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Overall and blade-element performance of a transonic compressor stage with multiple-circular-arc blades at tip speed of 419 meters per second
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kovich, G. Reid, L. |
| Copyright Year | 1973 |
| Description | A 50-centimeter-diameter axial-flow transonic compressor stage with multiple-circular-arc blades was designed and tested to study the effects of blade shape on efficiency and stall margin. At design speed, peak efficiency of 0.80 occurred at an equivalent weight flow of 29.0 kilograms per second. Measured total pressure ratio and total temperature ratio at peak efficiency were 1.69 and 1.20, respectively. The stall margin at design speed and an equivalent weight flow of 29.0 kilograms per second was 9 percent. The measured stall margin at design weight flow and speed was 15 percent. A comparison of rotor performance made with and without the stator showed a decrease in pressure ratio, peak efficiency, and maximum weight flow with the addition of the stator. |
| File Size | 5679123 |
| Page Count | 113 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730011268 |
| Archival Resource Key | ark:/13960/t9s22r690 |
| Language | English |
| Publisher Date | 1973-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Performance Tests Axial Flow Turbines Turbine Blades Aerodynamic Configurations Compressor Blades Engine Design Transonic Compressors Flow Characteristics Power Efficiency Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
