Author(s)

M. Egoavil & R. Puster

Abstract

A new airfoil-shaped fuel injector with an ignitor-booster system, was designed for the 8-Foot High-Temperature Tunnel (8-FT HTT) at NASA Langley Research Center. This fuel injector was developed so that it could be used as an uncooled injector in high-pressure, oxygen-enriched air. This effort required the development of new technology in fuel injector design. A high-velocity vortex stabilizer injector was developed. The development and tests conducted in a simple fan-driven apparatus are explained for the injectors at atmospheric pressure. Similar tests at high pressure were carried out in the Combustor Heated Test Facility (CHTF) with air and with oxygen enriched air The ignition of the fuel injector array is a quasi-stable ignition scheme The stabilizing concept was obtained through tests validated with the computa

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