Accession Number : ADA192169
Title : Research on Aero-Thermodynamic Distortion Induced Structural Dynamic Response of Multi-Stage Compressor Blading.
Descriptive Note : Final technical rept. Apr 83-Nov 87,
Corporate Author : PURDUE UNIV LAFAYETTE IND THERMAL SCIENCES AND PROPULSION CENTER
Personal Author(s) : Fleeter, Sanford
PDF Url : ADA192169
Report Date : 15 Jan 1988
Pagination or Media Count : 237
Abstract : The overall objective of this research program was to quantitatively investigate the fundamental phenomena relevant to aero-thermodynamic distortion induced structural dynamic blade responses in multi-stage gas turbine engine components. The technical approach involved both experiment and analysis. (1) The flow physics of multi-stage blade row interactions has been experimently investigated, with unique high reduced frequency unsteady aerodynamic data obtained to understand, quantify, and discriminate the fundamental flow phenomena as well as to direct the modeling of advanced analyses. (2) The development of an unsteady viscous flow analysis appropriate for aerodynamic forced response predictions was initiated. (3) A structural dynamics model based on an energy balance techniques coupled with the unsteady aerodynamic analyses under development is being utilized to investigate aerodynamically forced response of turbomachine blade rows. Keywords: Gas turbine, Aeroelasticity structural dynamics, Unsteady aerodynamics.
Descriptors : *AERODYNAMICS, *AEROELASTICITY, *BLADES, *DYNAMICS, *PREDICTIONS, AERODYNAMIC CHARACTERISTICS, AERODYNAMIC FORCES, BALANCE, ENERGY, FLOW, GAS TURBINES, METHODOLOGY, MODELS, PHYSICS, RESPONSE, STRUCTURAL PROPERTIES, TURBOMACHINERY, UNSTEADY FLOW, VISCOUS FLOW
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE