Research on Aero-Thermodynamic Distortion Induced Structural Dynamic Response of Multi-Stage Compressor Blading.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 15, 1988
- Accession Number
- ADA192169
Entities
People
- Sanford Fleeter
Organizations
- Purdue University