Advanced jet engine combustor test facility,
by Paul W. Adam and James W. Norris.

Description

Main Author

Adam, Paul W.

Related Names

Norris, James W., joint author.

Language(s)

English

Published

Washington, National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.] 1970.

Subjects

Airplanes > Airplanes / Turbojet engines > Airplanes / Turbojet engines / Combustion.

Summary

A test facility for conducting full-scale advanced annular jet engine combustor research and durability tests is described. Combustors have been operated on ambient or heated ASTM-A1, natural gas, and propane fuels to an average exit temperature of 2400' F (1589 K). The airflow of 285 lb/sec (129.4 kg/sec) at 1200' F (922 K), 115 psia (79.2 N/cm2), and 60 000-ft (18 240-m) altitude exhaust capability allows simulation of combustor inlet conditions over most of the range of interest in supersonic cruise engines. Description of a unique jet-engine-fired, nonvitiating air heater is included. The test section, the instrumentation, the data acquisition system, and operation techniques and experiences are also described.

Note

Cover title.

Physical Description

30 p. illus. 27 cm.

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