Research on Aero-Thermodynamic Distortion Induced Structural Dynamic Response of Multi-Stage Compressor Blading.
Abstract
The structural dynamic response of turbomachinery components to aerothermodynamic distortion induced excitations is of major concern in the design of advanced gas turbine engines. Rotor speeds at which these resonant forced responses occur can be predicted with Campbell diagrams. However, due to inadequacies of existing time-variant aerodynamic models, no accurate prediction can be made for the amplitude of the resulting vibrations and stresses. Therefore, this research program seeks to quantitatively investigate the fundamental phenomena relevant to aero thermodynamic distortion induced structural dynamic blade responses in multi-stage gas-turbine engine components. Flow physics of multi-stage blade row interactions is being experimentally investigated, with unique unsteady aerodynamic data obtained to understand, quantify, and discriminate the fundamental flow phenomena as well as to direct the modeling of advanced analyses. Data are being obtained to define both the potential and viscous flow interactions and the effect on the aerodynamic forcing function and the resulting unsteady aerodynamics of both rotor blades and stator vanes. Analytically, a first principles capability to predict the vibrational response of blading due to aerodynamic excitations is being developed. Unsteady viscous flow analyses, appropriate for aerodynamic forced response predictions, are also being developed. Recent progress includes: stationary vane row experiments in a research compressor which investigate the fundamental multi-stage blade row interaction aerodynamics; and identification and modeling of a vortex street in the instantaneous wakes of rotor blades.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1986
- Accession Number
- ADA175904
Entities
People
- Sanford Fleeter
Organizations
- Purdue University