Research on Aero-Thermodynamic Distortion Induced Structural Dynamic Response of Multi-Stage Compressor Blading.
Final rept. 15 Apr 82-14 Apr 83,
PURDUE UNIV LAFAYETTE IN SCHOOL OF MECHANICAL ENGINEERING
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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.
- Fluid Mechanics
- Jet and Gas Turbine Engines