Pattern Factor Improvement in the F-100 Primary Combustion System

Abstract

Causes of exit temperature nonuniformity in the primary combustion system of the F100 augmented turbofan engine have been identified and investigated in a comprehensive test program. This test program involved a combination of instrumented full engine, annular combustor rig, and subscale component rig tests. Modifications to the fuel nozzle, which provide significant improvements in combustor exit temperature uniformity, are now being incorporated into the production version of the engine. Modifications to the combustor configuration are being incorporated into growth versions of the engine.

Smoke Reduction in FJR-710 Turbofan Engines by an Airblast Combustor

“…In a series of rig tests, emphasis was placed on improving combuster performance and decreasing exhaust emission through cowl and liner modifications under nonuniform airflow conditions at combustor inlet. As a practical concern in combustor design, it is generally known that combustor performance is seriously affected by radial variations in compressor discharge pressure in nonuniform conditions in the annulus [14,15]. To provide radial pressure distortion in combustor inlet flows, 120 distortion pins were mounted around the inner casing, near the throat of the diffuser flow path, upstream from the leading edges of the liner struts, as shown in Fig.…”