Patent attributes
A combustion section of a gas turbine engine may include a cassette configured to couple to an annular combustor dome arranged around a flow path for the gas turbine engine. The annular combustor dome may include a dome wall comprising a plurality of inlets configured to receive compressed air for a combustion chamber located downstream, relative to the flow path, from the annular combustor dome. The cassette may include a combustor wall extended away from the dome wall in a downstream direction. The cassette may further include a cowl integral to the combustor wall. At least a portion of the cowl may extend away from the dome wall in an upstream direction relative to the flow path. The cowl may receive compressed air from a diffusor and guide the compressed air to a space upstream from the inlets, relative to the flow path.
