A sound attenuator includes part of a plate forming a combustion liner and an acoustic cover defining, in conjunction with this part of the plate, a space on the outer circumferential side of the combustion liner. A restrictor that reduces a gas flow path is provided inside the combustion liner. At least one through-hole penetrating from inside the combustion liner to the space is defined in the part of the plate. At least one of the through-holes in the sound attenuator is present within a region spanning from a position of a minimum restrictor diameter of the restrictor to positions, on an upstream side and a downstream side, at a distance equivalent to a minimum restrictor radius.

A sound attenuator includes part of a plate forming a combustion liner and an acoustic cover defining, in conjunction with this part of the plate, a space on the outer circumferential side of the combustion liner. A restrictor that reduces a gas flow path is provided inside the combustion liner. At least one through-hole penetrating from inside the combustion liner to the space is defined in the part of the plate. At least one of the through-holes in the sound attenuator is present within a region spanning from a position of a minimum restrictor diameter of the restrictor to positions, on an upstream side and a downstream side, at a distance equivalent to a minimum restrictor radius.

A combustor including a combustor main body having a transition piece that defines a flow channel therein, and a combustor basket inserted in the transition piece from an upstream side of the flow channel that defines a gap through which a film air is sent with an inner peripheral surface of the transition piece; a connecting pipe disposed upstream of an outlet of the gap that connects to the combustor main body from an outer peripheral side and communicates with the flow channel via a connection hole; and a flow guide disposed at an identical position to the outlet of the gap on a downstream side of a connecting portion of the connecting pipe and the combustor main body that guides a compressed air introduced from outside the connecting pipe so that a flow rate distribution is made uniform in a circumferential direction of the combustor main body.

A combustor including a combustor main body having a transition piece that defines a flow channel therein, and a combustor basket inserted in the transition piece from an upstream side of the flow channel that defines a gap through which a film air is sent with an inner peripheral surface of the transition piece; a connecting pipe disposed upstream of an outlet of the gap that connects to the combustor main body from an outer peripheral side and communicates with the flow channel via a connection hole; and a flow guide disposed at an identical position to the outlet of the gap on a downstream side of a connecting portion of the connecting pipe and the combustor main body that guides a compressed air introduced from outside the connecting pipe so that a flow rate distribution is made uniform in a circumferential direction of the combustor main body.

A combustor assembly (17) including guide vanes (44) located between an inner cylinder (24) and a flow sleeve (25). Each guide vane (44) includes a circumferentially angled flow directing portion (60) adjacent to a leading edge (46). The leading edge (46) of at least one guide vane (44) can be located radially inward along the longitudinal axis (54) relative to the leading edge (46) of at least one other of the guide vanes (44). The length of the guide vanes (44) may vary, and the circumferential spacing between a first pair of the guide vanes (44) can be different from a spacing between a second pair of the guide vanes (44).

A combustor including a transition piece that defines a flow channel therein; a combustor basket inserted in the transition piece from an upstream side of the flow channel that sends a combustion gas through the flow channel and defines a gap through which a compressed air is sent with an inner peripheral surface of the transition piece; wherein the combustor basket includes a notch portion recessed from an end of the combustor basket on a downstream side toward the upstream side, and a purge air introduction hole through which the compressed air in the gap is introduced into the notch portion.

A closed trapped vortex apparatus includes: a tubular structure having a structural wall, the structural wall forming a cavity within the tubular structure, the structural wall having a lower boundary wall forming a boundary between the cavity and a core flow passage; at least one driver hole passing through the structural wall; an ignition source communicating with the cavity; a fuel source communicating with the cavity; and a plurality of flame tubes extending through the lower boundary wall of the tubular structure at preselected locations so as to provide communication between the cavity and the core flow passage.

A closed trapped vortex apparatus includes: a tubular structure having a structural wall, the structural wall forming a cavity within the tubular structure, the structural wall having a lower boundary wall forming a boundary between the cavity and a core flow passage; at least one driver hole passing through the structural wall; an ignition source communicating with the cavity; a fuel source communicating with the cavity; and a plurality of flame tubes extending through the lower boundary wall of the tubular structure at preselected locations so as to provide communication between the cavity and the core flow passage.

A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each of the plurality of transition ducts is offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly. The turbomachine includes a late injection assembly providing fluid communication for an injection fluid to flow into the interior downstream of the inlet of at least one transition duct of the plurality of transition ducts.

The present disclosure is directed to a radially stacked fuel injection module for a segmented annular combustion system. The fuel injection module includes a bundled tube fuel nozzle portion and a plurality of fuel injection lances. In one instance, a first set of fuel injection lances and a second set of fuel injection lances share a housing with the bundled tube fuel nozzle. The first and second sets of fuel injection lances are radially stacked, each set of lances being in communication with a respective injector fuel plenum. The fuel injection lances deliver fuel to a respective premixing channel formed between the side walls of an integrated combustor nozzle, an aft end of which defines a turbine nozzle. In another instance, the bundled tube fuel nozzle may be provided as a radially inner fuel nozzle and a radially outer fuel nozzle, each with a respective bundled tube fuel plenum.