A fuel manifold adapter for a fuel system of an aircraft engine, the fuel manifold adapter comprising: a body having a body-output interface defining a downstream end of a body passage including a body bore about a bore axis, the body-output interface movably and fluidly connectable to a first component of the fuel system mounted to a first mounting point of the engine, and a body-input interface defining an upstream end of the body passage, the body-input interface rigidly and fluidly connectable to a second component of the fuel system mounted to a second mounting point of the engine, and a transfer tube having an upstream-tube end slidably engaged with the body along the bore axis via the body bore, the transfer tube having a downstream-tube end opposite the upstream-tube end slidably engageable along the bore axis with the first component, the downstream-tube end defining a downstream end of the fuel manifold adapter relative to fuel flow through the fuel manifold adapter.

A cartridge for attachment to the inner surface of a single-walled combustion liner of an annular combustor is provided. The cartridge includes at least one chute projecting into the combustion chamber for a counter swirl effect for improved fuel/air mixing in the combustion chamber and at least two studs projecting through associated stud holes in the liner. A method for attaching a cartridge to the inner surface of a single-walled combustion liner is also provided.

A combustor may comprise an outer combustor panel and an inner combustor panel radially inward of the outer combustor panel. A bulkhead panel may extend radially between the outer combustor panel and the inner combustor panel. An outer spacer may be located between an outer flange of the bulkhead panel and the outer combustor panel. An inner spacer may be located between an inner flange of the bulkhead panel and the inner combustor panel.

A combustor liner for a gas turbine engine, the combustor liner including a panel configured to at least partially define a combustion chamber. The combustor liner further includes a shell configured to mount to the panel and form a gap between the panel and the shell. The panel includes a stud and a plurality of a stand-off pins proximate to the stud defining a cavity therebetween. The shell includes a plurality of angled impingement holes located away from the cavity but extending through the shell at an orientation such that cooling air passing through the angled impingement holes is directed towards the cavity between adjacent stand-off pins and at an acute angle relative to the stud.

A combustor liner for a gas turbine engine, the combustor liner including a panel configured to at least partially define a combustion chamber. The combustor liner further includes a shell configured to mount to the panel and form a gap between the panel and the shell. The panel includes a stud and a plurality of a stand-off pins proximate to the stud defining a cavity therebetween. The shell includes a plurality of angled impingement holes located away from the cavity but extending through the shell at an orientation such that cooling air passing through the angled impingement holes is directed towards the cavity between adjacent stand-off pins and at an acute angle relative to the stud.

A combustor liner assembly includes a first liner panel that has a first forward end and a first aft end. A second liner panel has a second forward end and a second aft end. A support band has a plurality of circumferentially spaced holes. The support band is arranged between the first liner panel and the second liner panel. The support band has a protrusion with a first angled surface and a second angled surface. The first angled surface is in engagement with the first aft end and the second angled surface in engagement with the second forward end.

A combustor liner assembly includes a first liner panel that has a first forward end and a first aft end. A second liner panel has a second forward end and a second aft end. A support band has a plurality of circumferentially spaced holes. The support band is arranged between the first liner panel and the second liner panel. The support band has a protrusion with a first angled surface and a second angled surface. The first angled surface is in engagement with the first aft end and the second angled surface in engagement with the second forward end.

A gas burner for a cooktop includes a spreader extending along a major axis to define an elongated shape. The spreader further defines an underside and includes a first projection and a second projection extending away from the underside. An orifice holder includes a body and a first lobe and a second lobe extending radially outward from the body. The first and second projections are opposingly adjacent to at least one of the first and second lobes. The orifice holder is mutually engageable with the spreader, with the first and second projections opposingly adjacent with at least one of the first and second lobes.

A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.

A combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.