There is provided a gas turbine combustor capable of improving cooling performance of a combustion chamber thereof and reducing the amount of NOx emissions. The gas turbine combustor includes: a cylindrical combustion chamber that burns combustion air and fuel to thereby produce combustion gas; an outer casing disposed concentrically on an outside of the combustion chamber; an end cover disposed at an upstream side end portion of the outer casing; an annular passage formed by an outer peripheral surface of the combustion chamber and an inner peripheral surface of the outer casing, the annular passage allowing the combustion air to flow therethrough; and a passage formed inside a combustion chamber wall between the outer peripheral surface and an inner peripheral surface of the combustion chamber, the passage having a U-shape turned sideways and having ends disposed on an upstream side in a transverse cross-sectional view, in which the passage includes a first passage that extends in parallel with an axial direction of the combustion chamber and has a supply hole on a first end side thereof, the supply hole communicating with an outside of the combustion chamber wall, and a second passage that has a second end side communicating with a second end side of the first passage and has a jet hole on a first end side thereof, the jet hole communicating with an inside of the combustion chamber wall.

An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (14) is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include resonator chambers (26) that may be welded in place within resonator chamber (26) receivers (24) but easily replaceable without exposing the resonator housing (18) to damage. In another embodiment, an inner surface (32) of the resonator chamber (26) may be offset radially outward from an inner surface (34) of the resonator housing (18), thereby creating a flow-path discontinuity and reducing heating of the resonator chamber (26). The acoustic damping resonator system (14) may mitigate dynamics thereby increasing an engine operating envelope and decreasing emissions.

A combustion chamber assembly comprises an annular combustion chamber casing, a combustion chamber, a fuel injector and a tubular seal. The combustion chamber comprises an upstream end wall having an aperture extending there-through. A fuel injector head of the fuel injector is locatable in the aperture in the end wall and the fuel injector head has an axis. The tubular seal is positioned between the fuel injector head and the aperture in the end wall and the tubular seal has a flange and an aperture extends there-through. The tubular seal is movable radially and circumferentially with respect to the axis of the casing. The fuel injector head is locatable in the tubular seal. The aperture in the upstream end wall has a major radial dimension and a minor circumferential dimension relative to the axis of the casing to allow insertion or removal of a lean burn fuel injector head.

A heat shield provided with a gas turbine engine includes a heat shield body extending between a first heat shield end and a second heat shield end. The heat shield body has an exterior surface disposed proximate an inner surface of a first case and an interior surface disposed opposite the exterior surface. The interior surface defines a rib that extends towards a combustor vane support lock.

A combustor assembly for a gas turbine engine is includes a liner and a combustor dome formed of a ceramic matrix composite material. The combustor dome and liner together define at least in part a combustion chamber. The combustor dome extends along a circumferential direction and defines one or more openings, the combustor dome is configured to receive one or more fuel-air injector hardware assemblies in or through the one or more openings.

A combustor assembly for a gas turbine engine includes a liner and a combustor dome. The combustor dome and liner together at least in part define a combustion chamber. The combustor dome includes a transition portion and a forward wall. The transition portion extends from the forward wall towards the liner. Additionally the transition portion may define an angle relative to the forward wall and/or may define a radius of curvature between the forward wall of the combustor dome and a flat of the transition portion of the combustor dome for increasing an aerodynamic efficiency of the combustor dome.

A combustor assembly includes a first combustion chamber member and a second combustion chamber member. The first and second combustion chamber members are each formed of a CMC material and include adjacently positioned coupling flanges. A mounting assembly includes a pair of mounting flanges positioned on opposite sides of the coupling flanges of first and second combustion chamber members. An attachment member of the mounting assembly clamps the pair of mounting flanges together to mount the first and second combustion chamber members.

A combustor assembly for a gas turbine engine includes a combustor dome and a combustion chamber liner attached to or formed integrally with the combustor dome. The combustion chamber liner extends between a forward end and an aft end, and together with the combustor dome at least partially defines a combustion chamber. The combustor assembly additionally includes a mounting assembly attached to the liner proximate the forward end of the liner for supporting the combustor dome and combustion chamber liner within the gas turbine engine relative to a structural component of the gas turbine engine.

A combustor assembly for a gas turbine engine includes a combustor dome and a combustion chamber liner formed integrally of a ceramic matrix composite material. The combustor dome defines a plurality of openings for receiving a respective plurality of fuel air injector hardware assemblies and may extend continuously along a circumferential direction.

A combustor assembly for a gas turbine engine includes an inner liner, an outer liner, and a combustor dome. The inner liner, outer liner, and combustor dome together define at least in part a combustion chamber having an annulus height. Additionally, the combustor assembly includes a fuel-air injector hardware assembly positioned at least partially within an opening of the combustor dome. The fuel-air injector hardware assembly includes a heat shield located at least partially within the combustion chamber, the heat shield defining an outer diameter. A ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield may be at least about 1.5:1.