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Effect of inducer inlet and diffuser throat areas on performance of a low pressure ratio sweptback centrifugal compressor
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Klassen, H. A. |
| Copyright Year | 1975 |
| Description | A low-pressure-ratio centrifugal compressor was tested with nine combinations of three diffuser throat areas and three impeller inducer inlet areas which were 75, 100, and 125 percent of design values. For a given inducer inlet area, increases in diffuser area within the range investigated resulted in increased mass flow and higher peak efficiency. Changes in both diffuser and inducer areas indicated that efficiencies within one point of the maximum efficiency were obtained over a compressor specific speed range of 27 percent. The performance was analyzed of an assumed two-spool open-cycle engine using the 75 percent area inducer with a variable area diffuser. |
| File Size | 1035415 |
| Page Count | 28 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750005797 |
| Archival Resource Key | ark:/13960/t59d1qf5d |
| Language | English |
| Publisher Date | 1975-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Performance Tests Centrifugal Compressors Low Pressure Engine Inlets Gas Turbine Engines Performance Prediction Diffusers Engine Tests Intake Systems Mass Flow 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 |
