Reasons for Low Aerodynamic Performance of 13.5-Centimeter-Tip-Diameter Aircraft Engine Starter Turbine.

Abstract

An experimental investigation was made at the NASA Lewis Research Center to determine the reasons for the low aerodynamic performance of a 13.5-centimeter-tip-diameter aircraft engine starter turbine. The investigation consisted of an evaluation of both the stator and the stage. An approximate 10-percent improvement in turbine efficiency was obtained when the honeycomb shroud over the rotor blade tips was filled to obtain a solid shroud surface. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1981
Accession Number
ADA096949

Entities

People

  • Jeffrey E. Haas
  • Paul Hermann
  • Richard J. Roelke

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aircraft Engines
  • Aircrafts
  • Aspect Ratio
  • Blade Tips
  • Diffusers
  • Engine Starters
  • Engines
  • Flow
  • Hypervelocity Flow
  • Instrumentation
  • Load Cells
  • Mass Flow
  • Measurement
  • Reynolds Number
  • Sea Level
  • Static Pressure
  • Strain Gages

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerospace Engineering
  • Structural Dynamics.