DEVELOPMENT OF A SUPERSONIC TRANSPORT AIRCRAFT ENGINE - PHASE II-B.

Abstract

The basic design airflow of the STF-219 engine was changed to 650 lbs/sec. New ejector and installation concepts aimed at reducing drag and improving the over-all installation were examined. The effect of changing the engine from a 700 lb/sec to a 650 lb/sec size was discussed. Endurance testing of full-size air-cooled blades was resumed in the JT4 high spool engine. Twenty-five hours of endurance testing were completed on a set of unshrouded convectively-cooled blades at a turbine inlet temperature of 2300 F and a blade cooling air temperature of 1200 F. A blow-in-door-ejector nozzle was being fabricated in preparation for ground tests on a J57 afterburning engine to determine the effect of this nozzle configuration on exhaust noise radiation. Fabrication of parts for the two-stage fan rig was started and proceeding on schedule. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 15, 1965
Accession Number
AD0367974

Entities

Organizations

  • Pratt & Whitney

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Cooled
  • Air Temperature
  • Aircraft Engines
  • Aircrafts
  • Engines
  • Gas Turbine Nozzles
  • Nozzles
  • Supersonic Transport Aircraft
  • Transport Aircraft

Readers

  • Aerospace Engineering
  • Combustion and Flow Dynamics.
  • Software Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow