Cold-Air Performance of Compressor-Drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. II. Stage Performance.

Abstract

The aerodynamic performance of the compressor-drive turbine of the DOE Upgraded Gas Turbine (UGT) engine was determined in low-temperature air. The nominal turbine-inlet temperature was 320 K. Inlet pressures were varied between 0.4 and 2.4 bars absolute. The turbine blading used in these tests consisted of duplicates of the stator and rotor castings used in development engine tests. The as-received cast rotor blades had a significantly thicker profile than design and a fairly rough surface finish. Because of these blade profile imperfections three turbine rotor configurations were evaluated. These were the as-cast rotor, a reduced-roughness rotor, and a rotor with the blade profiles thinned to near the design profile. Tests to determine the effect of Reynolds number on the turbine performance were also made. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1982
Accession Number
ADA121041

Entities

People

  • Jeffrey E. Haas
  • Richard J. Roelke

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aspect Ratio
  • Boundary Layer
  • Computer Programs
  • Finishes
  • Flow
  • Gas Turbines
  • Instrumentation
  • Manufacturing
  • Mass Flow
  • Measurement
  • Reynolds Number
  • Sea Level
  • Static Pressure
  • Surface Roughness
  • Trailing Edges
  • Turbine Components
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Polymer Science and Engineering.