Effect of heat and power extraction on turbojet-engine performance.
4 - Analytical determination of effects of hot-gas bleed /
Stanley L. Koutz.

Description

Main Author

Koutz, Stanley L.

Related Names

United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1951.

Subjects

Airplanes > Airplanes / Motors > Airplanes / Motors / Performance.
Airplanes > Airplanes / Turbojet engines.

Summary

In general, with a turbojet engine operating at constant engine speed, bleeding gas from the tail pipe at constant tail-pipe-nozzle area and reduced turbine-inlet temperature caused 2.5 to 4 times as great a loss in thrust as bleeding gas at constant turbine-inlet temperature and reduced tail-pipe-nozzle area.
Generalized working charts are presented with which the performance of a turbojet engine operating with tail-pipe gas bleed can be determined. From these generalized working charts, the performance of an engine operating with tail-pipe gas bleed at several typical flight conditions and modes of engine operation is calculated. A method of determing the performance of a turbojet engine with turbine-inlet bleed from the performance with compressor-outlet bleed is also given.

Note

NACA TN No. 2304.
"March 1951."

Physical Description

43 p. : ill. ; 28 cm.

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