PARTIAL ALTITUDE MILITARY QUALIFICATION TEST OF THE TF37-GE-1 TURBOFAN ENGINE

Abstract

A partial altitude military qualification test of the TF37-GE-1 turbofan engine was conducted in accordance with the procedures outlined in MIL- E-5009B dated January 1958. Steady-state and/or transient data were obtained at flight conditions in the altitude range from sea level to 36,000 ft and in the Mach number range from 0 to 1.0 with standard, hot, and cold atmospheres. The steady-state engine performance in terms of net thrust and specific fuel consumption was equal to or better than the rated performance. Windmill starts and simulated flameouts and relights at altitudes up to 26,000 ft were successfully accomplished. The qualification test was terminated prior to completion because of compressor damage caused by foreign object ingestion.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1966
Accession Number
AD0628775

Entities

People

  • C. E. Chamblee
  • J. R. Evans

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Human Systems
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Altitude
  • Calorific Value
  • Compressors
  • Engines
  • Gas Flow
  • Gas Turbines
  • Generators
  • Guide Vanes
  • Mach Number
  • Measurement
  • Sea Level
  • Steady State
  • Strain Gages
  • Turbines
  • Turbofan Engines
  • Turbojet Engines

Readers

  • Aerospace Engineering
  • Technical Research and Report Writing.