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Effect of variable-position inlet guide vanes and interstage bleed on compressor performance of a high-pressure-ratio turbojet engine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1956 |
| Description | Increased guide-vane turning resulted in poorer overall performance, the decrease being greatest at the highest rotor speed. Rotating stall originating at the tips of the first stage correlated with the knee in the stall-limit line. Increasing guide-vane turning shifted the first-stage stall-free performance and the knee in the stall-limit line to a lower engine speed. Opening the interstage bleed reduced the minimum rotor speed at which stall-free performance of the first stage was possible and tended to eliminate the knee in the stall-limit line. |
| File Size | 3002878 |
| Page Count | 27 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930088889 |
| Archival Resource Key | ark:/13960/t86h98z66 |
| Language | English |
| Publisher Date | 1956-12-28 |
| Access Restriction | Open |
| Subject Keyword | 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 |
