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Performance of a single-stage axial-flow transonic compressor stage with a blade tip solidity of 1.7
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Reid, L. Moore, R. D. |
| Copyright Year | 1972 |
| Description | The overall and blade-element performance of a transonic compressor stage is presented over the stable operating range at rotative speeds from 50 to 100 percent of design speed. Stage peak efficiency of 0.784 was obtained at a weight flow of 28.6 kilograms per second and a pressure ratio of 1.706. Stall margin at design speed was 11.4 percent. The peak efficiency being significantly less than design efficiency was attributed to: (1) the stator loss and the radial gradient of losses being much higher than design, (2) the losses and blockages associated with the rotor part-span dampers not being incorporated into the design, and (3) mismatch of the rotor and stator badle elements. |
| File Size | 5316006 |
| Page Count | 113 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730006256 |
| Archival Resource Key | ark:/13960/t0ns5hq23 |
| Language | English |
| Publisher Date | 1972-12-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Equipment Specifications Turbocompressors Air Flow Performance Tests Axial Flow Turbines Turbine Wheels Compressor Efficiency Transonic Speed Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
