Aerodynamic Design of Symmetrical Blading for Three-Stage Axial Flow Compressor Test Rig.
Abstract
The report deals with the aerodynamic design of an axial compressor stage with symmetrical bladings for a research program to investigate tip clearance effects in a three-stage compressor. It establishes the blading data and the stage performance with an iterative three-dimensional approach, and gives criteria for the drive and the flow measuring device of the test unit. The calculated distributions of the flow properties in the stage will be used for future comparisons with test data. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1970
- Accession Number
- AD0714585
Entities
People
- Michael H. Vavra
Organizations
- Naval Postgraduate School