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High loading, 1800 ft/sec tip speed, transonic compressor fan stage. 2: final report
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Sulam, D. H. Morris, A. L. |
| Copyright Year | 1972 |
| Description | Tests were conducted on a 0.5 hub/tip ratio, single-stage fan-compressor designed to produce a pressure ratio of 2.285 an efficiency of 84 percent with a rotor tip speed of 1800 feet per second. A peak efficiency of 82 percent was achieved by the stage at a stall margin of 6.5 percent. Tests showed that stall-limit line was slightly sensitive to tip-radial distortion, but stall-line improvements were noted when the stage was subjected to circumferential and hub-radial flow distortions. Rotor blade passage and trailing edge shock positions were inferred from static pressure contours over the rotor tips. |
| File Size | 17917939 |
| Page Count | 234 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730006068 |
| Archival Resource Key | ark:/13960/t6h17sf0f |
| Language | English |
| Publisher Date | 1972-12-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Air Flow Performance Tests Gas Turbines Turbine Blades Engine Design Turbine Wheels Flow Characteristics Systems Analysis 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 |
