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

Abstract

The second build of engine FX-161 was completed and delivered to test on 14 May. Testing was terminated on 20 May, after 2.08 hours (total time 13.76 hours) because of over-temperature indications from the instrumented 1st-stage turbine vanes and evidence of distress of the transition duct. Several burned areas in the transition duct were found during disassembly inspection. This problem has been attributed to the airflow out of the individual starting bleed valves, which caused (1) disturbance of the air in the annulus outside the combustor, thereby locally reducing the cooling air to the transition duct; and (2) hot spots on the transition duct due to locally higher fuel/air ratios. The third build of engine FX-161 and the first build of engine FX-162 are being modified to utilize the diffuser bleed manifold for high compressor bleed. Both engines are scheduled to be mounted for test in mid-June. The rebuild of the high compressor rig using recambered stators showed a slight improvement of the high speed surge pressure ratio.

Document Details

Document Type
Technical Report
Publication Date
Jun 10, 1966
Accession Number
AD0376670

Entities

Organizations

  • Pratt & Whitney

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircraft Engines
  • Aircrafts
  • Combustors
  • Compressors
  • Diffusers
  • Disassembly
  • Engines
  • Hot Spots
  • Inspection
  • Jet Aircraft
  • Supersonic Aircraft
  • Supersonic Transport Aircraft
  • Transitions
  • Transport Aircraft

Readers

  • Aerospace Engineering
  • Combustion and Flow Dynamics.
  • Military and Counterinsurgency Studies.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers