Abstract: A fuel nozzle valve includes a fuel nozzle valve liner having a channel with an opening for allowing fuel to flow therethrough and a seat. A plunger has a stud and a base substantially perpendicular to the stud, the plunger being configured to move relative to the fuel nozzle valve liner to seal or to open the opening of the fuel nozzle valve. The fuel nozzle valve further includes a metal resilient member configured to contact the base of the plunger and the seat of the fuel nozzle valve liner to seal the opening of the fuel nozzle valve when the plunger is moved to seal the fuel nozzle valve.

Abstract: A fuel nozzle apparatus includes: a fuel distributor including an annular distributor ring, an aft interior mounting surface; and a pilot supply tube; a venturi defining a splitter with a first bore, and axially spaced-apart forward and aft exterior mounting surfaces; and a swirler including second bore and a forward interior mounting surface. The pilot supply tube is received in the second bore, outer ends of the inner vanes are received in the first bore; and the forward and aft exterior mounting surfaces of the venturi are received in the forward and aft interior mounting surfaces, respectively.

Abstract: A fuel nozzle for a gas turbine engine is disclosed, the fuel nozzle comprising at least one unitary component made using a rapid manufacturing process. In one aspect, the rapid manufacturing process is a laser sintering process. Unitary components disclosed include a conduit, swirler, distributor, venturi and a centerbody.

Abstract: A unitary distributor is disclosed, comprising at least one main flow passage located within a distributor ring body, the main flow passage having an arcuate portion oriented in a circumferential direction around a distributor axis. Exemplary embodiments of a unitary distributor having an annular ring located at the axially forward end of the distributor ring body are disclosed. A fuel distributor is disclosed, comprising a fuel conduit and a distributor wherein the fuel distributor has a unitary construction.

Abstract: A method for fabricating a unitary conduit is disclosed the method comprising the steps of determining three-dimensional information of the unitary conduit having at least one flow passage, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary conduit, and successively forming each layer of the unitary conduit by fusing a metallic powder using laser energy. A unitary conduit is disclosed, comprising a body and a flow passage, wherein the flow passage and the body have a unitary construction, and made by using a rapid manufacturing process.

Abstract: A unitary swirler is disclosed, comprising a body having a swirler axis, and a plurality of vanes arranged in a circumferential direction around the swirler axis, wherein the swirler has a unitary construction. In one embodiment, the unitary swirler has a rim located coaxially with the swirler axis, and a wall extending between a portion of the rim and a portion of the hub. In another embodiment, the unitary swirler has an adaptor having a passage that is configured to direct a flow of air towards at least some of the plurality of vanes.

Abstract: A unitary conduit for transporting a fluid is described, the conduit comprising a body and a flow passage located within the body, the flow passage having an inlet end and an exit end, wherein the flow passage and the body have a unitary construction. In another embodiment, a unitary conduit has a flow passage wherein the cross sectional shape of the flow passage changes from a first cross sectional shape to a second cross sectional shape. In another embodiment, the exterior contour of the body generally conforms to the interior contour of the flow passage. In another embodiment, the flow passage branches to a plurality of sub-passages.

Abstract: A method for assembling a gas turbine engine is provided. The method includes providing a combustor having a combustor liner assembly defining a combustion chamber. An outer combustor liner includes a radially extending first end that defines a combustion chamber input opening. An axially extending second end of the outer combustor liner defines a combustion chamber output opening. The first end transitions into the second end to form an arcuate cross-sectional shape of the outer combustor liner. A dome assembly is coupled to the first end of the combustor liner that extends downstream from the dome assembly. A fuel nozzle is positioned within a cyclone formed on the dome assembly and configured in a radial configuration.

Abstract: A method for assembling a gas turbine engine is provided. The method includes providing a combustor having a combustor liner assembly defining a combustion chamber. An outer combustor liner includes a radially extending first end that defines a combustion chamber input opening. An axially extending second end of the outer combustor liner defines a combustion chamber output opening. The first end transitions into the second end to form an arcuate cross-sectional shape of the outer combustor liner. A dome assembly is coupled to the first end of the combustor liner that extends downstream from the dome assembly. A fuel nozzle is positioned within a cyclone formed on the dome assembly and configured in a radial configuration.

Abstract: A method for fabricating a unitary conduit is disclosed the method comprising the steps of determining three-dimensional information of the unitary conduit having at least one flow passage, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary conduit, and successively forming each layer of the unitary conduit by fusing a metallic powder using laser energy. A unitary conduit is disclosed, comprising a body and a flow passage, wherein the flow passage and the body have a unitary construction, and made by using a rapid manufacturing process.

Abstract: A method of assembling a fuel nozzle comprises the steps of forming a pilot assembly; coupling the pilot assembly to a unitary distributor such that the pilot assembly is in flow communication with a pilot flow passage in the unitary distributor; coupling a unitary swirler having an adaptor to the unitary distributor; coupling the adaptor to a stem housing; coupling the unitary distributor to the stem housing; and coupling a centerbody to the stem housing.

Abstract: A unitary distributor is disclosed, comprising at least one main flow passage located within a distributor ring body, the main flow passage having an arcuate portion oriented in a circumferential direction around a distributor axis. Exemplary embodiments of a unitary distributor having an annular ring located at the axially forward end of the distributor ring body are disclosed. A fuel distributor is disclosed, comprising a fuel conduit and a distributor wherein the fuel distributor has a unitary construction.

Abstract: A venturi is disclosed, the venturi comprising a mixing cavity surrounded circumferentially by an annular venturi wall, and a swirler having a plurality of vanes arranged circumferentially around a swirler axis, wherein the swirler and the annular venturi wall have a unitary construction. In another exemplary embodiment the venturi comprises an annular venturi wall, a swirler located at an axially forward portion of the venturi, the swirler having a plurality of vanes arranged circumferentially around a swirler axis, and a heat shield located axially aft from the swirler, wherein the annular venturi wall, the swirler and the heat shield have a unitary construction.

Abstract: A method for fabricating a unitary venturi is disclosed, the method comprising the steps of determining three-dimensional information of the unitary venturi having an annular venturi wall and a swirler having a plurality of vanes arranged circumferentially around a swirler axis, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary venturi, and successively forming each layer of the unitary venturi by fusing a metallic powder using laser energy. Exemplary embodiments are disclosed, showing a unitary venturi comprising an annular venturi wall having a swirler axis and a heat shield located at an end wherein unitary venturi is made by using a rapid manufacturing process. In one aspect of the invention, the rapid manufacturing process is a laser sintering process.

Abstract: A unitary conduit for transporting a fluid is described, the conduit comprising a body and a flow passage located within the body, the flow passage having an inlet end and an exit end, wherein the flow passage and the body have a unitary construction. In another embodiment, a unitary conduit has a flow passage wherein the cross sectional shape of the flow passage changes from a first cross sectional shape to a second cross sectional shape. In another embodiment, the exterior contour of the body generally conforms to the interior contour of the flow passage. In another embodiment, the flow passage branches to a plurality of sub-passages.

Abstract: A method of repairing a fuel nozzle is disclosed comprising the steps of forming a pilot assembly; installing into a repair bore; inserting a primary adaptor into a repair bore such that the primary adaptor is in flow communication with a pilot flow passage and the pilot assembly; and coupling the primary adaptor to a distributor and the new pilot assembly.

Abstract: A unitary swirler is disclosed, comprising a body having a swirler axis, and a plurality of vanes arranged in a circumferential direction around the swirler axis, wherein the swirler has a unitary construction. In one embodiment, the unitary swirler has a rim located coaxially with the swirler axis, and a wall extending between a portion of the rim and a portion of the hub. In another embodiment, the unitary swirler has an adaptor having a passage that is configured to direct a flow of air towards at least some of the plurality of vanes.

Abstract: A fuel nozzle for a gas turbine engine is disclosed, the fuel nozzle comprising at least one unitary component made using a rapid manufacturing process. In one aspect, the rapid manufacturing process is a laser sintering process. Unitary components disclosed include a conduit, swirler, distributor, venturi and a centerbody.

Abstract: A method for fabricating a unitary swirler is disclosed, the method comprising the steps of determining three-dimensional information of the unitary swirler having a plurality of vanes arranged in a circumferential direction on a body around a swirler axis and a wall extending between a rim and a portion of the body, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary swirler, and successively forming each layer of the unitary swirler by fusing a metallic powder using laser energy. Exemplary embodiments are disclosed, showing a unitary swirler comprising a plurality of vanes extending from a hub having a unitary construction wherein unitary swirler is made by using a rapid manufacturing process. In one aspect of the invention, the rapid manufacturing process is a laser sintering process.

Abstract: A method for fabricating a unitary distributor is disclosed, the method comprising the steps of determining three-dimensional information of the unitary distributor having at least one flow passage having an arcuate portion located within a distributor ring body having an axis, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary distributor and successively forming each layer of the unitary distributor by fusing a metallic powder using laser energy. A distributor is disclosed comprising a flow passage with an arcuate portion located in a distributor ring body wherein the distributor is made by using a rapid manufacturing process. A unitary fuel distributor comprising a fuel conduit and a distributor is disclosed wherein the unitary fuel distributor is made by using a rapid manufacturing process.