摘要:
A combustor fuel nozzle includes a center body and an inner shroud that circumferentially surrounds at least a portion of the center body. The inner shroud has a downstream surface. The fuel nozzle includes an inner passage between the center body and the inner shroud, an outer passage that circumferentially surrounds at least a portion of the inner shroud and a first plurality of fuel ports extending substantially radially outward through the center body. The first plurality of fuel ports is upstream from the downstream surface of the inner shroud. A method for supplying fuel to a combustor fuel nozzle includes flowing a working fluid through an inner passage between a center body and an inner shroud, injecting a fuel from the center body against the inner shroud, and flowing a portion of the working fluid through an outer passage that surrounds at least a portion of the inner shroud.
摘要:
A combustor fuel nozzle includes a center body and an inner shroud that circumferentially surrounds at least a portion of the center body. The inner shroud has a downstream surface. The fuel nozzle includes an inner passage between the center body and the inner shroud, an outer passage that circumferentially surrounds at least a portion of the inner shroud and a first plurality of fuel ports extending substantially radially outward through the center body. The first plurality of fuel ports is upstream from the downstream surface of the inner shroud. A method for supplying fuel to a combustor fuel nozzle includes flowing a working fluid through an inner passage between a center body and an inner shroud, injecting a fuel from the center body against the inner shroud, and flowing a portion of the working fluid through an outer passage that surrounds at least a portion of the inner shroud.
摘要:
A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles.
摘要:
A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles.
摘要:
In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, and a catalytic region. The catalytic region includes a catalyst, disposed inside the wall along the central passage, configured to increase a reaction of fuel and air.
摘要:
A dual fuel nozzle for a gas turbine combustor includes a hub defining a fuel inlet and a plurality of liquid fuel jets disposed at a downstream end of the hub. The fuel jets are oriented to eject liquid fuel radially outward from the hub. An annular air passage includes a swirler that imparts swirl to air flowing in the annular air passage, and a splitter ring is disposed in the annular air passage and surrounds the plurality of liquid fuel jets. The nozzle allows liquid fuels to be injected into a swirling annular airstream and then atomized, dispersed and vaporized inside a lean premixing dual fuel nozzle for a gas turbine combustor.
摘要:
In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, and a catalytic region. The catalytic region includes a catalyst, disposed inside the wall along the central passage, configured to increase a reaction of fuel and air.
摘要:
A dual fuel nozzle for a gas turbine combustor includes a hub defining a fuel inlet and a plurality of liquid fuel jets disposed at a downstream end of the hub. The fuel jets are oriented to eject liquid fuel radially outward from the hub. An annular air passage includes a swirler that imparts swirl to air flowing in the annular air passage, and a splitter ring is disposed in the annular air passage and surrounds the plurality of liquid fuel jets. The nozzle allows liquid fuels to be injected into a swirling annular airstream and then atomized, dispersed and vaporized inside a lean premixing dual fuel nozzle for a gas turbine combustor.
摘要:
A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.
摘要:
A combustion liner assembly is provided and includes a combustion liner and a transition piece. A portion of the transition piece is circumferentially disposed around a portion of the combustion liner. A seal is attached to the transition piece, and the seal is configured to apply a compressive force to an aft end of the combustion liner.