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AssigneePratt & Whitney Canada Corp.
InventorsLev Alexander Prociw, Harris Shafique, Parthasarathy Sampath
Estimating the term…
A fuel injector for a combustor presented either as a simplex or duplex pressurized fuel injector, wherein the fuel is introduced into the injector to provide a swirl to the fuel in a first annular channel which communicates with a coaxial conical fuel swirl chamber and then the primary nozzle. In a duplex version, a secondary annular swirl channel is provided for spinning the fuel and communicating downstream with a conical fuel swirl chamber and eventually an annular nozzle whereby the fuel is atomized as it exits the nozzle. An air swirler is also provided with the fuel injector, and the air swirler includes air passages arranged in an annular array about the fuel injector tip. A second array of auxiliary air passages can be arranged spaced radially from the first array and also to provide an air swirl and to control the spray cone of the fuel air mixture.
A fuel injector for use in a combustor of a gas turbine engine, whereby the combustor includes a combustor wall defining a combustion chamber surrounded by pressurized air, the injector comprising an injector tip adapted to protrude, when in use, through the combustor wall into the chamber, the injector tip having an injector body extending along an injector tip axis, a primary fuel nozzle formed in the injector tip concentrically of the injector tip axis and communicating with a primary fuel chamber formed as a cone upstream of the fuel nozzle and coaxial therewith, a first annular fuel channel defined in the injector body upstream of the primary fuel chamber concentric with the injector tip axis and communicating with the primary fuel chamber, a second annular fuel channel defined in the injector body upstream of the first annular fuel channel, passages communicating the second annular fuel channel downstream to the first annular fuel channel, and an inlet conduit defined in the injector body to communicate the fuel under pressure tangentially into the second fuel channel so as to provide a swirl to the fuel in the second fuel channel, and then to the first annular fuel channel tangentially thereof in order to provide a swirl to the fuel flow in the second annular fuel channel, the first annular fuel channel, the primary fuel chamber, and thus to the injector tip, thereby atomizing the fuel as it exits the primary fuel nozzle.
In a fuel injector for use in a combustor of a gas turbine engine, wherein the fuel injector includes an injector tip having annular fuel flow passages, a stem containing at least one fuel flow passage extending from a stem fuel inlet to a stem fuel delivery outlet, a first annular fuel flow chamber provided in the stem near the fuel stem inlet, an inlet conduit extending from the fuel stem inlet to the first annular fuel flow chamber wherein the inlet conduit is angled to provide a tangential flow direction to the fuel passing through the conduit to the annular fuel flow chamber, an outlet conduit extending at an acute angle from the first annular fuel flow chamber to receive the fuel therefrom in a tangential direction, a first linear fuel conduit extending from the outlet conduit and extending axially of the stem and communicating with an injector inlet conduit at the fuel delivery outlet of the stem, the injector inlet conduit being angled to direct the fuel flow to a first annular passage in the injector in a tangential direction to provide a swirl to the fuel flow entering the annular passage in the injector tip.
A fuel injector for use in a combustor of a gas turbine engine, whereby the combustor includes a combustor wall defining a combustion chamber surrounded by pressurized air, the injector comprising an injector tip adapted to protrude, when in use, through the combustor wall into the chamber, the injector tip having an injector body extending along an injector tip axis, a primary fuel nozzle formed in the injector tip concentrically of the injector tip axis and communicating with a primary fuel chamber formed as a cone upstream of the fuel nozzle and coaxial therewith, at least a first annular fuel channel defined in the injector body upstream of the primary fuel chamber concentric with the injector tip axis and communicating with the primary fuel chamber, a plurality of slots to communicate the primary fuel chamber, wherein the slots are angled to provide a tangential delivery of the fuel flow from the first annular channel to the primary fuel chamber, and means for providing a flow of pressurized fluid to the first annular channel tangentially thereof in order to provide a swirl to the fuel flow in the first annular fuel channel, the primary fuel chamber, and thus to the tip nozzle, thereby atomizing the fuel as it exits the primary fuel nozzle.
A fuel injector for use in a combustor of a gas turbine engine, whereby the combustor includes a combustor wall defining a combustion chamber surrounded by pressurized air, the injector comprising an injector tip adapted to protrude, when in use, through the combustor wall into the chamber, the injector tip having an injector body extending along an injector tip axis, a primary fuel nozzle formed in the injector tip concentrically of the injector tip axis and communicating with a primary fuel chamber formed as a cone upstream of the fuel nozzle and coaxial therewith, at least a first annular fuel channel defined in the injector body upstream of the primary fuel chamber concentric with the injector tip axis and communicating with the primary fuel chamber, and means for providing a flow of pressurized fluid to the first annular channel tangentially thereof in order to provide a swirl to the fuel flow in the first annular fuel channel, the primary fuel chamber, and thus to the tip nozzle, thereby atomizing the fuel as it exits the primary fuel nozzle;
Dependencies are inferred from the claim text.