A swirler includes an inner shroud positioned radially inside an outer shroud. At least one of the outer shroud and inner shroud has a major diameter and a minor diameter, the major diameter being greater than the minor diameter, the major and minor diameters defining an ovate shape. The swirler fur
A swirler includes an inner shroud positioned radially inside an outer shroud. At least one of the outer shroud and inner shroud has a major diameter and a minor diameter, the major diameter being greater than the minor diameter, the major and minor diameters defining an ovate shape. The swirler further includes a plurality of vanes extending between the inner and outer shrouds.
대표청구항▼
1. A swirler comprising: an outer shroud and an inner shroud, the outer shroud and the inner shroud each having a proximal end and a distal end, the inner shroud having a smoothly extending transitional wall configured to operatively associate with a fuel injector, the inner shroud positioned radial
1. A swirler comprising: an outer shroud and an inner shroud, the outer shroud and the inner shroud each having a proximal end and a distal end, the inner shroud having a smoothly extending transitional wall configured to operatively associate with a fuel injector, the inner shroud positioned radially inside the outer shroud;a plurality of vanes extending axially between the inner shroud and the outer shroud;wherein a horizontal centerline of the swirler extends parallel to an inner shell and an outer shell of a combustor, wherein a vertical axis of the swirler extends perpendicular to the horizontal centerline from the inner shell to the outer shell, andwherein at least one of: the respective proximal ends of the inner shroud and the outer shroud each have a major diameter parallel to the vertical axis and a minor diameter parallel to the horizontal centerline, wherein the major diameter is larger than the minor diameter thereby defining respective ovate proximal ends; orthe respective distal ends of the inner shroud and the outer shroud each have a major diameter parallel to the vertical axis and a minor diameter parallel to the horizontal centerline, wherein the major diameter is larger than the minor diameter thereby defining respective ovate distal ends. 2. The swirler of claim 1, wherein the plurality of vanes are positioned in an ovate shaped arrangement. 3. The swirler of claim 1, wherein the swirler has said respective ovate proximal ends, and the respective distal ends of the inner shroud and the outer shroud are circular shaped. 4. The swirler of claim 1, wherein the swirler has said respective ovate distal ends, and the proximal ends are circular shaped. 5. The swirler of claim 1, further including a secondary outer shroud having a proximal end and a distal end, the secondary outer shroud positioned around the outer shroud. 6. The swirler of claim 5, wherein at least one of the respective proximal and distal ends of the secondary outer shroud is ovate shaped. 7. The swirler of claim 1, wherein the swirler is a component of a swirler assembly. 8. A gas turbine engine, comprising: a compressor;a combustor axially behind the compressor and having at least one swirler positioned through a forward bulkhead;a turbine axially behind the combustor and connected to the compressor by a rotatable shaft, andeach swirler including: a plurality of vanes, an outer shroud, and an inner shroud, said outer shroud and said inner shroud each having a proximal end and a distal end, said inner shroud having a smoothly extending transitional wall configured to operatively associate with a fuel injector, said inner shroud positioned radially inside said outer shroud, said plurality of vanes extending axially between said inner shroud and said outer shroud, and each swirler further comprising a horizontal centerline extending parallel to an inner shell and an outer shell of the combustor, and a vertical axis extending perpendicular to the horizontal centerline from the inner shell to the outer shell, wherein for each swirler at least one of: the respective proximal ends of the inner shroud and the outer shroud each have a major diameter parallel to the vertical axis and a minor diameter parallel to the horizontal centerline, wherein the major diameter is larger than the minor diameter thereby defining respective ovate proximal ends, orthe respective distal ends of the inner shroud and the outer shroud each have a major diameter parallel to the vertical axis and a minor diameter parallel to the horizontal centerline, wherein the major diameter is larger than the minor diameter thereby defining respective ovate distal ends. 9. The gas turbine engine of claim 8, wherein the plurality of vanes are positioned in an ovate shaped arrangement. 10. The gas turbine engine of claim 8, wherein each swirler has said respective ovate proximal ends, and the respective distal ends of the inner shroud and the outer shroud of each swirler are circular shaped. 11. The gas turbine engine of claim 8, wherein each swirler has said respective ovate distal ends, and the respective proximal ends of the inner shroud and the outer shroud of each swirler are circular shaped. 12. The gas turbine engine of claim 8, wherein the combustor has an annular shape. 13. The gas turbine engine of claim 12, wherein each outer shroud is symmetrical about the vertical axis. 14. The gas turbine engine of claim 8, each swirler further comprising an ovate shaped secondary outer shroud radially surrounding said outer shroud. 15. The gas turbine engine of claim 8, wherein the at least one swirler is a component of a swirler assembly. 16. A method of mixing air and fuel with the swirler according to claim 1, comprising: injecting fuel into the swirler by a fuel injection system; andcreating a mixing turbulence with air flowing through a plurality of air passages between the plurality of vanes of the swirler thereby creating an air-fuel mixture in the swirler, the plurality of vanes being arranged in an ovate shape. 17. The method of claim 16, further comprising providing a premixing of the air and fuel within the swirler wherein the swirler has said respective ovate proximal ends. 18. The method of claim 16, further comprising dispersing the air-fuel mixture into a combustion chamber in an air-fuel flow distribution by the swirler, wherein the swirler has said respective ovate distal ends.
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이 특허에 인용된 특허 (16)
Ansart Denis R. H. (Bois le Roi FRX) Sandelis Denis J. M. (Nangis FRX), Aerodynamic fuel injection system for a gas turbine combustion chamber.
Koshoffer John M. (Forest Park OH) Ekstedt Edward E. (Montgomery OH) Samuel Billy P. (Madeira OH) Stamm Edward I. (Madeira OH), Gas turbine engine carburetor.
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