A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.
An embodiment of a torch ignitor system for combustor of a gas turbine engine includes a torch ignitor, the torch ignitor having a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor system also includes a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and at least one glow plug, a tip at a downstream end of the combustion chamber, and a passage for pressurized oxygen containing gas passing through the cap from an exterior of the combustion chamber and in fluid communication with the combustion chamber. An embodiment of a method for starting a gas turbine engine is also disclosed.
A method includes joining a fuel plurality of injection components to a fuel manifold, wherein for each fuel injection component in the plurality of fuel injection components, a metallic joint is formed joining and sealing the fuel injection component to the manifold. A system includes a fuel manifold. A plurality of fuel injection components are connected in fluid communication with the fuel manifold with metallic joints sealing between each of the plurality of fuel injection components and the fuel manifold to prevent leakage from between the manifold and the plurality of fuel injection components.
A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
A fuel injector system for a torch igniter includes an injector body centered on an axis, a receiving aperture formed in a cap of the torch igniter, an injector aperture, an air channel, a fuel channel, and a purge passage formed in a housing of the torch igniter and fluidly connected to a cooling air source. The injector body includes an axial wall at a first axial end of the injector body, an outer wall connected to the axial wall and extending along the axis transverse to the first wall, and an inner portion connected to the axial wall and extending along the axis transverse to the axial wall. An outer surface of the inner portion is spaced a distance from an inner surface of the outer wall, forming an insulating space between the outer wall and the inner portion.
A torch igniter for a combustor of a gas turbine engine includes an igniter body and an igniter head. The igniter body is disposed within a high-pressure case of a gas turbine engine and extends primarily along a first axis, and includes an annular wall and an outlet wall. The annular wall surrounds the first axis and defines a radial extent of a combustion chamber therewithin. The outlet wall is disposed at a downstream end of the annular wall, defines a downstream extent of the combustion chamber, and includes an outlet fluidly communicating between the combustion chamber and an interior of the combustor. The igniter head is removably attached to the igniter body at an upstream end of the annular wall, wherein the igniter head defines an upstream extent of the combustion chamber, and includes an ignition source and a fuel injector.
A fuel filter includes a manifold, a connector element, a filter bowl, a filter element, an inlet shutoff valve, an outlet shutoff valve, an inlet port, an inlet conduit, an outlet port, an outlet conduit and a relief valve. The connector element is fixed to the manifold and the filter bowl is reversibly fixed to the connector element. The connector element engages with the filter element. The filter bowl reversibly receives the filter element and is configured so that when the filter element is located within the filter bowl and the filter bowl is attached to the connection element the filter element divides the space defined by the connector element and filter bowl into an inlet filter chamber and an outlet filter chamber. The inlet port is incorporated in the manifold, and the inlet port and inlet filter chamber are in fluid communication via the inlet conduit.
B01D 35/00 - Filtering devices having features not specifically covered by groups , or for applications not specifically covered by groups Auxiliary devices for filtrationFilter housing constructions
B01D 29/11 - Filters with filtering elements stationary during filtration, e.g. pressure or suction filters, not covered by groups Filtering elements therefor with bag, cage, hose, tube, sleeve or like filtering elements
G05D 7/01 - Control of flow without auxiliary power
An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter at least partially within the combustor case, and a removable surface igniter. The torch igniter includes a combustion chamber, a cap configured to receive a fuel injector, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, an aperture, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The torch igniter is configured to receive the removable surface igniter through the aperture. An internal end of the removable surface igniter extends through the aperture into the combustion chamber of the torch igniter.
An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage.
An embodiment of a torch igniter for a combustor of a gas turbine engine comprises a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber and oriented about the axis, a tip defining an axially downstream end of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, and a cooling system. The cooling system comprises an air inlet formed within the structural wall, a first flow path disposed between the structural wall and the igniter wall, and an aperture extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber.
A combustor system for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case and defining a main combustion chamber, a dome defining an upstream end of the main combustion chamber, and at least one torch injector attached to the dome of the main combustion chamber configured to inject combustion gases into the main combustion chamber. Each torch injector includes a torch injector housing defining and surrounding a torch combustion chamber configured to house a combustion reaction, an outlet passage defined by the torch injector housing, an electrothermal ignition source extending at least partially into the torch combustion chamber, and a fuel injector configured to inject fuel into the torch combustion chamber to at least partially impinge on the electrothermal ignition source and generate the combustion gases. The outlet passage directly fluidly connects the torch combustion chamber to the main combustion chamber.
A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a torch ignitor, a housing, a flow channel, and an outlet nozzle. The torch ignitor system is configured to receive high-pressure air from the high-pressure compressor region of a gas turbine engine to increase operational characteristics of the torch ignitor system, including fuel atomization, cooling of the torch ignitor system, and circulation of combustion air within the torch ignitor system.
A fuel injector system for a torch igniter includes an injector body centered on an axis, a receiving aperture formed in a cap of the torch igniter, an injector aperture, an air channel, a fuel channel, and a purge passage formed in a housing of the torch igniter and fluidly connected to a cooling air source. The injector body includes an axial wall at a first axial end of the injector body, an outer wall connected to the axial wall and extending along the axis transverse to the first wall, and an inner portion connected to the axial wall and extending along the axis transverse to the axial wall. An outer surface of the inner portion is spaced a distance from an inner surface of the outer wall, forming an insulating space between the outer wall and the inner portion.
A tube joint includes a first member and a second member. The first member has a bore defining an inner diameter. The second member has a first outer surface defining a first outer diameter with two or more helical protrusions extending radially from the first outer diameter. The two or more helical protrusions collectively define a second outer diameter. The second outer diameter of the second member is larger than the inner diameter of the first member by an amount sufficient to center and retain the second member within the bore of the first member. Brazed tube joint assemblies and methods of making brazed tube joints are also described.
A method of manufacturing a hydraulic plug. A shell with a circumferential wall, a sealed end, an open end and an axially extending cavity within is provided in which the cavity is defined by an internal surface with an inner diameter which narrows towards the open end. A head of an expander is inserted into the cavity, the expander further comprising a stem extending from the cavity for applying a tensile force (T) to the head. A sleeve is provided on a stem side of the head extending into the cavity, an end of the sleeve adjacent the head having an inner diameter which is less than a maximum outer diameter of the head. The sleeve is formed by expanding the sleeve by forcing the head into the end of the sleeve through urging the sleeve and/or expander towards the other in an axial direction.
F16L 55/132 - Means for stopping flow in pipes or hoses by introducing into the pipe a member expandable in situ introduced axially into the pipe or hose the closure device being a plug fixed by radially deforming the packing
F16L 55/13 - Means for stopping flow in pipes or hoses by introducing into the pipe a member expandable in situ introduced axially into the pipe or hose the closure device being a plug fixed by plastic deformation
F16J 13/14 - Detachable closure membersMeans for tightening closures attached exclusively by spring action or elastic action
F16J 13/12 - Detachable closure membersMeans for tightening closures attached by wedging action by means of screw-thread, interrupted screw-thread, bayonet closure, or the like
F16B 7/02 - Connections of rods or tubes, e.g. of non-circular section, mutually, including resilient connections with conical parts
F16B 19/10 - Hollow rivetsMulti-part rivets fastened by expanding mechanically
A method of manufacturing a hydraulic plug includes providing a shell comprising a circumferential wall, a sealed end, an open end and a cylindrical cavity opening to the open end is provided. The open end of the shell is wider externally than the sealed end. A head of an expander is inserted into the cavity. The head of the expander has a convex contact surface which is rounded in an axial direction (A) of the cavity. A region of the shell adjacent its open end is plastically deformed causing material from the circumferential wall of the shell to be displaced radially inward around the head of the expander to form a constricted opening retaining the expander within the cavity. The deforming reshapes an internal surface of the cavity from a cylindrical to a non-linear shaped ramp leading up to a constricted opening.
F16L 55/10 - Means for stopping flow in pipes or hoses
F16L 55/13 - Means for stopping flow in pipes or hoses by introducing into the pipe a member expandable in situ introduced axially into the pipe or hose the closure device being a plug fixed by plastic deformation
B65D 39/12 - Closures arranged within necks or pouring openings or in discharge apertures, e.g. stoppers expansible, e.g. inflatable
21.
Compensating for thermal expansion via controlled tube buckling
One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel. The fuel injector also has an outlet fitting for delivering fuel through a nozzle to a combustor of the gas turbine engine. An injector support extends between the inlet fitting and the outlet fitting and has an internal bore therethrough. A fuel tube extends from the inlet fitting through the internal bore of the injector support to the outlet fitting. The injector support has a greater coefficient of thermal expansion than the fuel tube. At room temperature the fuel tube is under compressive stress such that the fuel tube is buckled. As a result of differential thermal expansion of the fuel tube and the injector support during engine operation the fuel tube is relieved of compressive stress.
A nozzle for a fuel injector can include an outer air swirler having an inner surface with the outer air swirler having a groove on the inner surface and a prefilmer located concentrically within the outer air swirler with the prefilmer having at least one detent finger to engage the groove on the inner surface of the outer air swirler. The nozzle can also include a fuel swirler located concentrically within the prefilmer and configured to convey fuel to a forward end of the nozzle with the fuel swirler having at least one tab extending axially at an aft end, and an inner air swirler having a cylindrical forward end located concentrically within the fuel swirler and an aft support extending radially outward to contact the outer air swirler with the cylindrical forward end contacting at least one tab of the fuel swirler to hold the fuel swirler in place.
F02M 61/18 - Injection nozzles, e.g. having valve-seats
F23D 11/24 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
A swirler for inducing swirl on a liquid flow includes a swirler body defining a downstream end and an upstream end; a plurality of axial slots on an external surface of the swirler body, each of the plurality of axial slots having a slot entrance and a slot exit; and a slot relief at the slot exit. Each of the plurality of axial slots are helical and configured to impart swirl on the liquid flow as the liquid flow traverses through each of the slots.
B05B 1/34 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl
F23D 11/10 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
F23D 11/24 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
F23R 3/30 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
A method of additive manufacturing includes building a component having a top surface, attaching the component to a powder bed fusion plate that receives the component, filling the powder bed fusion chamber so the powder is flush with the top surface of the component, and adding a first layer of powdered metal level with the top surface of the component. The method of additive manufacturing also includes fusing the first layer of powdered metal to the top surface of the component to create a fusion joint, and building up an additively manufactured body from the top surface of the component in subsequent layers.
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
B22F 3/24 - After-treatment of workpieces or articles
B22F 7/08 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
A nozzle is provided including a fuel swirler having an outer wall, an interior wall, and a fuel flow path configured to receive a fuel flow. The fuel flow path extends from adjacent and inlet end of the nozzle to a discharge end of the nozzle and is arranged between the outer wall and the interior wall. The fuel flow path includes a first inlet portion and a volute. The first inlet portion is generally offset from a center of the fuel swirler.
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes
F23D 11/10 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
26.
Compensating for thermal expansion via controlled tube buckling
One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel. The fuel injector also has an outlet fitting for delivering fuel through a nozzle to a combustor of the gas turbine engine. An injector support extends between the inlet fitting and the outlet fitting and has an internal bore therethrough. A fuel tube extends from the inlet fitting through the internal bore of the injector support to the outlet fitting. The injector support has a greater coefficient of thermal expansion than the fuel tube. At room temperature the fuel tube is under compressive stress such that the fuel tube is buckled. As a result of differential thermal expansion of the fuel tube and the injector support during engine operation the fuel tube is relieved of compressive stress.
A fuel system includes an external cool air source, and a fuel injector. The fuel injector includes a fuel circuit, an outer air circuit, an inner air circuit, and an outlet. The fuel circuit receives liquid fuel from a fuel inlet. The outer air circuit receives cool air from the cool air source and substantially surrounds the fuel circuit. The inner air circuit is in fluid communication with the outer air circuit and a portion of the fuel circuit substantially surrounds the inner air circuit. The outlet provides atomized fuel from the fuel circuit, outer air circuit and inner air circuit to a combustor.
F02M 53/08 - Injectors with heating, cooling, or thermally-insulating means with air cooling
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
F01N 3/025 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust by means of filters using means for regenerating the filters, e.g. by burning trapped particles using fuel burner or by adding fuel to exhaust
F23D 11/10 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
A method of actively controlling pattern factor in a gas turbine engine includes the steps of issuing fuel into a combustion chamber of a gas turbine engine through one or more circumferentially disposed fuel injectors, determining an initial circumferential pattern factor in the combustion chamber, and adjusting fuel flow through one or more selected fuel injectors based on the initial circumferential pattern factor, to yield a modified circumferential pattern factor in the combustion chamber. The step of determining the circumferential pattern factor can include the steps of detecting a chemiluminescent signature within the combustor, correlating the chemiluminescent signature to an equivalence ratio, and computing the initial circumferential pattern factor based on the equivalence ratio. Alternatively, the step of determining the circumferential pattern factor can include the steps of measuring temperatures at a plurality of circumferential positions at the combustor exit and computing the initial circumferential pattern factor based on the measured temperatures.
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
29.
Active pattern factor control for gas turbine engines
A method of actively controlling pattern factor in a gas turbine engine includes the steps of issuing fuel into a combustion chamber of a gas turbine engine through one or more circumferentially disposed fuel injectors, determining an initial circumferential pattern factor in the combustion chamber, and adjusting fuel flow through one or more selected fuel injectors based on the initial circumferential pattern factor, to yield a modified circumferential pattern factor in the combustion chamber. The step of determining the circumferential pattern factor can include the steps of detecting a chemiluminescent signature within the combustor, correlating the chemiluminescent signature to an equivalence ratio, and computing the initial circumferential pattern factor based on the equivalence ratio. Alternatively, the step of determining the circumferential pattern factor can include the steps of measuring temperatures at a plurality of circumferential positions at the combustor exit and computing the initial circumferential pattern factor based on the measured temperatures.
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
A nozzle (40) includes an inlet at an upstream end of the nozzle, a discharge outlet at a downstream end of the nozzle, and a fluid delivery passage extending between the inlet and the discharge outlet. Exterior (210) and interior (208) walls of the nozzle (40) have downstream tip ends that are relatively longitudinally movable at one or more interfaces. An internal insulating gap (206b) is interposed between the interior and exterior walls to insulate fuel from ambient temperature conditions exterior to the nozzle. One or more flexible (222) seal structures internal to the nozzle isolate a portion of the insulating gap (206b) from any ambient fluid entering into the gap through the one or more interfaces while providing relative movement between interior and exterior walls of the nozzle.