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NASA-TN-D-7575
Performance of an asymmetric short annular diffuser with a nondiverging inner wall using suction
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:30:12Z | |
| date available | 2017-09-04T16:30:12Z | |
| date copyright | 01/01/1974 | |
| date issued | 1974 | |
| identifier other | ULBBFEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/93470 | |
| description abstract | The performance of a short highly asymmetric annular diffuser equipped with wall bleed (suction) capability was evaluated at nominal inlet Mach numbers of 0.188, 0.264, and 0.324 with the inlet pressure and temperature at near ambient values. The diffuser had an area ratio of 2.75 and a lengthTo inlet-height ratio of 1.6. Results show that the radial profiles of diffuser exit velocity could be controlled from a severely hub peaked to a slightly tip biased form by selective use of bleed. At the same time, other performance parameters were also improved. These results indicate the possible application of the diffuser bleed technique to control flow profiles to gas turbine combustors. | |
| language | English | |
| title | NASA-TN-D-7575 | num |
| title | Performance of an asymmetric short annular diffuser with a nondiverging inner wall using suction | en |
| type | standard | |
| page | 40 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1974 | |
| contenttype | fulltext | |
| subject keywords | ANNULAR FLOW | |
| subject keywords | COMBUSTION CHAMBERS | |
| subject keywords | FLOW CHARACTERISTICS | |
| subject keywords | FLOW DISTORTION | |
| subject keywords | GAS TURBINES | |
| subject keywords | INLET FLOW | |
| subject keywords | INLET PRESSURE | |
| subject keywords | PERFORMANCE TESTS | |
| subject keywords | PRESSURE DISTRIBUTION |
