A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution array having a plurality of dilution passages, each dilution passage of the plurality of dilution passages having a concatenated geometry repeating in a predetermined pattern and extending circumferentially around the liner body. The dilution passage integrates a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow and injects the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor. The dilution array is repeated along an axial length of the liner body.

Systems and methods are disclosed herein for passively managing cooling air in a gas turbine engine. A cooling air supply line may supply cooling air to a component in the gas turbine engine. A metering coupon may have a negative coefficient of thermal expansion. The metering coupon may allow more airflow through the metering coupon and through the component in response to an increase in temperature.

A gas turbine engine component assembly is provided. The gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, and a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow from the particulate.

A combustion chamber arrangement includes an annular outer and inner walls including at least one row of tiles. Each tile in the row of tiles has a rail extending towards and sealing with the outer wall and lip extending in a downstream direction from the row of tiles. The outer wall has a row of apertures to direct coolant onto the lips of the row of tiles. Each tile has a fastener positioned upstream of the rail and the fastener extends through a corresponding mounting aperture to secure the tile to the outer wall. The rail of each tile defines a plurality of slots with the outer wall and the slots are arranged in a region downstream of the corresponding fastener. None of the apertures in the row of apertures are in a region downstream of the tiles fastener. The arrangement reduces crack generation and propagation in the outer wall.

A combustor assembly for a gas turbine engine includes a combustor shell extending along a shell axis. The combustor shell includes a shell wall extending around the shell axis and a meter panel connected to an upstream end of the shell wall. The shell wall and the meter panel together define a combustion space therebetween. The combustor assembly further includes: a tile disposed within the combustor shell and including a tile flange portion extending radially with respect to the shell axis; a heatshield connected to the meter panel and extending at least radially towards the tile; a fastener connecting the tile flange portion to the meter panel; and a compartment thermally shielded from the combustion space. Either the heatshield and the tile together form the compartment or the tile alone forms the compartment. The fastener is spaced apart from the combustion space and at least partially disposed within the compartment.

An apparatus and system for assembling a combustor comprises a push bar including a first end portion that is laterally opposed from a second end portion. A first alignment block and a second alignment block are adjustably coupled to the push bar. A first threaded rod extends through the push bar proximate to the first end portion and a second threaded rod extends through the push bar proximate to the second end portion. The first alignment block and the second alignment block extend outwardly from an aft side of the push bar and are positioned between the first threaded rod and the second threaded rod. The installation tool includes a first nut and a second nut for applying axial force to the push bar.

The present application provides a combustor for a gas turbine engine. The combustor may include a number of fuel nozzles and an effusion plate assembly positioned about the fuel nozzles. The effusion plate assembly may include a cold pate, a hot plate, and a number of swirl inducing structures extending therebetween.

A gas turbine system (1) including a burner arrangement having a tubular combustion chamber (5), a turbine (6) and a transition duct (7) connecting the combustion chamber (5) and the turbine (6), wherein the transition duct (7) is provided with an axially extending cooling air channel (11). The transition duct (7) includes a plurality of axially extending cooling air channels, and wherein each cooling air channel (11) is provided with one single inlet (12) opened to the outside of the transition duct (7) and with one single outlet (12) opened to the inside of the transition duct (7).

A combustor for a gas turbine is described. The combustor comprises a combustor liner, a metering plate attached to an end of the combustor liner and a combustor casing at least partially surrounding the combustor liner. An end cover is further connected to the combustor casing. The combustor liner is connected to the combustor casing by means of a retainer arranged between the metering plate and the end cover, and attached to the metering plate and to the end cover.

A fuel injector is disclosed for reducing flashback. In an embodiment, the fuel injector may comprise an injector head with purge holes on a radial wall along a radial axis between an assembly axis of the fuel injector and a plurality of vanes arranged circumferentially around the assembly axis. In addition, the plurality of vanes may comprise fuel outlets connecting interior fuel passages to spaces between the vanes. The introduction of these purge holes near the bases of the vanes and the configuration and positioning of the fuel outlets in the vanes and elsewhere in the fuel injector may alter the stoichiometry (e.g., fuel-air ratio) within the premix passage of the fuel injector to reduce flashback. A plurality of such fuel injectors may be used in the combustor of a gas turbine engine.