Passive control of aerodynamically forced vibrations of supersonic turbomachine rotors by splitter bladesAn aeroelastic model is developed to examine the use of splitter blades as a passive detuning mechanism for flow induced forced response of unstalled supersonic turbomachine rotors. The splitters introduce aerodynamic and structural detuning to the rotor design. The relationship between aerodynamic and structural detuning and the location and chord lengths of splitters is analyzed. The model is applied to the flow induced response of four 12-blade rotors with Verdon's (1973) Cascade B flow geometry. The data reveal that for gusts characterized by forward and backward traveling waves the splitters generally decrease the maximum amplitudes of response; however, for some gust load interblade phase angles, such as -180 deg and 120 deg the splitters did not reduce the amplitudes of response.
Document ID
19860054154
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fleeter, S. (Purdue Univ. West Lafayette, IN, United States)
Topp, D. A. (Purdue University West Lafayette, IN, United States)
Hoyniak, D. (NASA Lewis Research Center Cleveland, OH, United States)