Single-Stage Axial Compressor Component Development for Small Gas Turbine Engines. Volume II. Rotor Development
Abstract
The report describes the development of the rotor for the 2.8:1 single stage supersonic axial compressor design. The rotor performance was evaluated through experimental testing with the inlet guide vanes but without the exit stator. The experimental results are analyzed and compared to the design data and criteria. Although a circumferential flow distortion at the rotor exit prevented a very accurate assessment of the performance potential, the data provided ample evidence that the rotor performance goals could be met with uniform exit conditions. The presence of the exit stator during the stage development tests in the subsequent phase was expected to reduce the flow distortion at the rotor exit to near uniform conditions.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1969
- Accession Number
- AD0857627
Entities
People
- Charles H. Muller
- Leslie R. Cox