Experimental Determination of the Relative Flow at the Tip of a Transonic Axial Compressor Rotor.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1983
- Accession Number
- ADA137483
Entities
People
- D. W. Cornell
Organizations
- Naval Postgraduate School