| contributor author | J. A. King | |
| date accessioned | 2017-05-09T01:08:25Z | |
| date available | 2017-05-09T01:08:25Z | |
| date copyright | July, 1961 | |
| date issued | 1961 | |
| identifier issn | 1528-8919 | |
| identifier other | JETPEZ-26617#291_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/154945 | |
| description abstract | The J83 turbojet engine was a high-performance, lightweight engine with a maximum thrust of 2450 lb, a diameter of 18 in., and a weight of approximately 300 lb. The compressor for this engine was a seven-stage, transonic, axial-flow compressor with an inlet tip diameter of 15.2 in. and a hub-lip ratio of 0.433. Details of the aero-thermodynamic design of this compressor and the problems encountered during its development are given in this paper. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | The J83 Seven-Stage Transonic Compressor | |
| type | Journal Paper | |
| journal volume | 83 | |
| journal issue | 3 | |
| journal title | Journal of Engineering for Gas Turbines and Power | |
| identifier doi | 10.1115/1.3673190 | |
| journal fristpage | 291 | |
| journal lastpage | 301 | |
| identifier eissn | 0742-4795 | |
| keywords | Compressors | |
| keywords | Engines | |
| keywords | Weight (Mass) | |
| keywords | Thrust | |
| keywords | Design | |
| keywords | Axial flow AND Turbojets | |
| tree | Journal of Engineering for Gas Turbines and Power:;1961:;volume( 083 ):;issue: 003 | |
| contenttype | Fulltext | |
