Study of Particulated Flows and Erosion in Turbomachinery.
Final rept. 14 Dec 81-30 Jun 86,
CINCINNATI UNIV OH DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS
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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.
- Jet and Gas Turbine Engines