Development and Testing of Ablative Rocket Engine with Selected 7.62-Centimeter (3.0 IN.) Diameter Throat Inserts.

Abstract

Five injector configurations were designed and the performance evaluated in a nitrogen tetroxide - 50-percent blend of unsymmetrical dimethyl-hydrazine and hydrazine propellant rocket engine. A triplet injector modified for 0/F zoning provided combustion efficiency of over 95 percent. Selected throat inserts (7. 62 cm (3. 0 in.) in diameter) were tested to demonstrate long-term firing duration and restart capability. The duty cycle chosen was an initial 300-second firing, five 20-second firings and a final 300-second firing. The best throat insert material tested was zirconia reinforced with tungsten-rhenium wire. Scale-up to larger throat sizes is discussed.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1971
Accession Number
ADA305315

Entities

People

  • Albert J. Pavli
  • Arthur M. Shinn Jr.
  • Donald A. Peterson
  • Jerry M. Winter

Organizations

  • Glenn Research Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Ablative Materials
  • Assembly
  • Chambers
  • Combustion
  • Erosion Resistance
  • Failure Mode And Effect Analysis
  • Heat Sinks
  • Heat Transfer
  • Materials
  • Resistance
  • Rocket Engines
  • Rocket Oxidizers
  • Steady State
  • Temperature Gradients
  • Tensile Strength
  • Test Facilities
  • Thrust Chambers

Readers

  • Powder metallurgy of Titanium alloys.
  • Rocket Propulsion.