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

Abstract

Assembly of the first experimental engine has been completed. An initial check run was made to idle thrust on 31 March 1966. Starting was smooth and operation at idle revealed no functional problems. The rebuilt high compressor rig was tested over the full speed range with vane positions set to the first experimental engine schedule. No significant stresses were encountered. The full-scale duct heater rig testing has continued at high fuel-air ratios at sea level conditions. High performance levels were achieved at fuel-air ratios up to 0.04. Testing of the 0.62-scale fan rig with recambered 1st- and 2nd-stage blades showed a significant improvement in engine surge margin; however, this was accompanied by a reduction in airflow at high corrected speeds. The rig was rebuilt with the original 1st-stage blades (build No. 5), and is being tested to evaluate the recambered 2nd-stage blade independently. Assembly of the JTF17A-20 engine installation mockup was completed, and it was delivered 15 March.

Document Details

Document Type
Technical Report
Publication Date
Apr 10, 1966
Accession Number
AD0376676

Entities

Organizations

  • Pratt & Whitney

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircraft Engines
  • Aircrafts
  • Assembly
  • Compressors
  • Engine Surge
  • Engines
  • Fuel Air Ratio
  • Jet Aircraft
  • Sea Level
  • Supersonic Aircraft
  • Supersonic Transport Aircraft
  • Transport Aircraft
  • Transport Ships

Readers

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

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow