Research On Aero Thermodynamic Distortion Induced Structural Dynamic Response Of Multi Stage Compressor Blading
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Research on Aero-Thermodynamic Distortion Induced Structural Dynamic Response of Multi-Stage Compressor Blading
The overall objective of this research is to quantitatively investigate the fundamental phenomena relevant to aerothermodynamic distortion-induced structural dynamic blade response in multi-stage gas turbine fans and compressors. Unique unsteady aerodynamic data will be obtained to validate and indicate necessary refinements to state-of-the-art analyses and to direct the modeling of new analyses. Also, for the first time, a first principles capability to predict the vibrational response amplitude of blading due to aerodynamic excitations will be developed. Progress and results obtained during the first year of this program. Include: the dynamic instrumentation of the first-stage vane row of a three-stage research compressor; the design, specification, and initiation of the development of the dynamic data acquisition and analysis system; the initiation of the development of the necessary data analysis and calibration techniques; and the theoretical development of a unique coupled mode structural dynamic blade response analysis based on an energy balance technique.