Investigation of Thermal Fatigue in Non-Tubular Regeneratively Cooled Thrust Chambers. Volume 2

Abstract

Long life non-tubular teneratively cooled thrust chambers were fabricated and hot-fire cyclic tested to verify the life prediction techniques established in Volume I of this report. Chambers incorporating copper alloy (NARLoy-Z and zirconium copper) and nickel for the hot gas wall material and electroformed nickel closures were fabricated by Rocketdyne and hot fire cyclic tested by Rocketdyne and hot fire cyclic tested by the AFRPL. Propellants were LO2/H2 at a nominal mixture ratio of 6:1. Chamber pressure was 750 psia and thrust (corrected to vacuum and with a full area ratio nozzle) was 3300 pounds. A calorimeter thrust chamber assembly (calorimeter thrust chamber and coaxial injector) were also fabricated and hot-fire tested to establish the heat flux profile. Post-test analysis and metallurgical evaluation of the chamber were performed to locate and define fatigue cracks.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1973
Accession Number
AD0760583

Entities

People

  • D. Fultons

Tags

Communities of Interest

  • Advanced Electronics
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Combustion
  • Coolants
  • Copper Alloys
  • Cyclic Tests
  • Design Criteria
  • Fabrication
  • Grain Size
  • Heat Transfer
  • Materials
  • Rocket Engines
  • Rocket Propulsion
  • Standards
  • Surface Roughness
  • Test And Evaluation
  • Test Facilities
  • Test Methods

Readers

  • Combustion and Flow Dynamics.
  • Rocket Propulsion.
  • Structural Health Monitoring of Composite Structures.