| contributor author | N. M. McDougall | |
| contributor author | N. A. Cumpsty | |
| contributor author | T. P. Hynes | |
| date accessioned | 2017-05-08T23:34:11Z | |
| date available | 2017-05-08T23:34:11Z | |
| date copyright | January, 1990 | |
| date issued | 1990 | |
| identifier issn | 0889-504X | |
| identifier other | JOTUEI-28600#116_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/107794 | |
| description abstract | Detailed measurements have been made of the transient stalling process in an axial compressor stage. The stage is of high hub-casing ratio and stall is initiated in the rotor. If the rotor tip clearance is small stall inception occurs at the hub, but at clearances typical for a multistage compressor the inception is at the tip. The crucial quantity in both cases is the blockage caused by the endwall boundary layer. Prior to stall, disturbances rotate around the inlet flow in sympathy with rotating variations in the endwall blockage; these can persist for some time prior to stall, rising and falling in amplitude before the final increase, which occurs as the compressor stalls. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Stall Inception in Axial Compressors | |
| type | Journal Paper | |
| journal volume | 112 | |
| journal issue | 1 | |
| journal title | Journal of Turbomachinery | |
| identifier doi | 10.1115/1.2927406 | |
| journal fristpage | 116 | |
| journal lastpage | 123 | |
| identifier eissn | 1528-8900 | |
| keywords | Compressors | |
| keywords | Stall inception | |
| keywords | Rotors | |
| keywords | Clearances (Engineering) | |
| keywords | Boundary layers | |
| keywords | Flow (Dynamics) AND Measurement | |
| tree | Journal of Turbomachinery:;1990:;volume( 112 ):;issue: 001 | |
| contenttype | Fulltext | |
