Blade Row Interaction Unsteady Aerodynamics and Variability for Aeromechanics and HCF

Abstract

This research is directed at the development of the technology needed to accurately predict significant blade row forced response in a multistage environment. Specific objectives include addressing design and off-design blade row interaction unsteady aerodynamics including unsteady aerodynamic variability. The technical approach requires that blade row interaction unsteady aerodynamic data be acquired and analyzed for realistic geometries and flow conditions. Thus, experiments are performed in the Purdue Transonic Research Compressor Facility. It features a 1-1/2 stage axial-flow geometry representative of that used in the front stages of advanced high-pressure compressors including advanced controlled diffusion airfoil (CDA) designed in cooperation with Pratt & Whitney. Note that this compressor design was directed at transonic blade row interaction unsteady aerodynamics and HCF studies.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2004
Accession Number
ADA435470

Entities

People

  • Sanford Fleeter

Organizations

  • Purdue Research Foundation

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aerodynamics
  • Axial Flow
  • Boundary Layer
  • Compressors
  • Computational Fluid Dynamics
  • Diffusion
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • High Pressure
  • High Pressure Compressors
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Unsteady Aerodynamics

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Systems Analysis and Design
  • Technical Research and Report Writing.