Study of Particulated Flows and Erosion in Turbomachinery.

Abstract

This report summarizes the results of an investigation of the solid particle dynamics and the resulting blade erosion through a helicopter engine with inlet particle separator. The particle trajectories are computed in the inlet separator which is characterized by considerable hub and tip contouring and radial variation in the swirling vane shape. The nonseparated particle trajectories are determined through the deswirling vanes and the five stage axial and one stage radial compressors. The impact data for a very large number of ingested particles is used to calculate the resulting blade surface erosion. The erosion pattern indicates the location of maximum blade erosion. In addition, the effect of high temperature on the erosion rate was determined in erosion wind tunnel for AM355 steel and Al2O3 ceramics.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1986
Accession Number
ADA172965

Entities

People

  • Widen Tabakoff

Organizations

  • University of Cincinnati

Tags

Communities of Interest

  • Air Platforms
  • Human Systems

DTIC Thesaurus Topics

  • Aircrafts
  • Axial Flow
  • Axial Flow Compressors
  • Combustion
  • Compressors
  • Engineering
  • Fluid Dynamics
  • Gas Turbines
  • Heat Transfer
  • Helicopter Engines
  • High Temperature
  • Materials
  • Particle Size
  • Turbine Components
  • Turbines
  • Turbomachinery
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerosol Science/Aerosol Physics