A combustor is provided for a turbine engine. The combustor includes a first liner having a
first side and a second side and a second liner having a first side and a second side. The …

In a gas turbine combustor having an inner and outer liner defining an annular combustion
chamber, at least an annular scoop ring provided on each inner and outer combustor liner …

An apparatus and method for a combustor, the combustor including combustor liner having
a plurality of dilution openings. The combustor receives a flow of fuel that is ignited and …

A cooling path structure for concentrated cooling of a seal area in a duct assembly and a gas
turbine combustor having the same are provided. The cooling path structure includes a …

The present disclosure is directed to a combustor assembly for a gas turbine engine. The
combustor assembly includes an inner liner and an outer liner together defining a …

(57) ABSTRACT A combustor for a gas turbine engine comprises a single skin liner defining
a combustion chamber. The single skin liner has an inner surface facing the combustion …

A shroud structure and a combustor burner using the shroud structure are provided for
improving swozzle flow. The shroud structure includes a shroud configured to surround a …

A gas turbine engine component assembly is provided. The gas turbine engine comprises: a
first component having a first surface and a second surface opposite the first surface; a …

A combustion chamber for a turbomachine that includes a chamber end wall and a plurality
of air and fuel injection systems distributed circumferentially about an axis of the combustion …

An insert element for closing an opening inside a wall of a hot gas path component of a gas
turbine includes a plate like body with an opening sided Surface. The Surface provides at …