ANNULAR PREMIXED PILOT IN FUEL NOZZLE
First Claim
Patent Images
1. A fuel/air nozzle for a gas turbine engine, the fuel/air nozzle comprising:
- an axially elongating peripheral wall defining an outer envelope of the fuel/air nozzle, the peripheral wall having an outer surface and an inner surface facing opposite the outer surface and defining an axially elongating inner cavity;
a hollow, axially elongating centerbody disposed within the inner cavity of the fuel/air nozzle and defining a central axis, the centerbody being defined by a centerbody wall defining an upstream end and a downstream end disposed axially opposite the upstream end, the centerbody wall being defined by an exterior surface and an interior surface facing opposite the exterior surface, the interior surface of the centerbody wall defining an axially elongating interior passage disposed concentrically about the central axis of the centerbody;
an elongated, hollow fuel supply line extending axially through the interior passage of the centerbody, the fuel supply line having an upstream end disposed at the upstream end of the centerbody and configured for connection to a source of fuel, the fuel supply line having a downstream end disposed at the downstream end of the centerbody;
a primary air flow channel being defined by an annular space between the exterior surface of the centerbody and the inner surface of the peripheral wall;
a premixed pilot nozzle having an upstream end connected to the downstream end of the centerbody, the premixed pilot nozzle having a downstream end disposed axially opposite the upstream end of the premixed pilot nozzle; and
the premixed pilot nozzle further defining a plurality of axially elongated, hollow premix conduits, each premix conduit having an upstream end disposed near the downstream end of the centerbody and defining an entrance opening that communicates fluidly with the interior passage of the centerbody, each premix conduit having at least one fuel hole being connected in fluid communication with the downstream end of the fuel supply line, each premix conduit having a downstream end defining an exit opening that allows fluid to discharge from the hollow premix conduit, each downstream end of each premix conduit defining a central axis that is not parallel to the central axis of the centerbody.
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Abstract
A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits that are configured with concentric axes that direct the fuel/air mixture axially from the premixed pilot nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix and including air jets that direct air radially outwardly from the premix conduits.
39 Citations
36 Claims
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1. A fuel/air nozzle for a gas turbine engine, the fuel/air nozzle comprising:
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an axially elongating peripheral wall defining an outer envelope of the fuel/air nozzle, the peripheral wall having an outer surface and an inner surface facing opposite the outer surface and defining an axially elongating inner cavity; a hollow, axially elongating centerbody disposed within the inner cavity of the fuel/air nozzle and defining a central axis, the centerbody being defined by a centerbody wall defining an upstream end and a downstream end disposed axially opposite the upstream end, the centerbody wall being defined by an exterior surface and an interior surface facing opposite the exterior surface, the interior surface of the centerbody wall defining an axially elongating interior passage disposed concentrically about the central axis of the centerbody; an elongated, hollow fuel supply line extending axially through the interior passage of the centerbody, the fuel supply line having an upstream end disposed at the upstream end of the centerbody and configured for connection to a source of fuel, the fuel supply line having a downstream end disposed at the downstream end of the centerbody; a primary air flow channel being defined by an annular space between the exterior surface of the centerbody and the inner surface of the peripheral wall; a premixed pilot nozzle having an upstream end connected to the downstream end of the centerbody, the premixed pilot nozzle having a downstream end disposed axially opposite the upstream end of the premixed pilot nozzle; and the premixed pilot nozzle further defining a plurality of axially elongated, hollow premix conduits, each premix conduit having an upstream end disposed near the downstream end of the centerbody and defining an entrance opening that communicates fluidly with the interior passage of the centerbody, each premix conduit having at least one fuel hole being connected in fluid communication with the downstream end of the fuel supply line, each premix conduit having a downstream end defining an exit opening that allows fluid to discharge from the hollow premix conduit, each downstream end of each premix conduit defining a central axis that is not parallel to the central axis of the centerbody. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A combustor for a gas turbine engine, the combustor comprising:
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a head end portion; at least one fuel/air nozzle carried by the head portion, each fuel/air nozzle further comprising; an axially elongating peripheral wall defining an outer envelope of the fuel/air nozzle, the peripheral wall having an outer surface and an inner surface facing opposite the outer surface and defining an axially elongating inner cavity; a hollow, axially elongating centerbody disposed within the inner cavity of the fuel/air nozzle and defining a central axis, the centerbody being defined by a centerbody wall defining an upstream end and a downstream end disposed axially opposite the upstream end, the centerbody wall being defined by an exterior surface and an interior surface facing opposite the exterior surface, the interior surface of the centerbody wall defining an axially elongating interior passage disposed concentrically about the central axis of the centerbody; an elongated, hollow fuel supply line extending axially through the interior passage of the centerbody, the fuel supply line having an upstream end disposed at the upstream end of the centerbody and configured for connection to a source of fuel, the fuel supply line having a downstream end disposed at the downstream end of the centerbody; a primary air flow channel being defined by an annular space between the exterior surface of the centerbody and the inner surface of the peripheral wall; a premixed pilot nozzle having an upstream end connected to the downstream end of the centerbody, the premixed pilot nozzle having a downstream end disposed axially opposite the upstream end of the premixed pilot nozzle; and the premixed pilot nozzle further defining a plurality of axially elongated, hollow premix conduits, each premix conduit having an upstream end disposed near the downstream end of the centerbody and defining an entrance opening that communicates fluidly with the interior passage of the centerbody, each premix conduit having at least one fuel hole being connected in fluid communication with the downstream end of the fuel supply line, each premix conduit having a downstream end defining an exit opening that allows fluid to discharge from the hollow premix conduit, each downstream end of each premix conduit defining a central axis that is not parallel to the central axis of the centerbody. - View Dependent Claims (10, 11, 12)
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13. A method of operating a fuel/air nozzle for improved flame stability and NOx in a gas turbine engine, the fuel/air nozzle being defined by a peripheral wall, a hollow centerbody disposed within the peripheral wall and defining a central axis, a swozzle extending from the exterior of the upstream end of the centerbody and radially toward the peripheral wall, and at the downstream end of centerbody a premix pilot nozzle including a plurality of premix conduits having exit openings, the method comprising the steps of:
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delivering a primary flow of air downstream past the swozzle to swirl the primary flow of air; delivering a primary flow of fuel through the swozzle to mix with the swirled primary flow of air downstream of the swozzle; delivering a flow of pilot fuel through a hollow fuel supply line to the premix pilot nozzle; delivering a secondary flow of air downstream through the centerbody to the premix pilot nozzle; mixing the pilot fuel with the secondary flow of air in a plurality of axially elongated, hollow premix conduits wherein each premix conduit defines a central axis at the downstream end thereof that is not parallel to the central axis of the centerbody and that discharges the fuel/air mixture from the downstream end of the premix pilot nozzle; and expelling the fuel/air mixture from the exit openings of the premix conduits of the premixed pilot nozzle. - View Dependent Claims (14, 15, 16, 17, 18, 19)
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20. A fuel/air nozzle for a gas turbine engine, the fuel/air nozzle comprising:
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an axially elongating peripheral wall defining an outer envelope of the fuel/air nozzle, the peripheral wall having an outer surface and an inner surface facing opposite the outer surface and defining an axially elongating inner cavity; a hollow, axially elongating centerbody disposed within the inner cavity of the fuel/air nozzle and defining a central axis, the centerbody being defined by a centerbody wall defining an upstream end and a downstream end disposed axially opposite the upstream end, the centerbody wall being defined by an exterior surface and an interior surface facing opposite the exterior surface, the interior surface of the centerbody wall defining an axially elongating interior passage disposed concentrically about the central axis of the centerbody; an elongated, hollow fuel supply line extending axially through the interior passage of the centerbody, the fuel supply line having an upstream end disposed at the upstream end of the centerbody and configured for connection to a source of fuel, the fuel supply line having a downstream end disposed at the downstream end of the centerbody; a primary air flow channel being defined by an annular space between the exterior surface of the centerbody and the inner surface of the peripheral wall; a premixed pilot nozzle having an upstream end connected to the downstream end of the centerbody, the premixed pilot nozzle having a downstream end disposed axially opposite the upstream end of the premixed pilot nozzle; the premixed pilot nozzle further defining a plurality of axially elongated, hollow premix conduits, each premix conduit having an upstream end disposed near the downstream end of the centerbody and defining an entrance opening that communicates fluidly with the interior passage of the centerbody, each premix conduit defining at least one fuel hole connected in fluid communication with the downstream end of the fuel supply line, each premix conduit having a downstream end defining an exit opening that allows fluid to discharge from the hollow premix conduit, at least each upstream end of each premix conduit defining a central axis configured and disposed so that the flow of fluid that enters the entrance opening of each premix conduit is directed parallel to the central axis of the centerbody; and an annular channel disposed radially outwardly from the premix conduits, the annular channel being configured to communicate fluidly with the interior passage of the centerbody. - View Dependent Claims (21, 22, 23, 24, 25)
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26. A combustor for a gas turbine engine, the combustor comprising:
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a head end portion; at least one fuel/air nozzle carried by the head portion, each fuel/air nozzle further comprising; an axially elongating peripheral wall defining an outer envelope of the fuel/air nozzle, the peripheral wall having an outer surface and an inner surface facing opposite the outer surface and defining an axially elongating inner cavity; a hollow, axially elongating centerbody disposed within the inner cavity of the fuel/air nozzle and defining a central axis, the centerbody being defined by a centerbody wall defining an upstream end and a downstream end disposed axially opposite the upstream end, the centerbody wall being defined by an exterior surface and an interior surface facing opposite the exterior surface, the interior surface of the centerbody wall defining an axially elongating interior passage disposed concentrically about the central axis of the centerbody; an elongated, hollow fuel supply line extending axially through the interior passage of the centerbody, the fuel supply line having an upstream end disposed at the upstream end of the centerbody and configured for connection to a source of fuel, the fuel supply line having a downstream end disposed at the downstream end of the centerbody; a primary air flow channel being defined by an annular space between the exterior surface of the centerbody and the inner surface of the peripheral wall; a premixed pilot nozzle having an upstream end connected to the downstream end of the centerbody, the premixed pilot nozzle having a downstream end disposed axially opposite the upstream end of the premixed pilot nozzle; and the premixed pilot nozzle further defining a plurality of axially elongated, hollow premix conduits, each premix conduit having an upstream end disposed near the downstream end of the centerbody and defining an entrance opening that communicates fluidly with the interior passage of the centerbody, each premix conduit being connected in fluid communication with the downstream end of the fuel supply line, each premix conduit having a downstream end defining an exit opening that allows fluid to discharge from the hollow premix conduit, each downstream end of each premix conduit defining a central axis configured and disposed so that the flow of fluid that discharges from exit opening is directed parallel to the central axis of each premix conduit; and an annular channel disposed radially outwardly from the premix conduits, the annular channel being configured to communicate fluidly with the interior passage of the centerbody. - View Dependent Claims (27, 28, 29, 30)
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31. A method of operating a fuel/air nozzle for a gas turbine engine, the fuel/air nozzle being defined by a peripheral wall, a hollow centerbody disposed within the peripheral wall and defining a central axis, a swozzle extending from the exterior of the upstream end of the centerbody and radially toward the peripheral wall, and at the downstream end of centerbody a premix pilot nozzle including a plurality of premix conduits having exit openings, the method comprising the steps of:
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delivering a primary flow of air downstream past the swozzle to swirl the primary flow of air; delivering a primary flow of fuel through the swozzle to mix with the swirled primary flow of air downstream of the swozzle; delivering a flow of pilot fuel through a hollow fuel supply line to the premix pilot nozzle; delivering a secondary flow of air downstream through the centerbody to the premix pilot nozzle; mixing the pilot fuel with the secondary flow of air in a plurality of axially elongated, hollow premix conduits that discharge the fuel/air mixture from the downstream end of the premix pilot nozzle; diverting some of the secondary flow of air to an annular channel that is disposed radially outwardly from the premix conduits of the premixed pilot nozzle; and expelling the fuel/air mixture from the exit openings of the premix conduits of the premixed pilot nozzle. - View Dependent Claims (32, 33, 34, 35, 36)
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Specification