Research on Aero-Thermodynamic Distortion Induced Structural Dynamic Response of Multistage Compressor Blading
Final rept. Nov 1987-May 1991,
PURDUE UNIV LAFAYETTE IN SCHOOL OF MECHANICAL ENGINEERING
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This report summarizes the results obtained on Contract F49620-88-C-0022. The overall objective of this basic research program was the quantitative investigation of the fundamental phenomena relevant to aero-thermodynamic distortion induced structural dynamic blade responses in multistage gas turbine engines. The technical approach involved unique benchmark experiments and also analyses. In particular, the flow physics of multistage blade row interactions were investigated, with unique unsteady aerodynamic data obtained and analyses developed to understand, quantify, and discriminate the fundamental flow phenomena as well as to direct the modeling of advanced analyses. Data obtained define the flow interactions and the effects on both the aerodynamic forcing function and the resulting unsteady aerodynamics of compressor rotor blades and stator vanes in a multistage environment over a wide range of realistic reduced frequency values for the first time.