Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas /
Charles C. Graves and Jack S. Grobman.

Description

Main Author

Graves, Charles C.

Related Names

Grobman, Jack S.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1957.

Subjects

Charts, diagrams, etc.
Mathematics.
Air flow.
Combustion chambers.
Airplanes > Airplanes / Turbojet engines.

Summary

The combustor total-pressure-loss coefficient and liner air-flow distribution are presented graphically in terms of the following dimensionless parameters: (1) combustor reference Mach number, (2) ratio of combustor-exit to inlet total temperature, (3) fraction of total airflow passing through the liner dome, (4) ratio of total open hole area in liner wall to total combustor cross-sectional area, and (5) ratio of liner cross-sectional area to total combustor cross-sectional area.
Compressible and incompressible flow calculations were made of the combustor total-pressure-loss coefficient and liner airflow distribution for tubular turbojet combustors having constant annulus and liner cross-sectional areas along the combustor axis. Information on static and total pressure distribution and liner air-jet entrance angles along the length of the combustor was obtained as an intermediate step in the calculations. The calculations include the effects of heat release, annulus wall friction, and variation in discharge coefficients of the liner wall openings along the combustor.

Note

NACA Research Memorandum E56I04.
"January 4, 1957."
Title from cover.

Physical Description

[1], 85 p. : ill. ; 27 cm.

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