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Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78, respectively, and with design pressure ratio of 1.82
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Reid, L. Moore, R. D. |
| Copyright Year | 1982 |
| Description | The overall and blade-element performance of a transonic compressor stage is presented over the stable operating flow range for speeds from 50 to 100 percent of design. The stage was designed for a pressure ratio of 1.82 at a flow 20.2 kg/sec and a tip speed of 455 m/sec. At design speed the stage achieved a peak efficiency of 0.821 at a pressure ratio of 1.817. The stage stall margin at design speed based on conditions at stall and peak efficiency was about 11 percent. |
| File Size | 4607292 |
| Page Count | 115 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820011348 |
| Archival Resource Key | ark:/13960/t3rv5cs95 |
| Language | English |
| Publisher Date | 1982-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Compressor Rotors Compressor Blades Transonic Compressors Rotor Aerodynamics Pressure Ratio Stator Blades Turbomachinery Intake Systems Aspect Ratio Aerodynamic Characteristics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
