EFFECT OF AXIALLY STAGED FUEL INTRODUCTION ON PERFORMANCE OF ONE-QUARTER SECTOR OF ANNULAR TURBOJET COMBUSTOR
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH GLENN RESEARCH CENTER
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An investigation was conducted to determine the effect of staging the fuel introduction in the primary zone on the performance of a one-quarter sector of a single-annulus turbojet combustor. Pressure-atomized liquid fuel was introduced simultaneously through hollow-cone spray nozzles spraying axially from the upstream face of the combustor and through small fan spray nozzles spraying radially into the combustor and located on the walls of the combustor as much as 5 inches downstream of the main fuel manifold. The investigation was made at a constant combustor-inlet pressure of 15 inches of mercury absolute, at two combustor-inlet-air temperatures 80 deg and 270 deg F and over a range of air flows from 1.5 to 3.6 pounds per second per square foot.
- Jet and Gas Turbine Engines
- Combustion and Ignition