(57) ABSTRACT A fuel nozzle is provided for a gas turbine engine, and can include a pilot
fuel injector having an axially-elongated, inner pilot centerbody wall and an outer pilot …

A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending
between a forward end and an aft end. The liner includes a plurality of quench air jets …

A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and
a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes …

A gas turbine engine including a trapped vortex combustor assembly is generally provided.
The combustor assembly includes an inner liner wall extended annularly around a …

An attritable engine includes an engine case, which includes an outer wall and a fuel rail
integral with the outer wall. The fuel rail includes a fuel line integral with the outer wall, a fuel …

The present application and the resultant patent thus pro vide a combustor for combusting a
number of flows of air and a number of flows of fuel. The combustor may include a central …

Abstract The aircraft Auxiliary Power Unit (APU) is required to provide power to start the
main engines, conditioned air and power when there are no facilities available and, most …

A combustor for a turbomachine engine includes a dome made of a ceramic matrix
composite (CMC) material, the dome being secured within a support structure. The …

A trapped vortex reverse flow combustor for a gas turbine includes a first dome structure
having a plurality of first-dome vortex driver airflow openings for providing a first vortex …

A combustor for a gas turbine engine includes an outer liner having a first end
interconnected to an opposite second end by an outer liner wall composed of a plurality of …