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

Abstract

Current developments included: (1) A coordination meeting was held to discuss installation and performance problems. New installation drawings and updated performance data including tables and IBM decks for both the STF 219 turbofan and STJ 227 turbojet engine were completed. (2) Scaled envelope drawings and IBM performance decks for the 525 lb/sec afterburning turbojet engine were made. (3) The endurance testing of full-size air-cooled blades was continued in the turbine development engine. Two-hundred hours of steady state endurance testing were accumulated on a set of convectively cooled blades at a turbine inlet temperature of 2300 F with a blade cooling air temperature of 1200 F. (4) Sound tests were continued on a large-scale blow-in-door ejector nozzle installed on a J-57 afterburning engine. Tests were completed on the standard configuration and with simulated scoops and mixers installed. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 10, 1965
Accession Number
AD0367976

Entities

Organizations

  • Pratt & Whitney

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Cooled
  • Air Temperature
  • Aircraft Engines
  • Aircrafts
  • Engines
  • Gas Turbine Nozzles
  • Jet Aircraft
  • Steady State
  • Supersonic Transport Aircraft
  • Transport Aircraft
  • Turbines
  • Turbofan Engines
  • Turbojet Engines

Readers

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

Technology Areas

  • Hypersonics