Investigation of a 1500 ft/sec, Transonic, High-through-Flow, Single- Stage Axial-Flow Compressor with Low Hub/Tip Ratio
Abstract
Complete experimental results are presented from tests of an axial compressor stage designed for a flow per frontal area of 39.7 lb/sec/ft square, a total pressure ratio of 1.912 and a tip speed of 1500 ft/sec. The performance objectives of this stage were derived from a preliminary design study of a multi-stage compressor for an advanced turbojet engine. Since the most serious aerodynamic design problems of the over-all compressor were observed to be associated with the first stage, this stage was chosen as the subject of a research program. Results of the tests indicated that, at design speed, design flow was achieved with a rotor isentropic efficiency of 90.4 percent, a stage isentropic efficiency of 88.2 percent and a stage total pressure ratio of 2.065.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1976
- Accession Number
- ADB016506
Entities
People
- Arthur J. Wennerstrom
- C. Herbert Law
- Robert D. Derose
- William A. Buzzell
Organizations
- Air Force Research Laboratory