Performance of Compressor of XJ-41-V Turbojet Engine. 1 - Preliminary Investigation at Equivalent Compressor Speed of 8000 rpm

Abstract

The operation and performance of centrifugal impeller, vaneless diffuser, vaned collector, bearings, and state of air stream in simulated combustion chamber were investigated. Test apparatus, procedure and instrumentation are described. The compressor showed stable and smooth mechanical operating characteristics over a range of actual compressor speeds from 3300 to 8000 rpm. at 8000 rpm, the maximum over-all adiabatic efficiency between inlet and discharge pipes was 0.77 and the maximum pressure ratio was 2.14.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1949
Accession Number
ADB814337

Entities

People

  • Ambrose Ginsburg
  • John W. Creagh

Organizations

  • Glenn Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Flow
  • Air Force
  • Chambers
  • Combustion Chambers
  • Compressor Components
  • Compressors
  • Dynamic Pressure
  • Engines
  • Flow
  • Instrumentation
  • Mass Flow
  • Mechanical Engineering
  • Pressure Gradients
  • Pressure Measurement
  • Static Pressure
  • Thrust Bearings
  • Turbojet Engines

Fields of Study

  • Engineering

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.