Performance of Compressor-Turbine Jet-Propulsion Systems

Abstract

An analysis of the performance of compressor-turbine jet-propulsion systems was carried out by calculating thrust power from a compressor turbine jet engine with a systematic variation of pressure ratio, fuel-air ratio, compressor and turbine efficiencies, flight speed, altitude, and maximum gas temperature. It was found that by increasing turbine and compressor efficiencies from 70 to 80 percent, over-all efficiency of the engine was doubled at 300 mph. Maximum power output at a particular altitude was found to be approximately proportional to temperature difference between combustion chamber and free atmosphere.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1945
Accession Number
ADA801128

Entities

People

  • Carl B. Palmer

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Altitude
  • Chambers
  • Combustion
  • Combustion Chambers
  • Compressors
  • Efficiency
  • Flight Speeds
  • Fuel Air Ratio
  • Gas Turbines
  • Internal Combustion Engines
  • Jet Engines
  • Jet Propulsion
  • Mach Number
  • Propulsion Systems
  • Sea Level
  • Turbines

Fields of Study

  • Engineering
  • Physics

Readers

  • Electrical Engineering
  • Petroleum Engineering
  • Solar Physics