Patent Application
20220099290
The present disclosure relates generally to turbine engines, and more particularly to fuel injectors having fuel nozzles for turbine engines, such as an airblast-type fuel nozzle.
A turbine engine typically includes an outer casing extending radially from an air diffuser and a combustion chamber. The casing encloses a combustor for containment of burning fuel. The combustor includes a liner and a combustor dome, and an igniter is mounted to the casing and extends radially inwardly into the combustor for igniting fuel.
The turbine also typically includes one or more fuel injectors for directing fuel from a manifold to the combustor. Fuel injectors also function to prepare the fuel for mixing with air prior to combustion. Each injector typically has an inlet fitting connected either directly or via tubing to the manifold, a tubular extension or stem connected at one end to the fitting, and one or more spray nozzles connected to the other end of the stem for directing the fuel into the combustion chambers. A fuel passage (e.g., a tube or cylindrical passage) extends through the stem to supply the fuel from the inlet fitting to the nozzle. Appropriate valves and/or flow dividers can be provided to direct and control the flow of fuel through the nozzle. The fuel injectors are often placed in an evenly-spaced annular arrangement to dispense (spray) fuel in a uniform manner into the combustion chamber. Additional concentric and/or series combustion chambers may each include their own arrangements of nozzles that can be supported separately or on common stems. In an air-blast nozzle-type, the fuel provided by the injectors is mixed with air and ignited, so that the expanding gases of combustion can, for example, move rapidly across and rotate turbine blades in a gas turbine engine to power an aircraft, or in other appropriate manners in other combustion applications.
One problem that generally persists with conventional aircraft fuel nozzles is heat transfer from the ambient environment to the fuel passing through the nozzle. This may cause the fuel to break down into its constituent components and cause coking deposition within the fuel passages of the nozzle. The coke in the fuel passages of the fuel injector can build up to restrict fuel flow to the nozzle.
Conventional nozzle designs tend to manage thermal energy transfer to the fuel by using heat shields or by transferring the thermal energy through intentionally long thermal paths that can reduce wetted wall temperatures and heat pick-up in the fuel. However, as the trend toward more efficient gas turbine engines continues to increase combustor temperatures, the use of such solutions appears to be reaching their limits. Moreover, the use of such additional heat shields or extra material for thermal path lengths increases the weight of the nozzles, which generally is disadvantageous in aircraft design.
An aspect of the present disclosure provides a unique fuel injector having particular application in an aircraft gas turbine engine, and more particularly, a unique fuel nozzle that reduces fuel temperatures and/or thermal stresses compared to a conventional design.
According to one aspect, the unique fuel nozzle is configured to transport bulk fuel flow further along the nozzle before being split or spread downstream in the fuel circuit for final spray distribution. The transport of bulk fuel flow downstream within the fuel nozzle reduces the surface area (and more particularly the surface area to volume ratio) of fuel exposed to heat transfer at points along this section of the fuel circuit, which promotes lower fuel temperatures and reduces the possibility of coking.
More particularly, according to an aspect, a fuel injector includes: a housing stem; a fuel nozzle operatively coupled to the housing stem, the fuel nozzle extending in a longitudinal direction between an upstream end and a downstream discharge end of the fuel nozzle, the fuel nozzle comprising a fuel circuit having an inlet section and an outlet section; and a fuel conduit extending through the housing stem into the fuel nozzle to form the inlet section of the fuel circuit, and extending through the fuel nozzle in the longitudinal direction toward the downstream discharge end to form an upstream portion of the fuel circuit; wherein the fuel conduit is configured to provide bulk fuel flow through the housing stem and the upstream portion of the fuel circuit, the fuel conduit fluidly connecting downstream to a fuel manifold located at an intermediate longitudinal position in the fuel nozzle between the upstream end and the downstream discharge end, the fuel manifold being configured to split the bulk fuel flow into a plurality of fuel flow passages in a downstream portion of the fuel circuit for fuel distribution through the outlet section and fuel discharge from the fuel nozzle.
According to another aspect, the unique fuel nozzle reduces high thermal conductivity contact paths between an external wall of the nozzle in thermal communication with ambient environment and an internal portion of the nozzle in thermal communication with the fuel circuit. Such a design promotes a reduction in the heat pick-up in the fuel and can thus promote lower wetted wall temperatures.
More particularly, according to an aspect a fuel injector includes: a housing stem; a fuel nozzle operatively coupled to the housing stem, the fuel nozzle including an internal wall in heat transfer relation with fuel flowing through the nozzle, and an external wall in heat transfer relation with ambient environment; wherein the internal wall and the external wall are coupled together via a plurality of legs that are circumferentially spaced apart from each other about a longitudinal axis of the fuel nozzle for minimizing thermal conduction and heat pick-up in the fuel.
According to another aspect, the unique fuel injector is configured to minimize stresses caused by thermal growth mismatches in different regions of the fuel flow path.
More particularly, according to an aspect a fuel injector includes: a housing stem; a fuel nozzle operatively coupled to the housing stem, the fuel nozzle extending in a longitudinal direction between an upstream end and a downstream discharge end of the fuel nozzle; and a fuel tube extending through the housing stem into the fuel nozzle; wherein the fuel tube includes a coiled section contained within a portion of the fuel nozzle for compensating for thermal growth mismatches of the fuel injector.
The following description and the annexed drawings set forth certain illustrative embodiments of the invention. These embodiments are indicative, however, of but a few of the various ways in which the principles of the invention may be employed. Other objects, advantages and novel features according to aspects of the invention will become apparent from the following detailed description when considered in conjunction with the drawings.
The principles and aspects according to the present disclosure have particular application to fuel injectors and nozzles for gas turbine engines, such as airblast fuel nozzles, and thus will be described below chiefly in this context. It will of course be appreciated, and also understood, that the principles and aspects according to the present disclosure may be useful in other applications including other fuel nozzle applications, or more generally applications where a fluid is injected by a nozzle, especially under high-temperature conditions.
Referring to
A fuel injector 30 is received within an aperture 32 formed in the engine casing 12 and extends inwardly through an aperture 34 in the combustor liner 22. The fuel injector 30 includes a fitting 36 exterior of the engine casing 12 for receiving fuel, such as by connection to a fuel manifold or fuel line (not shown); a fuel nozzle 40 disposed within the combustor 20 for dispensing fuel; and a housing stem 42 interconnecting and structurally supporting the fuel nozzle 40 with respect to fitting 36. The fuel injector 30 is suitably secured to the engine casing 12, such as via an annular flange 41 that may be formed in one piece with the housing stem 42 proximate the fitting 36. The flange 41 extends radially outward from the housing stem 42 and includes appropriate means, such as apertures, to allow the flange 41 to be easily and securely connected to, and disconnected from, the casing 12 of the engine using, for example, fasteners, such as bolts or rivets. The housing stem 42 has a thickness sufficient to support the fuel nozzle 40 in the combustor when the injector is mounted to the engine, and is formed of material appropriate for the particular application.
Turning to
As shown in the conventional design, to reduce the amount of heat pick-up in the fuel flowing through the fuel circuit portion 562, the conventional nozzle 540 is designed with intentionally long thermal path lengths (shown with thermal gradient arrows, T, in the illustration) formed by radially an outer shroud 564 in thermal communication with ambient environment (E) (commonly referred to as the compressor exit temperature). As is apparent, the use of such extra material for increasing the thermal path lengths increases the weight of the conventional nozzle 540, which generally may be disadvantageous for aircraft design.
Also as shown in the conventional design, an end of the fuel conduit 552 extending from the housing stem 542 connects to an inlet section 563 of the fuel circuit portion 562, where the bulk fuel flow through the conduit 552 gets spread around an annular upstream portion 569 of the fuel circuit 562. As the trend toward more efficient gas turbine engines continues to increase compressor exit and combustor temperatures while incorporating lower fuel flows, this higher surface area and/or reduced surface area to volume ratio of spread fuel flow in the conventional nozzle 540 can lead to increased heat pick-up in the fuel, which can increase wetted wall temperatures and can potentially lead to coking of the fuel. In addition, during such higher temperature engine operation, the housing stem 542 may tend to thermally grow radially within the engine casing (designated by double-arrow Y) while the fuel nozzle 540 may tend to thermally grow axially (designated by double-arrow X), whereas cooling provided by the fuel may tend to cause the fuel conduit 552 to not thermally grow as much, which can lead to thermal stresses in the fuel circuit of the conventional design.
The exemplary fuel injector 30 and fuel nozzle 40 described herein solve one or more of these potential issues with the conventional design 530, 540 by providing inter alia a unique configuration that reduces fuel temperatures internal to the nozzle, transports bulk fuel flow downstream within the fuel nozzle to promote lower fuel temperatures, minimizes high thermal conductivity contact paths between an annular outer shroud of the nozzle and the fuel circuit to promote lower fuel temperatures, reduces mass of the fuel nozzle, and/or minimizes stresses caused by thermal growth mismatches in different regions of the fuel flow path.
Turning particularly to
As shown in greater detail in
In the illustrated embodiment, the lower end of the housing stem 42 forms a rearward portion of an annular outer shroud 64 of the nozzle 40. This rearward portion of the outer shroud 64 may be connected at its downstream end to an annular wall 66 of a forward portion of the nozzle 40 that includes the outer air swirler portion 120. In this manner, the annular outer wall 66 forms a continuation of the outer shroud (e.g., annular wall) 64 provided by the lower portion of the housing stem 42. The connection may be made by any suitable means, such as by welding or brazing at a joint 68. As shown, the outer annular shroud 64 and/or annular wall 66 each may be a single-wall structure that forms a heat shield and surrounds the inner air swirler portion 110 to enclose the insulating gap 58. In the illustrated embodiment, the insulating gap 58 is formed as a relatively large cavity that protects the fluid circuit portion 62 extending therethrough from elevated temperatures. In exemplary embodiments, as noted above, this insulating gap 58 may be in fluid communication with the insulating gap 56 of the housing stem 42 to alleviate increasing temperatures.
The inner air swirler portion 110 (also referred to as inner air swirler 110) has an inner annular wall 112 that bounds an air passage (duct) 114. The annular inner wall 112 may act as a heat shield that extends centrally within the nozzle 40. As shown, the air passage 114 includes an airflow inlet at the upstream (rearward) end 60 of the nozzle 40, and discharges this internal airflow at a downstream end of the inner air swirler 110. In exemplary embodiments, the annular wall 112 of the inner air swirler 110 has a streamlined geometry with the flow area of the air passage 114 decreasing in the direction of flow. This minimizes boundary layer growth and prevents boundary layer separation of the air flow. The inner air swirler 110 also includes radially-extending vanes 116 for directing and swirling airflow downstream through the passage 114.
The outer air swirler portion 120 (also referred to as outer air swirler 120) may extend radially outwardly relative to the annular outer wall 66 of the forward portion of the nozzle 40. As shown in the illustrated embodiment, the outer air swirler 120 may include a first outer air swirler portion 122 and a second outer air swirler portion 124, in which the first (dome) air swirler portion 122 is located radially outward of the second (inner) air swirler portion 124. Each portion 122, 124 of the outer air swirler 120 may include a plurality of vanes 126 and an airflow guide surface 128 tapered radially inwardly to direct airflow in a swirling and converging manner toward the central axis A and toward the downstream end 61 of the fuel swirler. In exemplary embodiments, the vanes 126 are helical, curved or angled vanes. The respective vanes 126 of each portion 122, 124 may be configured to provide co-rotating or counter-rotating air flows of the first outer air swirler portion 122 relative to the second outer air swirler portion 124. The vanes 126 can vary to increase/decrease the direction, speed, or volume of airflow depending upon the particular application. As shown, the (inner) portion 124 of outer air swirler may include an annular, inwardly tapered (frustoconical) downstream end, which may provide the primary outer air flow for atomization of the fuel at the discharge end. The (outer/dome) portion 122 of outer air swirler may include an annular bulbous portion 129, which may provide good spray patternation and droplet dispersion. It is understood that although two air swirler portions 122, 124 are shown, the nozzle may include a fewer or greater number of such portions.
The fuel circuit portion 62 (also referred to as the fuel circuit 62) generally includes an upstream inlet section 70 where fuel enters the nozzle 40, and a downstream outlet section 72 where fuel is distributed from the fuel circuit 62 for being discharged from the nozzle 40. In exemplary embodiments, the fuel circuit 62 internal to the nozzle 40 is configured to transport bulk fuel flow from the fuel conduit 52 in the housing stem 42 through the inlet section 70 of the fuel circuit 62 and downstream in the longitudinal (X) direction from an upstream portion 74 of the fuel circuit 62 to a transition section 76 of the fuel circuit 62, where the bulk fuel flow is then split into a downstream portion 78 of the fuel circuit 62 for final spray distribution. This transportation of bulk fuel flow downstream within the fuel nozzle 40 reduces the surface area (and more particularly the surface area to volume ratio) of fuel exposed to heat transfer at points along the upstream portion 74 of the fuel circuit 62, which thereby promotes lower fuel temperatures and reduces the possibility of coking in the fuel circuit 62.
The inlet section 70 and/or upstream portion 74 of the fuel circuit 62 may be formed by any suitable fuel conduit or combination of conduits having one or more fluid passages configured to transport the bulk fuel. In exemplary embodiments, the fuel circuit upstream portion 74 is formed by at least one fuel conduit section 80 that is a continuation of the at least one fuel conduit 52 extending through the housing stem 42. Such continuity provided between the fuel conduit 52 in the housing stem 42 and the fuel conduit section 80 in the fuel nozzle 40 may be seamless (e.g., a single conduit, such as a tube), or may be segmented (e.g., multiple conduit segments (e.g., tube segments) connected together with a fluid adapter or connector 82). In such manner, a fuel conduit (e.g., conduit 52) extending through the housing stem 42 is considered to extend into the fuel nozzle 40 (e.g., via separate fuel conduit section 80) to form the fuel circuit inlet section 70, and extends internally through the fuel nozzle 40 (e.g., via separate fuel conduit section 80) to form the fuel circuit upstream portion 74 that provides bulk fuel flow to the transition section 76 at an intermediate axial position in the nozzle 40.
In the illustrated embodiment, the upstream portion 74 of the fuel circuit 62 includes at least one fuel tube that constitutes the fuel conduit section 80. The fuel tube (also referred to with reference 80) may have any suitable structure for providing bulk fuel flow, such as a rigid metal tube. As shown, at least a portion of the fuel tube 80 extends axially through the insulating gap 58 toward the downstream end 61 of the nozzle 40 to connect with the transition section 76 of the fluid circuit 62 (described in further detail below). The fuel tube 80 may have one or more bends and/or one or more connectors 82 to provide fluid connection with the fuel conduit 52 on one side and the transition section 76 on the other side. As shown, at least a portion (preferably a majority) of the fuel tube 80 is spaced apart from the annular outer wall(s) 64, 66 of the nozzle 40 to minimize heat transfer into the fuel. Suitable supports located at spaced apart positions along the fuel tube 80 also could be used to damp vibrations if desirable. Also as is apparent in the illustrated embodiment, and in contrast with the annular fuel passage (between outer and inner walls 565, 567) that circumscribes the axis of the conventional nozzle 540, the fuel tube 80 of the exemplary nozzle 40 provides the bulk fuel at a concentrated region within the nozzle 40 (e.g., on one side of the axis A), thereby minimizing heat transfer from the 360-degrees of ambient environment surrounding the fuel nozzle 40.
During high-temperature engine operation, the housing stem 42 may tend to thermally grow radially while the fuel nozzle 40 may tend to thermally grow axially, each or both of which may thermally grow by different amounts than the fuel conduit (tube) 52 and/or fuel conduit section (tube) 80. To mitigate thermal stresses caused by such thermal mismatch, the fuel nozzle 40 may incorporate a coiled tube section 81 for compensating for such thermal growth mismatch. In exemplary embodiments, the coiled tube section 81 is formed as part the upstream portion 74 of the fuel circuit 62 internally to the nozzle 40. In the illustrated embodiment, for example, the fuel conduit (tube) 52 is a straight tube that extends through the length of the housing stem 42, and the coiled tube section 81 is located below the conduit 52 in the portion of the insulating gap 58 formed by the outer shroud 64. The coiled tube section 81 may be at least partially circumscribed around the heatshield wall 112 of the inner air swirler 110 to provide suitable flow performance and adequate compensation for thermal growth mismatch. As shown, the coiled tube section 81 may be continuous (e.g., seamless) with the axially extending fuel conduit section 80, such that these respective sections 80, 81 of the upstream portion 74 are formed with the same tube. As such, in the illustrated embodiment, an end of the coiled tube section 81 of the fuel tube 80 is connected to the fuel conduit (tube) 52 via the connector 82.
As described above, the bulk fuel flow provided by the upstream portion 74 of the fuel circuit 62 (e.g., conduit section 80) may promote lower fuel temperatures by reducing the surface area to volume ratio of fuel flowing through this region of the fuel nozzle 40 as compared to the fuel flow provided by the downstream portion 78. To provide such effect, the bulk fuel flow path provided by the upstream portion 74 generally may be concentrated, confined or “bulked” into a conduit section (e.g., conduit section or tube 80) that is in an angular region on one side of the nozzle axis A as the fuel flows axially, and thus is not spread into an annular region that mostly or entirely encompasses the axis as is the case with the conventional nozzle 540 described above. Also as described above, the bulk fuel flow provided by the upstream portion 74 of the fuel circuit 62 (e.g., conduit section 80) may promote lower fuel temperatures, by providing a major portion (e.g., majority or greater than 50%) of the upstream portion 74 (e.g., conduit section 80) being spaced apart from the annular outer wall(s) 64, 66 of the nozzle 40, which thereby minimizes heat transfer into the fuel. In exemplary embodiments, the bulk fuel flow provided by the upstream portion 74 of the fuel circuit 62 and the bulk fuel flow provided by the fuel conduit 52 in the housing stem 42 have effectively the same bulk fluid flow characteristic(s), such as by mass or volumetric flow.
To maximize the benefit provided by the bulk fuel flow in the upstream portion 74 of the fuel circuit 62, it generally may be advantageous to maximize the axial distance of such bulk fuel flow in the longitudinal direction of the nozzle 40. This, however, is weighed against such factors as providing a suitable distance for the fuel circuit downstream portion 78 that will allow sufficient flow distribution to provide adequate spray performance (e.g., fine atomization, spray uniformity, spray angle, etc.). In exemplary embodiments, the axial distance (L1) provided by the fuel circuit upstream portion 74 that provides bulk fuel flow (including, for example, conduit section 80 and coil section 81) is at least 30% or more of the overall axial distance (L1+L2) of the fuel circuit 62 (as measured from the axial location of the inlet section 70 (where fuel enters the nozzle 40) to the axial location of the outlet section 72 (where fuel is distributed from the fuel circuit 62). More particularly, the axial distance (L1) of the upstream portion 74 providing bulk fuel flow may be in a range from 30% to 99% of the overall axial distance (L1+L2) of the fuel circuit 62 (such as 30%, 40%, 50%, 60%, 70%, 80%, 90%, or 99%, including all values and subranges between the stated values). The fuel circuit downstream portion 78 which constitutes the split fuel flow may have an axial distance (L2) that is the balance of the overall fuel circuit axial distance (L1+L2), for example.
The transition section 76 of the fuel circuit 62 may be any suitable structure or combination of structures configured to split the bulk fuel flow from the upstream portion 74 into the downstream portion 78 of the fuel circuit 62. Likewise, the split fuel flow may be provided in any suitable manner by any suitable structure(s), such as by branching the fuel into multiple passages, or the like. Generally, such split fuel flow caused by the transition section 76 will have different fluid flow characteristic(s) (e.g., velocity, pressure, etc.) and/or different thermal absorption characteristic(s) at points along the downstream portion 78 as compared to the bulk fuel flow at points along the upstream section 74. For example, splitting the fuel flow generally may increase the surface area of the fuel exposed to temperature at points along the wetted wall of the downstream flow path, may reduce the volume of fuel along such points, and/or may reduce the surface area to volume ratio of fuel along such points. The transition section 76 generally will be the first section along the fuel circuit 62 that provides a split in fuel flow among multiple passages that causes a significant change in the fluid flow and/or thermal absorption characteristics of the fuel when comparing the upstream portion 74 to the downstream portion 78.
Still referring to
Referring to
In the illustrated embodiment, each of the fuel flow passages 88 has a cross-sectional area (transverse to a direction of fluid flow) that is less than a cross-sectional area (transverse to a direction of fluid flow) of fuel conduit section (e.g., tube) 80 that is part of the fuel circuit upstream portion 74. This enables fuel velocity to increase as it passes through the smaller passages 88 toward the outlet section 72, which improves spray performance. As noted above, however, such split fuel flow provided by the passages 88 in the downstream portion 78 may increase the outer surface area to volume ratio of fuel at points in the downstream portion 78 compared to the upstream portion 74, which may increase heat pick-up in the fuel in this downstream portion 78. By way of non-limiting example, in the illustrated embodiment, six fuel passages 88 are provided, each of which have an outer surface area at the wall that is 25% the surface area per 1 mm axial length as compared to the outer surface area per 1 mm axial length of the wall of the fuel tube. This gives a total surface area of the six fuel passages per 1 mm axial length that is 50% greater than the surface area per 1 mm axial length of the wall of the fuel tube 80. Accordingly, as described above, it generally may be beneficial to extend the bulk fuel flow (or minimize the split or spread fuel flow) as much as possible while still enabling good spray performance from the nozzle 40.
Turning again to
The particular angle of the outlets 89 may vary depending upon the desired swirl for the fuel and/or the geometry of the outlets 89 may vary to tune the flow therethrough to ensure equal pressure drop through each outlet 89. In exemplary embodiments, each of the outlets 89 of the fuel passages 88 is configured as a metering slot 89 (with the same reference numeral 89 used to refer to both the outlet opening and metering slot for clarity). The metering slots 89 may be configured to meter the amount of fuel flowing through the passages 88 and/or direct the fuel at the discharge end 61 in a particular manner. The metering slots 89 may thus provide improved flow uniformity as the fuel is discharged from the fuel circuit 62, which may reduce recirculation zones and hot spotting, thereby improving the lifespan of the turbine. The metering slots 89 may have a cross-sectional area that is the same as or that is different from the cross-sectional area of the fuel passage 88. In addition, although each of the metering slots 89 is shown with the same cross-sectional area, and each is shown angled and oriented in the same direction, it is understood that one or more of the metering slots 89 may have different cross-sectional areas, angles, or orientations from other one(s) of the metering slots. Such differing configurations may be used to increase/decrease the amount of swirling of the fuel and/or to increase/decrease the velocity of the fuel exiting the orifices for staging the fuel, as may be desired for particular applications.
In exemplary embodiments, the swirl annulus 91 is part of a prefilmer 90 which such construction may be well-known in the art. In the illustrated embodiment, for example, the outlets 89 (e.g., metering slots) of the fuel passages 88 all open into an upstream edge of the swirl annulus 91 and provide a swirling motion of flow to direct fuel towards a tapered portion 92 of the prefilmer 90. The swirling and radially inwardly directed fuel in the prefilmer 90 is then discharged from the outlet section 72 of the fuel circuit 62.
As shown, the prefilmer 90 is disposed downstream of the inner air swirler 110 and upstream of the outer air swirler 120. The downstream tapered portion 92 of the prefilmer 90 may assist the fuel in forming a thin, continuous sheet across the prefilmer surface, and in accelerating the fuel as the fuel passes downstream along the surface. The aerodynamic drag forces from the air/fuel interface may accelerate the fuel, to assist distributing the fuel evenly in a thin sheet across the prefilmer surface. The air flow from the inner air swirler 110 passes inwardly of the fuel streams to form a swirling, inner air flow centrally of the fuel sheet to aid the atomization of the fuel downstream from the prefilmer discharge end 94. In the illustrated embodiment, the discharge end 94 of the prefilmer 90 is the axial end (outlet section 72)) of the fuel circuit 62. As the fuel sheet releases from the downstream lip of the prefilmer surface at the discharge end 94, the sheet is impacted by the converging air from the outer air swirler 120 (e.g., including first air swirler portion 122 and second air swirler portion 124), and the inner air flow provided by the inner air swirler 110. As a result, a fairly significant velocity gradient is established at the prefilmer lip that results in a high shear rate at the locations where the incoming fuel streams impinge. The sheet is quickly atomized into a fine dispersion, and is evenly distributed in a conical spray. This enables the nozzle 40 to provide good spray performance, a wide spray angle, and improved spray uniformity with essentially no streaks, voids or non-homogeneities.
Alternatively or additionally to the foregoing benefits provided by expanding bulk fuel flow in the nozzle 40, the exemplary fuel nozzle 40 may include one or more additional features that promote a reduction in the heat pick-up in the fuel and can thus promote lower wetted wall temperatures.
For example, referring again to
The exemplary fuel nozzle 40 also may have an annular gap 102 where the external wall 64, 66 comes into proximity with the outlet section 72 of the fuel circuit 62 for the purpose of reducing metal-to-metal contact and heat transfer with the fuel circuit. In such a configuration, the circumferentially spaced apart legs 100 may be the primary or only supports between the external wall 64, 66 and the body portion 63.
The exemplary fuel nozzle 40 also may strategically locate thermal insulation pocket(s) 104 within the nozzle 40. In the illustrated embodiment, for example, an annular pocket is formed around the inner heat shield wall 112 at the axial location corresponding with the downstream portion 78 of the fuel circuit. As described above, the relatively large internal insulating gap 58 (or cavity) also may be provided in the region between the external wall 64, 66 and the body portion (wall) 63. Such a configuration may enable the outer annular shroud (external wall) 64 to be a single wall structure, which may reduce weight of the nozzle.
Overall, the unique nozzle design may be configured to minimize heat pick-up into the fuel circuit as a result of metal-to-metal contact. In exemplary embodiments, the exit of the nozzle may be the only location having 360-degree metal-to-metal contact.
Turning to
It is understood that the fuel nozzle 40 may be made of any suitable material(s) in any suitable manner to accommodate the pressures, flow rates, temperatures, fluid types, external environment, assembly, and other factors apparent from the foregoing description. For example, portions of the nozzle 40 (such as forward end portion having wall 66 and body 63) may be formed as a monolithic (unitary) and seamless construction. This may be accomplished by additive manufacturing methods, such as direct laser deposition, direct metal laser sintering, etc. Alternatively or additionally, the portions of the nozzle 40 may be formed using conventional manufacturing techniques, for example, milling, machining, brazing, welding, or the like. Use of additive manufacturing may be advantageous to facilitate lighter, more complex, and more cost-efficient nozzle designs. By way of example, the straight tube and coiled tube may be created by machining and conventional manufacturing processes, respectively. The tube adaptor can be created by additive manufacturing processes, machining, or forging. The housing stem and inlet fitting can be made by conventional manufacturing or additive manufacturing methods. The inner air heatshield can be created by conventional methods or additive manufacturing. As identified, such a nozzle provides advantages such as lower wetted wall temperatures, fewer joins, fewer components, and lower weight (roughly 25% weight saving on like-for-like parts; 5% for total nozzle).
An exemplary fuel injector for a gas turbine engine of an aircraft having an exemplary fuel nozzle has been described herein. The exemplary fuel injector may include a housing stem, a fuel nozzle coupled to the housing stem, and a fuel conduit extending through the housing stem and into the fuel nozzle where the fuel conduit bends to extend in a longitudinal downstream direction within the fuel nozzle. The fuel conduit may be configured to transport bulk fuel flow further along the nozzle before being split downstream in the fuel circuit for final spray distribution, thereby promoting lower fuel temperatures. The fuel nozzle may minimize metal-to-metal contact between an external wall of the nozzle in thermal communication with ambient environment and an internal portion of the nozzle in thermal communication with the fuel circuit to minimize heat pick-up in the fuel. The fuel conduit may include a coiled section within a cavity of the fuel nozzle for compensating for thermal growth mismatches of the fuel injector.
According to an aspect of the present disclosure, a fuel injector includes: a housing stem; a fuel nozzle operatively coupled to the housing stem, the fuel nozzle extending in a longitudinal direction between an upstream end and a downstream discharge end of the fuel nozzle, the fuel nozzle comprising a fuel circuit having an inlet section and an outlet section; and a fuel conduit extending through the housing stem into the fuel nozzle to form the inlet section of the fuel circuit, and extending through the fuel nozzle in the longitudinal direction toward the downstream discharge end to form an upstream portion of the fuel circuit; wherein the fuel conduit is configured to provide bulk fuel flow through the housing stem and the upstream portion of the fuel circuit, the fuel conduit fluidly connecting downstream to a fuel manifold located at an intermediate longitudinal position in the fuel nozzle between the upstream end and the downstream discharge end, the fuel manifold being configured to split the bulk fuel flow into a plurality of fuel flow passages in a downstream portion of the fuel circuit for fuel distribution through the outlet section and fuel discharge from the fuel nozzle.
Embodiments may include one or more of the following additional features, separately or in any combination.
In some embodiments, the upstream portion of the fuel circuit provided by the fuel conduit has a surface area to volume ratio of that is less than a surface area to volume ratio of the downstream portion of the fuel conduit provided by the plurality of fuel flow passages.
In some embodiments, the upstream portion of the fuel circuit provided by the fuel conduit is confined to a partial angular region on one side of the longitudinal axis as the fuel conduit extends in the longitudinal direction.
In some embodiments, the upstream portion provided by the fuel conduit extends through an insulating gap internal to the fuel nozzle, and a major portion of the upstream portion provided by the fuel conduit is spaced apart from one or more walls of the fuel nozzle that are in heat transfer relation to an external environment of the fuel nozzle.
In some embodiments, the fuel conduit includes a fuel tube having a coiled section internal to the fuel nozzle, the coiled section at least partially circumscribing a longitudinal axis of the fuel nozzle.
In some embodiments, each of the plurality of fuel flow passages of the downstream portion has a cross-sectional area transverse to a direction of fuel flow that is less than a cross-sectional area transverse to a direction of fuel flow of the upstream portion provided by the fuel conduit.
In some embodiments, the plurality of fuel flow passages are internal fuel flow passages enclosed by a body portion of the fuel nozzle.
In some embodiments, the fuel conduit includes a fuel tube that is segmented into sections, with the sections being fluidly connected together via a fluid connector.
In some embodiments, the fuel conduit includes a single unitary fuel tube.
In some embodiments, each of the plurality of fuel flow passages include an outlet that opens into an annulus fluidly connected to the outlet section, the outlets forming an array of outlets circumferentially spaced apart about a longitudinal axis of the fuel nozzle.
In some embodiments, the downstream portion of the fuel circuit includes a fuel prefilmer between the outlets of the plurality of fuel flow passages and the outlet section of the fuel circuit, the annulus being an axially extending swirl annulus at an upstream portion of the fuel prefilmer in which the outlets open into the swirl annulus at an angle to provide swirling fuel flow, and the fuel prefilmer having a radially inwardly converging portion at a downstream portion thereof, the fuel prefilmer being configured to terminate at a downstream prefilmer orifice which forms the outlet section of the fuel circuit.
In some embodiments, the fuel injector further includes an inner air swirler, and an outer air swirler outwardly surrounding the inner air swirler, in which the fuel circuit is radially interposed between the inner air swirler and the outer air swirler.
In some embodiments, an overall axial distance of the fuel circuit is measured from the axial location of the inlet section where fuel enters the fuel nozzle to the axial location of the outlet section where fuel is distributed from the fuel circuit, and wherein an axial distance of the upstream portion providing bulk fuel flow is in a range from 30% to 99% of the overall axial distance of the fuel circuit.
In some embodiments, the fuel manifold is part of a transition section that is a first point of transition from bulk fuel flow to split flow as fuel flows downstream from a section of the fuel conduit in the housing stem.
According to another aspect, a fuel injector includes: a housing stem; a fuel nozzle operatively coupled to the housing stem, the fuel nozzle extending in a longitudinal direction between an upstream end and a downstream discharge end of the fuel nozzle; and a fuel tube extending through the housing stem into the fuel nozzle; wherein the fuel tube includes a coiled section contained within a portion of the fuel nozzle.
Embodiments may include one or more of the foregoing or following additional features, separately or in any combination.
In some embodiments, the fuel nozzle includes an inner air heatshield, and the coiled section is at least partially coiled around the inner air heatshield.
In some embodiments, the fuel tube is segmented into sections, with the sections being fluidly connected together via a fluid connector.
In some embodiments, the fuel tube is a single unitary tube.
In some embodiments, the fuel tube includes an axially extending section that extends in a longitudinal direction of the fuel nozzle downstream of the coiled section, the axially extending section configured to transport bulk fuel flow through the fuel nozzle.
According to another aspect, a fuel injector includes: a housing stem; a fuel nozzle operatively coupled to the housing stem, the fuel nozzle including an internal wall in heat transfer relation with fuel flowing through the nozzle, and an external wall in heat transfer relation with ambient environment; wherein the internal wall and the external wall are coupled together via a plurality of legs that are circumferentially spaced apart from each other about a longitudinal axis of the fuel nozzle.
Embodiments may include one or more of the foregoing or following additional features, separately or in any combination.
In some embodiments, the plurality of legs are equally spaced apart with gaps between the legs.
In some embodiments, the internal wall is formed by a body portion of the nozzle that encloses one or more fuel flow passages internal to the fuel nozzle.
In some embodiments, at least a rearward portion of the external wall is a single wall.
In some embodiments, the plurality of legs are the only coupling points between the inner wall and the external wall.
It is to be understood that terms such as “top,” “bottom,” “upper,” “lower,” “left,” “right,” “front,” “rear,” “forward,” “rearward,” and the like as used herein may refer to an arbitrary frame of reference, rather than to the ordinary gravitational frame of reference.
It is to be understood that all ranges and ratio limits disclosed in the specification and claims may be combined in any manner. It is to be understood that unless specifically stated otherwise, references to “a,” “an,” and/or “the” may include one or more than one, and that reference to an item in the singular may also include the item in the plural.
The term “about” as used herein refers to any value which lies within the range defined by a variation of up to ±10% of the stated value, for example, ±10%, ±9%, ±8%, ±7%, ±6%, ±5%, ±4%, ±3%, ±2%, ±1%, ±0.01%, or ±0.0% of the stated value, as well as values intervening such stated values.
The phrase “and/or” should be understood to mean “either or both” of the elements so conjoined, i.e., elements that are conjunctively present in some cases and disjunctively present in other cases. Other elements may optionally be present other than the elements specifically identified by the “and/or” clause, whether related or unrelated to those elements specifically identified unless clearly indicated to the contrary. Thus, as a non-limiting example, a reference to “A and/or B,” when used in conjunction with open-ended language such as “comprising” can refer, in one embodiment, to A without B (optionally including elements other than B); in another embodiment, to B without A (optionally including elements other than A); in yet another embodiment, to both A and B (optionally including other elements); etc.
The word “or” should be understood to have the same meaning as “and/or” as defined above. For example, when separating items in a list, “or” or “and/or” shall be interpreted as being inclusive, i.e., the inclusion of at least one, but also including more than one, of a number or list of elements, and, optionally, additional unlisted items. Only terms clearly indicated to the contrary, such as “only one of” or “exactly one of,” may refer to the inclusion of exactly one element of a number or list of elements. In general, the term “or” as used herein shall only be interpreted as indicating exclusive alternatives (i.e. “one or the other but not both”) when preceded by terms of exclusivity, such as “either,” “one of,” “only one of,” or “exactly one of.”
The transitional words or phrases, such as “comprising,” “including,” “carrying,” “having,” “containing,” “involving,” “holding,” and the like, are to be understood to be open-ended, i.e., to mean including but not limited to.
Although the invention has been shown and described with respect to a certain embodiment or embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings. In particular regard to the various functions performed by the above described elements (components, assemblies, devices, compositions, etc.), the terms (including a reference to a “means”) used to describe such elements are intended to correspond, unless otherwise indicated, to any element which performs the specified function of the described element (i.e., that is functionally equivalent), even though not structurally equivalent to the disclosed structure which performs the function in the herein illustrated exemplary embodiment or embodiments of the invention. In addition, while a particular feature of the invention may have been described above with respect to only one or more of several illustrated embodiments, such feature may be combined with one or more other features of the other embodiments, as may be desired and advantageous for any given or particular application.
This application claims the benefit of U.S. Provisional Application No. 63/084,591 filed Sep. 29, 2020, which is hereby incorporated herein by reference in its entirety.
| Number | Date | Country | |
|---|---|---|---|
| 63084591 | Sep 2020 | US |
