Transonic flow, Supersonic flow, Measurement, Wind tunnel models, Blowdown, Transonic wind tunnels, Pressure distribution, Computerized simulation, Experimental design, Pressure transducers, Analog to digital converters, Flow rate, Sampling, Real time, Synchronism, Data acquisition, Computer programs, Numerical methods and procedures, Theses

Subject Categories : Test Facilities, Equipment and Methods
      Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE