Abstract: A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.

Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome with a swirler mounting wall formed integral with the CMC dome, and a swirler assembly including a plurality of clevis dome attachment members for connecting the swirler assembly to the CMC dome. Bushings are arranged within a plurality of dome-side swirler assembly mounting openings of the swirler mounting wall, and the CMC dome is arranged within respective ones of the plurality of clevis dome attachment members of the swirler assembly. A swirler-dome connecting member is disposed through each of the clevis dome attachment members so as to mount the swirler assembly to the CMC dome.

Abstract: A combustor for a gas turbine includes a cowl structure, a pseudo-dome structure, a ceramic matrix composite (CMC) dome, and a swirler assembly. The swirler assembly is connected to the pseudo-dome structure, which is connected to the cowl structure, and the CMC dome is separately connected to the cowl structure apart from the swirler assembly. The swirler assembly includes a swirler dome interface wall that interfaces with the CMC dome on an upstream side of the CMC dome, and a swirler outlet extends through a CMC dome swirler opening through the CMC dome.

Abstract: A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.

Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome with a swirler mounting wall formed integral with the CMC dome, and a swirler assembly including a plurality of clevis dome attachment members for connecting the swirler assembly to the CMC dome. Bushings are arranged within a plurality of dome-side swirler assembly mounting openings of the swirler mounting wall, and the CMC dome is arranged within respective ones of the plurality of clevis dome attachment members of the swirler assembly. A swirler-dome connecting member is disposed through each of the clevis dome attachment members so as to mount the swirler assembly to the CMC dome.

Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome including a swirler opening therethrough with a flare interface surface surrounding the swirler opening, a swirler assembly including (a) a secondary swirler having a threaded flare attachment portion, and (b) a flare having (i) a threaded secondary swirler attachment portion, and (ii) a dome interface wall that interfaces with the flare interface surface of the CMC dome, and a swirler-dome attachment member. The flare is connected to the secondary swirler via the threaded flare attachment portion and the threaded secondary swirler attachment portion, and the swirler-dome attachment member applies a force to the CMC dome to engage the dome interface wall and the flare interface surface so as to connect the CMC dome and the swirler assembly.

Abstract: A combustor for a gas turbine includes a cowl structure, a pseudo-dome structure, a ceramic matrix composite (CMC) dome, and a swirler assembly. The swirler assembly is connected to the pseudo-dome structure, which is connected to the cowl structure, and the CMC dome is separately connected to the cowl structure apart from the swirler assembly. The swirler assembly includes a swirler dome interface wall that interfaces with the CMC dome on an upstream side of the CMC dome, and a swirler outlet extends through a CMC dome swirler opening through the CMC dome.

Abstract: A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.

Abstract: A system includes a fuel nozzle including a first wall disposed about a central axis, a second wall disposed about the first wall, and a plurality of lobes disposed between the first and second walls, wherein the plurality of lobes is spaced about the central axis to define a plurality of flow passages, and the plurality of flow passages is configured to output a plurality of flows into a flame region.

Abstract: A gas turbine system include a first body including a central passage extending from a mixing region to a central outlet at a first downstream end portion of the first body, a fuel outlet in the mixing region, an oxidant outlet in the mixing region, and an outer passage including a first passage extending in a downstream direction toward the first downstream end portion and a second passage extending in an upstream direction from the first downstream end portion into the mixing region.

Abstract: A micromixer system includes a casing having a first side wall and a second side wall. Further, the micromixer system includes a plurality of pipes spaced apart from each other and disposed within the casing. Each pipe includes an inlet and an outlet formed in the first and second side walls respectively. The micromixer system includes a first plenum having a first inlet formed in the casing. The first plenum is disposed around a first portion of the plurality of pipes and fluidically coupled to the plurality of pipes. The micromixer system includes a second plenum having a second inlet formed in the casing and disposed around a second portion of the plurality of pipes. Further, the micromixer system includes a plurality of openings formed in the second side wall, surrounding the outlets of at least some pipes of the plurality of pipes, and fluidically coupled to the second plenum.

Abstract: A system includes an annular combustor having a housing disposed about a head end chamber upstream of a combustion chamber. The annular combustor is configured to extend circumferentially about a rotational axis of a gas turbine engine, and an axis of the combustion chamber is acutely angled relative to the rotational axis. The system also includes a holder coupled to the housing and extending through the head end chamber in an axial direction relative to the axis of the combustion chamber. The holder includes a first receptacle configured to hold a first fuel nozzle, and the holder comprises a first fuel passage extending to the first receptacle.

Abstract: A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.

Abstract: A system includes a fuel nozzle including a first wall disposed about a central axis, a second wall disposed about the first wall, and a plurality of lobes disposed between the first and second walls, wherein the plurality of lobes is spaced about the central axis to define a plurality of flow passages, and the plurality of flow passages is configured to output a plurality of flows into a flame region.

Abstract: A gas turbine system include a first body including a central passage extending from a mixing region to a central outlet at a first downstream end portion of the first body, a fuel outlet in the mixing region, an oxidant outlet in the mixing region, and an outer passage including a first passage extending in a downstream direction toward the first downstream end portion and a second passage extending in an upstream direction from the first downstream end portion into the mixing region.

Abstract: A micromixer system includes a casing having a first side wall and a second side wall. Further, the micromixer system includes a plurality of pipes spaced apart from each other and disposed within the casing. Each pipe includes an inlet and an outlet formed in the first and second side walls respectively. The micromixer system includes a first plenum having a first inlet formed in the casing. The first plenum is disposed around a first portion of the plurality of pipes and fluidically coupled to the plurality of pipes. The micromixer system includes a second plenum having a second inlet formed in the casing and disposed around a second portion of the plurality of pipes. Further, the micromixer system includes a plurality of openings formed in the second side wall, surrounding the outlets of at least some pipes of the plurality of pipes, and fluidically coupled to the second plenum.