Accession Number:

ADA162432

Title:

Research on Aero-Thermodynamic Distortion Induced Structural Dynamic Response of Multi-Stage Compressor Blading.

Descriptive Note:

Annual rept. 16 Apr 83-15 Apr 84,

Corporate Author:

PURDUE UNIV LAFAYETTE IN SCHOOL OF MECHANICAL ENGINEERING

Personal Author(s):

Report Date:

1984-06-01

Pagination or Media Count:

60.0

Abstract:

The structural dynamic response of turbomachinery components to aero-thermodynamic distortion induced excitations is of major concern in the design of advanced gas turbine engines. The rotor speeds at which these resonant forced responses occur can be predicted with Campbell diagrams. However, due to the inadequacies of the existing time-variant aerodynamic models, no accurate prediction can currently be made for the amplitude of the resulting stresses. The overall objective of this research program is to quantitatively investigate the fundamental phenomena relevant to aerothermodynamic distortion induced structural dynamic blade response in multi-stage gas turbine fans and compressors. Progress during this reporting period includes the calibration of stator vanes instrumented with dynamic pressure transducers the completion and verification of the steady and dynamic data acquisition and analysis procedures the check-out and initial experimental study of the first state vane row unsteady aerodynamics the initiation of the development of the dynamic instrumentation and calibration procedures for the rotor studies and the completion of the structural dynamics portion of the coupled mode blade vibration energy balance structural dynamics math model. Keywords Turbomachinery structural dynamic response Unsteady aerodynamics and Aerothermodynamic distortion.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE