WEAPON SYSTEM 107A-2. PRODUCT ENGINEERING PROGRAM

Abstract

The objective of this project is to develop a reliable thermal barrier capable of surface temperature operation above 3300 F for use on regeneratively-cooled thrust chambers employing Aerozine-50/N2O4 propellant. Thermal barrier film-coating is a technique for improving liquid rocket engine performance by reducing film-cooling flow rates. During this period the YLR91 AJ-5 thrust chamber has been shipped to test area C to undergo three tests at the planned 17% fuel film cooling flow rate for duration of 5, 10, and 15 sec. A design study is underway to determine the best means for modifying an unbaffled in jector to give 5% fuel film cooling for all sub sequent tests.

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Document Details

Document Type
Technical Report
Publication Date
Jul 16, 1963
Accession Number
AD0409879

Entities

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Combustion
  • Combustion Chambers
  • Engineering
  • Exhaust Gases
  • Fabrication
  • Film Cooling
  • Films
  • Flow Rate
  • Heat Transfer
  • Jet Propulsion
  • Materials
  • Materials Processing
  • Physics Laboratories
  • Rocket Engines
  • Test And Evaluation
  • Thrust Chambers

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Software Engineering
  • Thermal Physics or Thermal Science.