| contributor author | R. E. Kielb | |
| contributor author | J. K. Ramsey | |
| date accessioned | 2017-05-08T23:31:18Z | |
| date available | 2017-05-08T23:31:18Z | |
| date copyright | October, 1989 | |
| date issued | 1989 | |
| identifier issn | 0889-504X | |
| identifier other | JOTUEI-28598#462_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/106137 | |
| description abstract | An application of a simple aeroelastic model to an advanced supersonic axial flow fan is presented. Lane’s cascade theory is used to determine the unsteady aerodynamic loads. Parametric studies are performed to determine the effects of mode coupling, Mach number, damping, pitching axis location, solidity, stagger angle, and mistuning. The results show that supersonic axial flow fan and compressor blades are susceptible to a strong torsional mode flutter having critical reduced velocities that can be less than one. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Flutter of a Fan Blade in Supersonic Axial Flow | |
| type | Journal Paper | |
| journal volume | 111 | |
| journal issue | 4 | |
| journal title | Journal of Turbomachinery | |
| identifier doi | 10.1115/1.3262294 | |
| journal fristpage | 462 | |
| journal lastpage | 467 | |
| identifier eissn | 1528-8900 | |
| keywords | Flutter (Aerodynamics) | |
| keywords | Axial flow | |
| keywords | Blades | |
| keywords | Damping | |
| keywords | Mach number | |
| keywords | Compressors | |
| keywords | Stress AND Cascades (Fluid dynamics) | |
| tree | Journal of Turbomachinery:;1989:;volume( 111 ):;issue: 004 | |
| contenttype | Fulltext | |
