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Effects of reset stators and a rotating, grooved stator hub on performance of a 1.92-pressure-ratio compressor stage
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lewis Jr., G. W. Urasek, D. C. Reid, L. |
| Copyright Year | 1977 |
| Description | The overall performance and blade-element performance of a transonic fan stage are presented for two modified test configurations and are compared with the unmodified stage. Tests were conducted with reset stators 2 deg open and reset stators with a rotating grooved stator hub. Detailed radial and circumferential (behind stator) surveys of the flow conditions were made over the stable operating range at rotative speeds of 70, 90, and 100 percent of design speed. Reset stator blade tests indicated a small increase in stage efficiency, pressure ratio, and maximum weight flow at each speed. Performance with reset stators and a rotating, grooved stator hub resulted in an additional increase in stage efficiency and pressure ratio at all speeds. The rotating grooved stator hub reduced hub losses considerably. |
| File Size | 7265376 |
| Page Count | 94 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770010055 |
| Archival Resource Key | ark:/13960/t87h6cr01 |
| Language | English |
| Publisher Date | 1977-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Turbocompressors Calibrating Turbofans Compressor Efficiency Transonic Compressors Stators Air Breathing Engines Rotor Blades Hubs Axial Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
