Test Results of the RS-44 Integrated Component Evaluator Liquid Oxygen/ Hydrogen Rocket Engine

Abstract

An advanced LOX/LH2 expander cycle rocket engine, producing 15,000 Ibf thrust for Orbital Transfer Vehicle missions, was tested to determine ignition, transition, and main stage characteristics. Detail design and fabrication of the pumped-fed RS44 integrated component evaluator (ICE) was accomplished using company discretionary resources and was tested under this contracted effort. Successful demonstrations were completed to about the 50% fuel turbopump power level (87,000 RPM), but during this last test, a high pressure fuel turbopump (HPFTP) bearing failed curtailing the test program. No other hardware were affected by the HPFTP premature shutdown. The ICE operations matched well with the predicted start transient simulations. The tests demonstrated the feasibility of high performance advanced expander cycle engine. All engine components operated nominally, expect for the HPFTP, during the engine hot-fire tests. A failure investigation was completed using company discretionary resources.

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Document Details

Document Type
Technical Report
Publication Date
Oct 12, 1993
Accession Number
ADA277085

Entities

People

  • A. Bermúdez Martínez
  • B. W. Lariviere
  • H. Manko
  • M. Taniguchi
  • R. Baily
  • R. F. Sutton

Tags

Communities of Interest

  • Biomedical
  • Human Systems
  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Barometric Pressure
  • Combustion
  • Combustion Chambers
  • Data Acquisition
  • Engine Components
  • Engineers
  • Failure Mode And Effect Analysis
  • Fuel Injection
  • Fuel Injectors
  • Heat Transfer
  • Ignition
  • Ignition Systems
  • Logic Gates
  • Measurement
  • Pressure Measurement
  • Rocket Engines
  • Test Facilities

Readers

  • Aerospace Test and Evaluation
  • Economics
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster