Accession Number:

ADA175090

Title:

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

Descriptive Note:

Annual summary rept. 16 Apr 84-15 May 85,

Corporate Author:

PURDUE UNIV LAFAYETTE IN SCHOOL OF MECHANICAL ENGINEERING

Personal Author(s):

Report Date:

1985-07-01

Pagination or Media Count:

46.0

Abstract:

The flow physics of multi-stage blade row interactions is being investigated. Unique data are being obtained to define the potential and viscous flow interactions and the effect on the aerodynamic forcing function and the unsteady aerodynamics of both rotors and stators. Analytically, a first principles capability to predict the vibrational response of blading is being developed. Also, unsteady viscous flow analyses for aerodynamic forcing response predictions are being developed. Progress during this reporting period include vane row experiments which investigate fundamental blade row aerodynamics interactions the identification and modeling of a vortex street structure in the instantaneous rotor wakes preparations for rotating blade row experiments the developement and application of a locally analytic numerical method for steady viscous flows the formulation of an unsteady incompressible viscous thin airfoil theory. Keywords Unsteady aerodynamics, Aeroelasticity, Forced vibrations, Gas turbines, Turbomachinery.

Subject Categories:

  • Fluid Mechanics
  • Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE