A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange.

An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

A turbo machine including an annular liner assembly defining a reverse flow combustion chamber is generally provided. The liner assembly includes a first piece defining an inner diameter (ID) combustor inlet portion, an outer diameter (OD) combustor outlet portion, and an outer diameter turbine shroud portion, in which the first piece defines a substantially solid volume between the inner diameter combustor inlet portion and the outer diameter combustor outlet portion.

A turbo machine including an annular liner assembly defining a reverse flow combustion chamber is generally provided. The liner assembly includes a first piece defining an inner diameter (ID) combustor inlet portion, an outer diameter (OD) combustor outlet portion, and an outer diameter turbine shroud portion, in which the first piece defines a substantially solid volume between the inner diameter combustor inlet portion and the outer diameter combustor outlet portion.

A gas turbine engine includes an engine casing and a combustor liner enclosed within the engine casing. The engine includes a flow path for cooling the combustor liner with an air stream and located in between the engine casing and the combustor liner. The engine includes an inspection port penetrating the engine casing, the flow path, and the combustor liner and wherein the inspection port is positioned to allow an operator to view sacrificed zones of a sacrificial support structure.

A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner. An annular fuel manifold has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber.

An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine by one or more fastening elements that are integrally formed with the annular ring. The fastening elements are mountable with corresponding features of the support element and removably fastened thereto.