Gas Turbine Cycle Calculations: Experimental Verificaiton of Off- Design-Point Performance Predictions for a Two-Spool Turbojet with Various Air Bleeds

Abstract

As part of a continuing program of gas turbine cycle calculations, the Engine Laboratory of the National Research Council of Canada has proposed a simplified method for calculating off-design-point performance of turbojet and turbofan engines, both at sea level static and at altitude flight conditions. This method specifically implies constancy of component efficiencies and linearity of corrected mass flow with corrected engine speed. During a series of tests on a J-75 two-spool turbojet engine, experimental data were gathered at part-throttle conditions, and subsequently with compressor bleed extraction and with propelling nozzle area change.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1971
Accession Number
AD0741914

Entities

People

  • M. S. Chappell
  • W. Grabe

Organizations

  • National Research Council Canada

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Masses
  • Altitude
  • Combustion Products
  • Data Reduction
  • Experimental Data
  • Flow Rate
  • Fuel Consumption
  • Gas Turbine Nozzles
  • Gas Turbines
  • Mass Flow
  • Measurement
  • Pressure Measurement
  • Sea Level
  • Thermodynamic Cycles
  • Turbines
  • Turbofan Engines
  • Turbojet Engines

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Combustion and Flow Dynamics.