Unsteady Aerodynamic Damping Measurement of Annular Turbine Cascade With High Deflection in Transonic FlowSource: Journal of Turbomachinery:;1990:;volume( 112 ):;issue: 004::page 732Author:H. Kobayashi
DOI: 10.1115/1.2927716Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Unsteady aerodynamic forces acting on oscillating blades of a transonic annular turbine cascade were investigated in both aerodynamic stable and unstable domains, using a Freon gas annular cascade test facility. In the facility, whole blades composing the cascade were oscillated in the torsional mode by a high-speed mechanical drive system. In the experiment, the reduced frequency K was changed from 0.056 to 0.915 with a range of outlet Mach number M 2 from 0.68 to 1.39, and at a constant interblade phase angle. Unsteady aerodynamic moments obtained by two measuring methods agreed well. Through the moment data the phenomenon of unstalled transonic cascade flutter was clarified as well as the significance of K and M 2 for the flutter. The variation of flutter occurrence with outlet flow velocity in the experiments showed a very good agreement with theoretical analysis.
keyword(s): Cascades (Fluid dynamics) , Damping , Turbines , Deflection , Transonic flow , Flutter (Aerodynamics) , Blades , Flow (Dynamics) , Mach number , Aerodynamics , Mechanical drives , Test facilities AND Theoretical analysis ,
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| contributor author | H. Kobayashi | |
| date accessioned | 2017-05-08T23:34:01Z | |
| date available | 2017-05-08T23:34:01Z | |
| date copyright | October, 1990 | |
| date issued | 1990 | |
| identifier issn | 0889-504X | |
| identifier other | JOTUEI-28606#732_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/107699 | |
| description abstract | Unsteady aerodynamic forces acting on oscillating blades of a transonic annular turbine cascade were investigated in both aerodynamic stable and unstable domains, using a Freon gas annular cascade test facility. In the facility, whole blades composing the cascade were oscillated in the torsional mode by a high-speed mechanical drive system. In the experiment, the reduced frequency K was changed from 0.056 to 0.915 with a range of outlet Mach number M 2 from 0.68 to 1.39, and at a constant interblade phase angle. Unsteady aerodynamic moments obtained by two measuring methods agreed well. Through the moment data the phenomenon of unstalled transonic cascade flutter was clarified as well as the significance of K and M 2 for the flutter. The variation of flutter occurrence with outlet flow velocity in the experiments showed a very good agreement with theoretical analysis. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Unsteady Aerodynamic Damping Measurement of Annular Turbine Cascade With High Deflection in Transonic Flow | |
| type | Journal Paper | |
| journal volume | 112 | |
| journal issue | 4 | |
| journal title | Journal of Turbomachinery | |
| identifier doi | 10.1115/1.2927716 | |
| journal fristpage | 732 | |
| journal lastpage | 740 | |
| identifier eissn | 1528-8900 | |
| keywords | Cascades (Fluid dynamics) | |
| keywords | Damping | |
| keywords | Turbines | |
| keywords | Deflection | |
| keywords | Transonic flow | |
| keywords | Flutter (Aerodynamics) | |
| keywords | Blades | |
| keywords | Flow (Dynamics) | |
| keywords | Mach number | |
| keywords | Aerodynamics | |
| keywords | Mechanical drives | |
| keywords | Test facilities AND Theoretical analysis | |
| tree | Journal of Turbomachinery:;1990:;volume( 112 ):;issue: 004 | |
| contenttype | Fulltext |