Single Chamber Capture Vortex Burner

Abstract

The present disclosure is directed to a combustor assembly for a propulsion system. The combustor assembly includes an annular inner liner extended generally along the longitudinal direction. The combustor assembly further includes an annular outer liner defining a first wall at a first radius extended at least partially along the longitudinal direction, a second wall at a second radius extended at least partially along the longitudinal direction, and a transition wall therebetween coupling the first wall and the second wall between the first radius and the second radius. The combustor assembly further includes a bulkhead wall disposed at the upstream end of the inner and outer liners. The bulkhead wall generally extends in the radial direction and couples the inner liner and the outer liner. The bulkhead wall, the inner liner, and the outer liner together define a combustion chamber therebetween. The bulkhead wall, the first wall of the outer liner, and the transition wall of the outer liner together define a single annular cavity of the combustion chamber. The bulkhead wall defines a primary airflow opening radially inward of the single annular cavity. The bulkhead wall and / or the outer liner defines one or more secondary airflow openings. The combustor assembly further includes a fuel nozzle defining a fuel nozzle exit disposed adjacent to the single annular cavity of the combustion chamber.

Description

[0001] Federally Funded Research [0002] This invention was made with Government support under Contract No. FA8650-15-D-2501 to the United States Government. The government may have certain rights in this invention. technical field [0003] This topic generally relates to propulsion system combustion components. More specifically, the subject matter relates to captured vortex combustor assemblies. Background technique [0004] A propulsion system such as a gas turbine engine typically includes a combustion section where compressed air is mixed with fuel and ignited to produce high pressure, high temperature combustion gases, which then flow downstream and expand to drive a fan section coupled to a compressor section and / or the turbine section of the loading device. Traditional combustion segments are challenged by burning fuel types of various calorie values. Traditional combustion sections are also challenged to reduce emissions such as nitric oxide, unburned hydrocarb...

AI Technical Summary

Problems solved by technology

Still further, conventional combustion sections are challenged to achieve any or all of these criteria while maintaining or reducing longitudinal and / or radial dimensions and / or component count

Images