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Experimental performance of a 13.65-centimeter-tip-diameter tandem-bladed sweptback centrifugal compressor designed for a pressure ratio of 6
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wood, J. R. Schumann, L. F. Klassen, H. A. |
| Copyright Year | 1977 |
| Description | A 13.65 cm tip diameter backswept centrifugal impeller having a tandem inducer and a design mass flow rate of 0.907 kg/sec was experimentally investigated to establish stage and impeller characteristics. Tests were conducted with both a cascade diffuser and a vaneless diffuser. A pressure ratio of 5.9 was obtained near surge for the smallest clearance tested. Flow range at design speed was 6.3 percent for the smallest clearance test. Impeller exit to shroud axial clearance at design speed was varied to determine the effect on stage and impeller performance. |
| File Size | 1047088 |
| Page Count | 30 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780003059 |
| Archival Resource Key | ark:/13960/t8cg4hd29 |
| Language | English |
| Publisher Date | 1977-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Static Pressure Performance Tests Centrifugal Compressors Mass Flow Rate Cascades Impellers Gas Turbine Engines Pressure Distribution Pressure Measurement Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
