A slinger combustor has an annular combustor shell defining a combustion chamber having a radially inner fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger. The combustion chamber has a fuel atomization zone extending radially outwardly from the fuel inlet and merging into a radi
A slinger combustor has an annular combustor shell defining a combustion chamber having a radially inner fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger. The combustion chamber has a fuel atomization zone extending radially outwardly from the fuel inlet and merging into a radially outwardly flaring expansion zone leading to a combustion zone. A plurality of nozzle air inlets are defined in the fuel atomization zone of the combustor shell. The nozzle air inlets have a nozzle axis intersecting the stream of fuel and a tangential component in a direction of rotation of the fuel slinger. A plurality of dilution holes are defined in the combustor shell and have a dilution axis intersecting the combustion zone. The dilution axis of at least some of the dilution holes has a tangential component opposite to the direction of rotation of the fuel slinger.
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1. A slinger combustor for a gas turbine engine, the slinger combustor comprising: an annular combustor shell concentrically disposed about a central axis and defining an annular combustion chamber having a radially inner annular fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger
1. A slinger combustor for a gas turbine engine, the slinger combustor comprising: an annular combustor shell concentrically disposed about a central axis and defining an annular combustion chamber having a radially inner annular fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger mounted for rotation about the central axis, the combustor shell having front and rear annular liners, a fuel atomization zone extending radially outwardly from the radially inner circumferential fuel inlet and merging into a radially outwardly flaring expansion zone leading to a combustion zone, wherein the fuel atomization zone is provided in the form of a straight radially extending sub-chamber bounded by axially facing parallel inner peripheral ring portions of the front and rear annular liners, a plurality of nozzle air inlets defined in the fuel atomization zone of the combustor shell, the nozzle air inlets comprising at least one circumferential array of nozzle air inlets in each of the inner peripheral ring portions of the front and rear liners, each nozzle air inlet having a nozzle axis intersecting the stream of fuel centrifuged by the fuel slinger upstream of the radially outwardly flaring expansion zone, the nozzle axis having a tangential component in a direction of rotation of the fuel slinger, and a plurality of dilution holes defined in the combustor shell, the dilution holes having a dilution axis intersecting the combustion zone, and wherein the dilution axis of at least some of the dilution holes has a tangential component in a circumferential direction opposite to the direction of rotation of the fuel slinger. 2. The slinger combustor defined in claim 1, further comprising effusion holes wherein the effusion holes are defined in the expansion zone of the combustor shell, the effusion holes having a tangential component in the direction of rotation of the fuel slinger. 3. The slinger combustor defined in claim 1, further comprising effusion holes, wherein the effusion holes are defined in the combustor shell downstream from the combustion zone, the effusion holes having a tangential component in a direction opposite to the direction of rotation of the fuel slinger and opposite to the tangential component of the nozzle air inlets. 4. The slinger combustor defined in claim 1, wherein the nozzle axis of each of the nozzle air inlets on the front and rear annular liners has opposite axial components and similar radially outer components. 5. The slinger combustor defined in claim 1, wherein the dilution holes have a length/diameter ratio ranging from 3.5 to 4.5. 6. The slinger combustor defined in claim 1, wherein the front and rear annular liners being axially spaced-apart to define the combustion chamber therebetween, wherein the dilution holes comprise a first array of diffusion holes defined in the front annular liner and a second array of diffusion holes defined in the rear annular liner, the tangential components of the dilution axes of all the dilution holes of at least one of said first and second arrays being in a direction opposite to the direction of rotation of the fuel slinger. 7. The slinger combustor defined in claim 6, wherein the tangential components of the dilution axes of the dilution holes of both the first and second arrays are in a direction opposite to the direction of rotation of the fuel slinger. 8. The slinger combustor defined in claim 6, wherein the tangential components of the dilution axes of the dilution holes of the second array on the rear annular liner are in the same direction as the direction of rotation of the fuel slinger. 9. A method for mixing fuel and air in an annular combustion chamber defined between front and rear liners mounted about a central axis, comprising: using a rotary fuel slinger, atomizing and spraying fuel in a radially outward direction through a radially inner annular fuel inlet of the combustion chamber, the fuel having a swirl component in a circumferential direction of the combustion chamber;further atomizing the fuel in atomization zone by directing air jets into the flow of fuel through air jet holes defined in the front and rear liners at said radially inner annular fuel inlet, the air jets being injected with a swirl component in a same direction as that of the swirl component of the fuel, wherein the fuel atomization zone is provided in the form of straight radially extending sub-chamber bounded by axially facing parallel inner peripheral ring portions of the front and rear liners, andinjecting dilution air through dilution holes defined in the front and rear liners at a location downstream from the air jet holes, the dilution holes being oriented such that the dilution air flowing through at least one of said front and rear liners has a swirl component in a direction opposite to the swirl component of the fuel. 10. The method defined in claim 9, wherein the swirl component of the dilution air injected through both the front and rear liners are opposite to the swirl component of the fuel. 11. The method defined in claim 9, wherein the swirl component of the dilution air injected through the front liner is opposite to the swirl component of the fuel, whereas the swirl component of the dilution air injected through the rear liner is in the same direction as that of the fuel. 12. The method defined in claim 9, further comprising effusion cooling respective inner surfaces of the front and rear liners between the nozzle air holes and the dilution holes, wherein effusion cooling comprises injecting effusion air through effusion holes defined in the front and rear liners, the effusion holes being oriented to cause effusion air to flow over the inner surfaces of the front and rear liners with a swirl component in the same direction as the swirl component of the fuel. 13. The method defined in claim 12, further comprising effusion cooling a portion of the front and rear liners downstream of the dilutions holes by injecting additional effusion air in said portion with a swirl component in a direction opposite to the swirl component of the fuel.
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이 특허에 인용된 특허 (33)
Overton Dennis L. (Bristol GB3) Jones Leighton (Bristol GB3), Annular combustor with fuel manifold.
McCarty William L. (Orlando FL) Wescott Kermit R. (Winter Springs FL) Tyler Paul J. (Winter Springs FL) St. Onge Leo P. (Wexford PA), Apparatus for ignition diagnosis in a combustion turbine.
Jorgensen Robert A. (Clifton Park NY) Farrell Roger A. (Schenectady NY) Gerhold Bruce W. (Rexford NY), Dual stage-dual mode low emission gas turbine combustion system.
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