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Performance of a low-pressure-ratio centrifugal compressor with four diffuser designs
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Klassen, H. A. |
| Copyright Year | 1973 |
| Description | A low-pressure-ratio centrifugal compressor was tested with four different diffuser configurations. One diffuser had airfoil vanes. Two were pipe diffusers. One pipe diffuser had 7.5 deg cone diffusing passages. The other had trumpet-shaped passages designed for linear static-pressure rise from throat to exit. The fourth configuration had flat vanes with elliptical leading edges similar to those of pipe diffusers. The side walls were contoured to produce a linear pressure rise. Peak compressor efficiencies were 0.82 with the airfoil vane and conical pipe diffusers, 0.80 with the trumpet, and 0.74 with the flat-vane design. Surge margin and useful range were greater for the airfoil-vane diffuser than for the other three. |
| File Size | 1015435 |
| Page Count | 28 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730011270 |
| Archival Resource Key | ark:/13960/t8gf5k85r |
| Language | English |
| Publisher Date | 1973-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Static Pressure Performance Tests Centrifugal Compressors Low Pressure Vanes Airfoils Diffusers Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
