A fuel injector for a lean direct injection fuel nozzle has a pilot air swirler which sits radially outboard of a pilot fuel swirler radially outer wall. The air swirler is bounded on its radially outer side by joined wall portions. One wall portion extends axially and another wall portion converges
A fuel injector for a lean direct injection fuel nozzle has a pilot air swirler which sits radially outboard of a pilot fuel swirler radially outer wall. The air swirler is bounded on its radially outer side by joined wall portions. One wall portion extends axially and another wall portion converges radially. On the radially inwardly facing surface, the wall portions meet to provide a continuing wall surface of the air swirler which transitions from axial extension to radial convergence over a smooth radius. The curvature of this surface broadly mirrors the radially outwardly facing profile of the pilot fuel swirler radially outer wall. The axially extending wall portion is extended axially to form a first part of a join interface. The radially converging portion is extended in a radial direction to provide a second part of the join interface.
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1. A fuel injector for a lean direct injection fuel nozzle, the fuel injector comprising: a fuel swirler arranged about an axis and an air swirler arranged coaxial with and radially displaced from the fuel swirler,each of the fuel swirler and air swirler having a circumferentially extending wall com
1. A fuel injector for a lean direct injection fuel nozzle, the fuel injector comprising: a fuel swirler arranged about an axis and an air swirler arranged coaxial with and radially displaced from the fuel swirler,each of the fuel swirler and air swirler having a circumferentially extending wall comprising an axially extending wall portion and a convergent portion which converges radially at a downstream end of the circumferentially extending wall towards an outlet, the outlet of the air swirler axially displaced from the outlet of the fuel swirler in a downstream direction,wherein the convergent portion of the air swirler circumferentially extending wall comprises a material different from that of the axially extending wall portion of the air swirler and is joined to the axially extending wall portion at a weld interface join by a molten interface joining method, and wherein a radially inwardly facing surface of the circumferentially extending wall included in the air swirler transitions from an axial extension to a radial convergence over a radius and the axially extending wall portion included in the air swirler defines at least a first portion of the radial convergence,wherein the convergent portion of the air swirler includes:a radially inward facing radially convergent surface,a radially outward facing radially convergent surface,an interface surface extending parallel with the axis, anda downstream-facing planar end surface that abuts, and is perpendicular with, the interface surface;said surfaces extend circumferentially about the axis of the air swirler,the radially inward facing radially convergent surface defines at least a second portion of the radial convergence downstream of the first portion of the radial convergence of the circumferentially extending wall,the interface surface extends axially away from the radially inward facing radially convergent surface,the downstream-facing planar end surface extends radially inward from the interface surface to the radially outward facing radially convergent surface, andthe downstream-facing planar end surface does not form part of the weld interface join between the convergent portion and the axially extending wall portion. 2. The fuel injector as claimed in claim 1 wherein the axially extending wall portion and the convergent portion included in the circumferentially extending wall of the air swirler are adapted to provide the weld interface join therebetween using a laser butt weld. 3. The fuel injector as claimed in claim 2 wherein the fuel injector is a pilot fuel injector having a pilot fuel swirler arranged radially inboard of the air swirler. 4. The fuel injector as claimed in claim 3 wherein the air swirler is provided with a first array of effusion cooling holes which extend from the radially inward facing radially convergent surface to the radially outward facing radially convergent surface. 5. The fuel injector as claimed in claim 4 wherein the first array of effusion cooling holes are round. 6. The fuel injector as claimed in claim 5 wherein the air swirler is provided with a second array of effusion cooling holes which extend from the radially inward facing radially convergent surface to the radially outward facing radially convergent surface. 7. The fuel injector as claimed in claim 6 wherein the second array of effusion cooling holes are elongate slots. 8. The fuel injector as claimed in claim 1 wherein the axially extending wall portion and convergent portion are joined at the weld interface join with a layer of braze material. 9. The fuel injector as claimed in claim 1 wherein the axially extending wall portion and the convergent portion are joined using a laser welding method. 10. The fuel injector as claimed in claim 9 wherein a notch is cut into one or both of the axially extending wall portion and the convergent portion at the weld interface join into which excess weld upset flows. 11. The fuel injector as claimed in claim 1 wherein the axially extending wall portion and the convergent portion are joined using a brazing method. 12. The fuel injector as claimed in claim 11 wherein a notch is cut into one or both of the axially extending wall portion and the convergent portion at the weld interface join into which excess braze flows. 13. The fuel injector as claimed in claim 1 wherein the air swirler is provided with a first array of effusion cooling holes which extend through the radially inward facing radially convergent surface and the downstream-facing planar end surface of the convergent portion. 14. The fuel injector as claimed in claim 1 wherein the axially extending wall portion of the air swirler includes: an inner surface,an outer surface,a downstream-facing planar end surface, andan interface surface;said surfaces extend circumferentially about the axis of the air swirler;the inner surface extends axially and a downstream end of the inner surface defines the first portion of the radial convergence of the circumferentially extending wall,the outer surface is spaced apart radially from the inner surface,the downstream-facing planar end surface of the axially extending wall portion extends perpendicular to and radially inward from the outer surface to the convergent portion, andthe interface surface of the axially extending wall portion extends axially downstream from the first portion of the radial convergence of the circumferentially extending wall to the downstream-facing planar end surface of the axially extending wall portion, and the interface surface of the axially extending wall portion faces the interface surface of the convergent portion. 15. A lean direct injection fuel nozzle comprising one or more fuel injectors, each of the one or more fuel injectors comprising: a fuel swirler arranged about an axis and an air swirler arranged coaxial with and radially displaced from the fuel swirler,each of the fuel swirler and air swirler having a circumferentially extending wall comprising an axially extending wall portion and a convergent portion which converges radially at a downstream end of the circumferentially extending wall towards an outlet,the outlet of the air swirler axially displaced from the outlet of the fuel swirler in a downstream direction,wherein the convergent portion of the air swirler circumferentially extending wall comprises a material comprising a thermal performance characteristic which is different from that of the axially extending wall portion of the air swirler and is joined to the axially extending wall portion at a molten interface join by a molten interface joining method, and wherein a radially inwardly facing surface of the circumferentially extending wall included in the air swirler transitions from an axial extension to a radial convergence and at least a portion of the axially extending wall portion of the air swirler defines at least a first portion of the radial convergence,wherein the convergent portion of the air swirler includes:a radially inward facing radially convergent surface,a radially outward facing radially convergent surface,an interface surface extending parallel with the axis, anda downstream-facing planar end surface that abuts, and is perpendicular with, the interface surface;said surfaces extend circumferentially about the axis,the radially inward facing radially convergent surface defines at least a second portion of the radial convergence downstream of the first portion defined by the axially extending wall portion,the interface surface extends axially away from the radially inward facing radially convergent surface,the downstream-facing planar end surface extends radially inward from the interface surface to the radially outward facing radially convergent surface, andthe downstream-facing planar end surface does not form part of the molten interface join between the convergent portion and the axially extending wall portion. 16. A lean direct injection fuel nozzle comprising: a pilot fuel injector and main fuel injector arranged in a staged configuration, the pilot fuel injector arranged radially inboard of the main fuel injector and the pilot fuel injector comprising a pilot fuel swirler arranged about an axis and a pilot air swirler arranged coaxial with and radially outboard of the pilot fuel swirler, each of the pilot fuel swirler and pilot air swirler having a circumferentially extending outer wall comprising an axially extending portion and a convergent portion which converges radially at a downstream end of the circumferentially extending outer wall towards an outlet,the outlet of the pilot air swirler axially displaced from the outlet of the pilot fuel swirler in a downstream direction, wherein the convergent portion of the pilot air swirler circumferentially extending outer wall comprises a material comprising a thermal performance characteristic which is different from the axially extending portion of the pilot air swirler circumferentially extending outer wall and is joined to the axially extending portion at a molten interface join by a molten interface joining method, and wherein a radially inwardly facing surface of the circumferentially extending outer wall included in the pilot air swirler transitions from an axial extension to a radial convergence and at least a portion of the axially extending portion of the pilot air swirler defines at least a first portion of the radial convergence,wherein the convergent portion of the pilot air swirler includes:a radially inward facing radially convergent surface,a radially outward facing radially convergent surface,an interface surface extending parallel with the axis, anda downstream-facing planar end surface that abuts, and is perpendicular with, the interface surface;said surfaces extend circumferentially about the axis,the radially inward facing radially convergent surface defines at least a second portion of the radial convergence downstream of the first portion defined by the axially extending portion,the interface surface extends axially away from the radially inward facing radially convergent surface,the downstream-facing planar end surface extends radially inward from the interface surface to the radially outward facing radially convergent surface, andthe downstream-facing planar end surface does not form part of the molten interface join between the convergent portion and the axially extending portion.
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이 특허에 인용된 특허 (9)
Sanjay Sampath ; Jack E. Vanderpool, Advanced Mo-based composite powders for thermal spray applications.
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