Patent Publication Number: US-11639795-B2

Title: Tapered fuel gallery for a fuel nozzle

Description:
BACKGROUND OF THE DISCLOSURE 
     1. Technical Field 
     This disclosure relates generally to a turbine engine and, more particularly, to a fuel injector for the turbine engine. 
     2. Background Information 
     A fuel nozzle for a gas turbine engine includes an internal fuel circuit. This fuel circuit is configured to direct fuel through the fuel nozzle to a fuel nozzle outlet for injection into a combustion chamber of the turbine engine. The fuel circuit may include an annular fuel gallery that distributes the fuel to multiple exit passages. While such a fuel nozzle has various benefits, there is still room in the art for improvement. 
     SUMMARY OF THE DISCLOSURE 
     According to an aspect of the present disclosure, a fuel injector is provided for a turbine engine. This fuel injector includes a fuel nozzle, and the fuel nozzle includes a gallery, a plurality of feed passages and a plurality of exit passages. The gallery extends within the fuel nozzle circumferentially around an axis between a first end of the gallery and a second end of the gallery. A size of the gallery changes as the gallery extends circumferentially around the axis between the first end of the gallery and the second end of the gallery. The feed passages extend within the fuel nozzle to the gallery. The feed passages are configured to supply fuel to the gallery. The exit passages extend within the fuel nozzle from the gallery. The exit passages are configured to receive the fuel from the gallery. 
     According to another aspect of the present disclosure, another fuel injector is provided for a turbine engine. This fuel injector includes a fuel nozzle, and the fuel nozzle includes a gallery, a feed passage and a plurality of exit passages. The gallery extends within the fuel nozzle circumferentially around an axis between a first end of the gallery and a second end of the gallery. A size of the gallery decreases as the gallery extends circumferentially around the axis from an intermediate location towards the first end of the gallery. The size of the gallery decreases as the gallery extends circumferentially around the axis from the intermediate location towards the second end of the gallery. The feed passage extends within the fuel nozzle to the gallery. The feed passage is configured to supply fuel to the gallery. The exit passages extend within the fuel nozzle from the gallery. The exit passages are configured to receive the fuel from the gallery. 
     According to still another aspect of the present disclosure, another fuel injector is provided for a turbine engine. This fuel injector includes a fuel nozzle, and the fuel nozzle includes a gallery, a feed passage and a plurality of exit passages. The gallery extends within the fuel nozzle circumferentially around an axis less than one-hundred and eighty degrees between a first end of the gallery and a second end of the gallery. A size of the gallery changes as the gallery extends circumferentially around the axis between the first end of the gallery and the second end of the gallery. The feed passage extends within the fuel nozzle to the gallery. The feed passage is configured to supply fuel to the gallery. The exit passages extend within the fuel nozzle from the gallery. The exit passages are configured to receive the fuel from the gallery. 
     The size of the gallery may decrease as the gallery extends circumferentially around the axis away from an intermediate location towards the first end of the gallery. The size of the gallery may decrease as the gallery extends circumferentially around the axis away from the intermediate location towards the second end of the gallery. The feed passage may be fluidly coupled to the gallery at the intermediate location. 
     The size of the gallery may decrease as the gallery extends circumferentially around the axis from the first end of the gallery towards the second end of the gallery. The feed passage may be fluidly coupled to the gallery at the first end of the gallery. 
     An axial height of the gallery may change as the gallery extends circumferentially around the axis between the first end of the gallery and the second end of the gallery. 
     A radial width of the gallery may change as the gallery extends circumferentially around the axis between the first end of the gallery and the second end of the gallery. 
     A cross-sectional area of the gallery may change as the gallery extends circumferentially around the axis between the first end of the gallery and the second end of the gallery. 
     The size of the gallery may decrease as the gallery extends circumferentially around the axis from the first end of the gallery to the second end of the gallery. 
     The feed passages may be fluidly coupled to the gallery at the first end of the gallery. 
     The feed passages may include a first feed passage that is fluidly coupled with the gallery at a first feed passage orifice. The exit passages may include a first exit passage that is fluidly coupled with the gallery at a first exit passage orifice. The first exit passage orifice may be circumferentially between the first feed passage orifice and the first end of the gallery. 
     The size of the gallery may decrease as the gallery extends in a first direction circumferentially around the axis from an intermediate location towards the first end of the gallery. The size of the gallery may decrease as the gallery extends in a second direction circumferentially around the axis from the intermediate location towards the second end of the gallery. 
     At least one of the feed passages may be fluidly coupled to the gallery at the intermediate location. 
     The gallery may extend, more than two-hundred and seventy degrees and less than three-hundred and sixty degrees, circumferentially around the axis from the first end of the gallery to the second end of the gallery. 
     The gallery may extend, less than one-hundred and eighty degrees, circumferentially around the axis from the first end of the gallery to the second end of the gallery. 
     A first of the exit passages may extend along a centerline that is non-parallel with the axis. 
     The intermediate location may be about circumferentially midway between the first end of the gallery and the second end of the gallery. 
     The feed passage may extend to and may be fluidly coupled with the gallery at the intermediate location. 
     A first set of the exit passages may extend from and may be fluidly coupled with the gallery circumferentially between the first end of the gallery and the intermediate location. 
     A second set of the exit passages may extend from and may be fluidly coupled with the gallery circumferentially between the second end of the gallery and the intermediate location. 
     The present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof. 
     The foregoing features and the operation of the invention will become more apparent in light of the following description and the accompanying drawings. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG.  1    is a side sectional schematic illustration of an aircraft propulsion system. 
         FIG.  2    is a cross-sectional schematic illustration of a fuel system for delivering fuel to a turbine engine combustor. 
         FIG.  3    is a partial side sectional illustration of the turbine engine combustor and the fuel delivery system. 
         FIG.  4    is a side sectional illustration of a fuel nozzle arranged with portion of a combustor wall. 
         FIG.  5    is a cross-sectional illustration of the fuel nozzle taken along line  5 - 5  in  FIG.  4   . 
         FIG.  6    is a cross-sectional illustration of the fuel nozzle taken along line  6 - 6  in  FIG.  4   . 
         FIGS.  7  and  8    are side illustrations of a fuel nozzle circuit within the fuel nozzle, where internal volumes of the fuel nozzle circuit are positively depicted. 
         FIG.  9    is a cross-sectional illustration of the fuel nozzle configured with a radially tapering fuel gallery. 
         FIG.  10    is a perspective illustration of a portion of the fuel nozzle circuit configured with skewed exit passages, where the internal volumes of the fuel nozzle circuit are positively depicted. 
         FIG.  11    is a cross-sectional illustration of the fuel nozzle depicted with fuel flowing within an arcuate fuel gallery. 
         FIG.  12    is a cross-sectional illustration of a prior art fuel nozzle depicted with fuel flowing within an annular fuel gallery. 
         FIG.  13    is a cross-sectional illustration of a fuel nozzle configured with a double tapered fuel gallery. 
         FIGS.  14  and  15    are cross-sectional illustration of fuel nozzles configured with multiple fuel galleries. 
         FIG.  16    is a side sectional illustration of a multi-segment fuel nozzle arranged with portion of the combustor wall. 
     
    
    
     DETAILED DESCRIPTION 
       FIG.  1    illustrates an aircraft propulsion system  20  with a turbofan gas turbine engine  22 . This turbine engine  22  extends along a centerline  24  of the engine  22  between an upstream airflow inlet  26  and a downstream airflow exhaust  28 . The turbine engine  22  includes a fan section  30 , a compressor section  32 , a combustor section  34  and a turbine section  36 . 
     The fan section  30  includes a fan rotor  38 . The compressor section  32  includes a compressor rotor  40 . The turbine section  36  includes a high pressure turbine (HPT) rotor  42  and a low pressure turbine (LPT) rotor  44 , where the LPT rotor  44  is configured as a power turbine rotor. Each of these rotors  38 ,  40 ,  42  and  44  includes a plurality of rotor blades arranged circumferentially around and connected to one or more respective rotor disks. 
     The fan rotor  38  is connected to the LPT rotor  44  through a low speed shaft  46 . The compressor rotor  40  is connected to the HPT rotor  42  through a high speed shaft  48 . The low speed shaft  46  and the high speed shaft  48  of  FIG.  1    are concentric with one another and rotatable about the engine centerline  24 ; e.g., a rotational axis. The low speed shaft  46  extends through a bore of the high speed shaft  48  between the fan rotor  38  and the LPT rotor  44 . 
     During operation, air enters the turbine engine  22  through the airflow inlet  26 . This air is directed through the fan section  30  and into a core flowpath  50  and a bypass flowpath  52 . The core flowpath  50  extends sequentially through the engine sections  32 ,  34  and  36 ; e.g., an engine core. The air within the core flowpath  50  may be referred to as “core air”. The bypass flowpath  52  extends through a bypass duct, which bypasses the engine core. The air within the bypass flowpath  52  may be referred to as “bypass air”. 
     The core air is compressed by the compressor rotor  40  and directed into an annular combustion chamber  54  of an annular combustor  56  in the combustor section  34 . Fuel is injected into the combustion chamber  54  and mixed with the compressed core air to provide a fuel-air mixture. This fuel-air mixture is ignited and combustion products thereof flow through and sequentially cause the HPT rotor  42  and the LPT rotor  44  to rotate. The rotation of the HPT rotor  42  drives rotation of the compressor rotor  40  and, thus, compression of air received from an inlet into the core flowpath  50 . The rotation of the LPT rotor  44  drives rotation of the fan rotor  38 , which propels bypass air through and out of the bypass flowpath  52 . The propulsion of the bypass air may account for a significant portion (e.g., a majority) of thrust generated by the turbine engine  22 . 
     Referring to  FIG.  2   , the turbine engine  22  includes a fuel system  58  for injecting the fuel into the combustion chamber  54 . This fuel system  58  includes a fuel source  60 , a fuel supply circuit  62  and one or more fuel injectors  64 . 
     The fuel source  60  of  FIG.  2    includes a fuel reservoir  66  and a fuel regulator  68 . The fuel reservoir  66  may be configured as or otherwise include a container; e.g., a tank, a cylinder, a pressure vessel, a bladder, etc. The fuel reservoir  66  is configured to contain and hold a quantity of the fuel. The fuel regulator  68  may be configured as or otherwise include a pump and/or a valve. The fuel regulator  68  is configured to control flow of the fuel from the fuel reservoir  66  to one or more downstream components of the fuel system  58 . The fuel regulator  68  of  FIG.  2   , for example, directs (e.g., pumps) the fuel out from the fuel reservoir  66  to the fuel supply circuit  62  for delivery to fuel injectors  64 . 
     The fuel supply circuit  62  is configured to deliver the fuel received from the fuel source  60  to the fuel injectors  64 . The fuel supply circuit  62  of  FIG.  2   , for example, includes a fuel supply circuit input passage  70 , a fuel supply circuit manifold  72  and one or more fuel supply circuit output passages  74 . The input passage  70  is between, connected to and fluidly couples the fuel source  60  and the manifold  72 . The manifold  72  is between, connected to and fluidly couples the input passage  70  and the output passages  74 . The manifold  72  is thereby operable to (e.g., substantially evenly) distribute the fuel received from the fuel source  60  through the input passage  70  to the output passages  74 . Each of the output passages  74  is between, connected to and fluidly couples the manifold  72  and a respective one of the fuel injectors  64 . Each output passage  74  is thereby operable to direct the fuel received from the manifold  72  to the respective fuel injector  64 . 
     The fuel injectors  64  of  FIG.  2    are arranged circumferentially about the engine centerline  24  in an annular array. Referring to  FIG.  3   , each fuel injector  64  includes a fuel injector base  76 , a fuel injector stem  78  and a fuel injector nozzle  80 , referred to below as a “fuel nozzle”. 
     The injector base  76  is configured to connect the respective fuel injector  64  to a static structure of the turbine engine  22 . The injector base  76  of  FIG.  3   , for example, mounts the respective fuel injector  64  and its injector stem  78  to a case  82  of the turbine engine  22 . Briefly, this turbine engine case  82  may be configured as a diffuser case. The turbine engine case  82  of  FIG.  3   , for example, is spaced from and circumscribes the combustor  56  so as to at least partially form a diffuser plenum  84  surrounding the combustor  56 . 
     The injector stem  78  is configured to locate and support the fuel nozzle  80 . The injector stem  78 , for example, structurally connects the fuel nozzle  80  to the injector base  76 . The injector stem  78  of  FIG.  3    extends within/through the diffuser plenum  84  from the injector base  76  to the fuel nozzle  80 . The injector stem  78  also forms and/or shields at least one internal fuel injector fuel conduit  88  that fluidly couples a respective one of the output passages  74  to the fuel nozzle  80 . 
     Referring to  FIG.  4   , the fuel nozzle  80  is mated with the combustor  56 . A head  90  of the fuel nozzle  80  of  FIG.  4   , for example, is received by and may project through a receptacle  92  in a wall  94  of the combustor  56 ; e.g., an opening in an annular bulkhead of the combustor  56 . The fuel nozzle head  90  may be configured to float within the receptacle  92 . Alternatively, the fuel nozzle head  90  may be fixedly attached to the combustor wall  94 . 
     The fuel nozzle  80  of  FIG.  4    includes an internal fuel nozzle circuit  96 . This fuel nozzle circuit  96  is configured to receive the fuel from the fuel conduit  88  and direct that received fuel out of the fuel nozzle head  90  into the combustion chamber  54 . The fuel nozzle circuit  96  of  FIG.  4    includes an arcuate (non-annular) fuel gallery  98 , one or more fuel feed passages  100 A and  100 B (generally referred to as “ 100 ”) and a plurality of fuel exit passages  102 A-D (generally referred to as “ 102 ”); see also  FIGS.  5  and  6   . The fuel nozzle circuit  96  of  FIG.  4    may also include an annular fuel film passage  104 . 
     The fuel gallery  98  extends axially within the fuel nozzle  80  along an axis  106  between and to an axial first (e.g., back, upstream) side  108  of the fuel gallery  98  and an opposite axial second (e.g., front, downstream) side  110  of the fuel gallery  98 , which axis  106  may be an axial centerline and/or a spray axis of the fuel nozzle  80 . The fuel gallery  98  extends radially within the fuel nozzle  80  relative to the axis  106  between and to a radial inner side  112  of the fuel gallery  98  and an opposite radial outer side  114  of the fuel gallery  98 . Referring to  FIGS.  5  and  6   , the fuel gallery  98  extends circumferentially within the fuel nozzle  80  partially around the axis  106  between and to a circumferential first end  116  of the fuel gallery  98  and an opposite circumferential second end  118  of the fuel gallery  98 . More particularly, the fuel gallery  98  extends circumferentially around the axis  106  from the gallery first end  116  to the gallery second end  118  more than two-hundred and seventy degrees (270°) but less than three-hundred and sixty degrees (360°). The fuel gallery  98  of  FIGS.  5  and  6   , for example, extends between three-hundred and fifteen degrees (315°) and three-hundred and forty-five degrees (345°); e.g., about (e.g., +/−2°) three-hundred and thirty degrees (330°). The present disclosure, of course, is not limited to such an exemplary fuel gallery configuration. The fuel gallery  98 , for example, may extend less than two-hundred and seventy degrees (270°) circumferentially around the axis  106  from the gallery first end  116  to the gallery second end  118 ; e.g., between one-hundred and eighty degrees (180°) and two-hundred and seventy degrees (270°). 
     The fuel gallery first end  116  may be configured as an upstream end of the fuel gallery  98 . The fuel gallery second end  118  may be configured as a downstream end of the fuel gallery  98 . 
     Referring to  FIGS.  7  and  8   , the fuel gallery  98  is configured with a size that continuously (or intermittently) changes as the fuel gallery  98  extends circumferentially around the axis  106  from or about the gallery first end  116  to or about the gallery second end  118 . A cross-sectional area of the fuel gallery  98 , for example, may continuously (or intermittently) decrease as the fuel gallery  98  extends circumferentially around the axis  106  from or about the gallery first end  116  to or about the gallery second end  118 . Thus, the fuel gallery cross-sectional area in a first plane  120 A (e.g., parallel and coincident with the axis  106 ) located at (e.g., on, adjacent or proximate) the gallery first end  116  may be larger than the fuel gallery cross-sectional area in a second plane  120 B (e.g., parallel and coincident with the axis  106 ) located at (e.g., on, adjacent or proximate) the gallery second end  118 ; see also  FIG.  5   . This change in the fuel gallery cross-sectional area may be provided by continuously (or intermittently) changing an axial length  122  of the fuel gallery  98  between the opposing gallery sides  108  and  110 . The change in the fuel gallery cross-sectional area may also or alternatively be provided by continuously (or intermittently) changing a radial height  124  of the fuel gallery  98  between the opposing gallery sides  112  and  114 ; see  FIG.  9   . Furthermore, while a geometry (e.g., shape) of the fuel gallery  98  may remain substantially constant as the fuel gallery  98  extends circumferentially around the axis  106  as shown in  FIGS.  4 - 7   , this fuel gallery geometry may alternatively change as the fuel gallery  98  extends circumferentially around the axis  106  in other embodiments. The fuel gallery cross-sectional area may thereby also or alternatively be changed by changing the fuel gallery geometry. 
     Referring to  FIGS.  7  and  8   , the feed passages  100  are configured to fluidly couple the fuel conduit  88  to the fuel gallery  98 . The feed passages  100  of  FIGS.  7  and  8   , for example, are fluidly coupled to the fuel conduit  88  in parallel through, for example, a coupling  126 . This coupling  126  may be configured as a manifold or another type of junction; e.g., T-junction, Y-junction, etc. Each of the feed passages  100  extends within (or into) the fuel nozzle  80  (see  FIG.  4   ) to the fuel gallery  98 . Each of the feed passages  100  of  FIG.  5   , for example, has a respective feed passage orifice  128 A,  128 B (generally referred to as “ 128 ”) (e.g., a feed passage outlet orifice, a fuel gallery inlet orifice) in the gallery first side  108 . 
     The feed passage orifices  128  are located at (e.g., on, adjacent or proximate) the gallery first end  116 ; see also  FIGS.  7  and  8   . The feed passage orifice  128 A, for example, is spaced slightly circumferentially from the gallery first end  116  by a circumferential distance  130 . The feed passage orifice  128 B is spaced more circumferentially from the gallery first end  116  by a circumferential distance  132  that may be different (e.g., greater) than the circumferential distance  130 . Thus, the feed passage orifice  128 A may be located circumferentially between the feed passage orifice  128 B and the gallery first end  116 . The present disclosure, however, is not limited to the foregoing exemplary relative feed passage orifice arrangement. For example, in other embodiments, the feed passage orifices  128  may be equally spaced from the gallery first end  116 . In still other embodiments, one or each of the feed passage orifices  128  may be located directly adjacent or on the gallery first end  116 . 
     Each of the feed passages  100  has a cross-sectional area when viewed, for example, perpendicular to a longitudinal centerline of the respective feed passage  100 . The feed passage cross-sectional areas may be equal. Alternatively, one of the cross-sectional area of one of the feed passages  100  (e.g., the feed passage  100 A or the feed passage  100 B) may be different (e.g., greater or less) than the cross-sectional area of the other feed passage  100  (e.g., the feed passage  100 B or the feed passage  100 A). 
     The exit passages  102  of  FIG.  4    are configured to fluidly couple the fuel gallery  98  to the fuel film passage  104 . Each of the exit passages  102  of  FIG.  4   , for example, extends within the fuel nozzle  80  between and to the fuel gallery  98  and the fuel film passage  104 . Referring to  FIGS.  7  and  8   , the exit passages  102  are thereby fluidly coupled in parallel between the fuel gallery  98  and the fuel film passage  104 . 
     Referring to  FIG.  6   , the exit passages  102  are arranged circumferentially around the axis  106  in an annular (or acuate) array. Each of the exit passages  102  of  FIG.  6    has a respective exit passage orifice  134 A-D (e.g., an exit passage inlet orifice, a fuel gallery outlet orifice) in the gallery second side  110 . 
     The (e.g., upstream-most) exit passage orifice  134 A is located at (e.g., on, adjacent or proximate) the gallery first end  116 ; see also  FIGS.  7  and  8   . The exit passage  102 A, for example, is spaced slightly circumferentially from the gallery first end  116  by a circumferential distance  136 . This circumferential distance  136  may be greater than the circumferential distance  130  and less than the circumferential distance  132 ; see  FIG.  5   . Thus, the exit passage  102 A may be located circumferentially between the feed passage orifice  128 A and the feed passage orifice  128 B. The exit passage  102 A is located circumferentially between the feed passage orifice  128 B and the gallery first end  116 . The feed passage orifice  128 A is located circumferentially between the exit passage orifice  134 A and the gallery first end  116 . The present disclosure, however, is not limited to the foregoing exemplary relative exit passage orifice arrangement. For example, in other embodiments, the exit passage  102 A may be circumferentially aligned with one or each of the feed passage orifices  128 ; e.g., the circumferential distance  136  may be equal to the circumferential distance  130  and/or  132 . The exit passage orifice  134 A may be located circumferentially between each feed passage orifice  128  and the gallery first end  116 , or vice versa. In addition or alternatively, the exit passage  102 A may be located directly adjacent or on the gallery first end  116 . 
     The (e.g., downstream-most) exit passage orifice  134 D is located at (e.g., on, adjacent or proximate) the gallery second end  118 ; see also  FIGS.  7  and  8   . The exit passage  102 D, for example, is spaced slightly circumferentially from the gallery second end  118  by a circumferential distance  138 . This circumferential distance  138  may be equal to or different (e.g., greater or less) than the circumferential distance  136 . The present disclosure, however, is not limited to the foregoing exemplary relative exit passage orifice arrangement. For example, in other embodiments, the exit passage  102 D may be located directly adjacent or on the gallery second end  118 . 
     The (e.g., intermediate) exit passage orifice  134 B and the (e.g., intermediate) exit passage orifice  134 C are located at discrete locations circumferentially between the exit passage orifice  134 A and the exit passage orifice  134 D. The exit passage orifice  134 B is spaced circumferentially from the exit passage orifice  134 A by a circumferential distance  140 . The exit passage orifice  134 B is spaced circumferentially from the exit passage orifice  134 C by a circumferential distance  141 . The exit passage orifice  134 C is spaced circumferentially from the exit passage orifice  134 D by a circumferential distance  142 . The circumferential distances  140 - 142  may be equal such that the exit passages  102  and the orifices  134  are arranged equispaced about the axis  106 . In other embodiments, however, one or more of the circumferential distances  140 - 142  may be different than the other(s). 
     Each of the exit passages  102  has a cross-sectional area when viewed, for example, perpendicular to a longitudinal centerline  144 A-D (generally referred to as “ 144 ”) of the respective exit passage  102 . The exit passage cross-sectional areas may be equal. Alternatively, one of the cross-sectional area of one or more of the exit passages  102  may be different (e.g., greater or less) than the cross-sectional area of one or more of the other exit passages  102 . 
     Referring to  FIG.  7   , at least a portion or an entirety of each exit passage longitudinal centerline  144  may be configured parallel with the axis  106 . Alternatively, referring to  FIG.  10   , one or more or each of the exit passage longitudinal centerline  144  may be configured non-parallel with the axis  106 . Each exit passage longitudinal centerlines  144  of  FIG.  10   , for example, is circumferentially skewed such that its inlet orifice (the exit passage orifice  134 ) is circumferentially offset to its outlet orifice  146 A-D (generally referred to as “ 146 ”). The inlet orifice (the exit passage orifice  134 ) may also or alternatively be radially offset from the outlet orifice  146  such that the respective exit passage longitudinal centerline  144  is also or alternatively radially skewed. 
     Referring to  FIG.  4   , the fuel film passage  104  is configured to fluidly couple the exit passages  102  with a plenum outside of the fuel nozzle head  90 ; e.g., the combustion chamber  54 . The fuel film passage  104  of  FIG.  4   , for example, extends axially within the fuel nozzle  80  along the axis  106  between and to the exit passages  102  and their outlet orifices  146  to a fuel nozzle outlet orifice  148  at a distal end of the fuel nozzle head  90 . The fuel film passage  104  extends radially within the fuel nozzle  80  between and to a (e.g., frustoconical) radial inner surface  150  and an opposing (e.g., frustoconical) radial outer surface  152 . The fuel film passage  104  extends circumferentially completely around the axis  106 , thereby configuring the fuel film passage  104  as an annulus; e.g., a frustoconical annular passage. 
     During fuel injector operation, the fuel conduit  88  delivers the fuel to the feed passages  100 . The feed passages  100  direct the received fuel into the fuel gallery  98 . The fuel gallery  98  distributes the fuel to the exit passages  102 . Each exit passage  102  injects the fuel as a jet into the fuel film passage  104  to impinge against the film passage outer surface  152 . This impingement may disperse the fuel jet into a film and/or may vaporize the fuel. The fuel film passage  104  directs the fuel (e.g., film of vaporized fuel) out of the fuel nozzle head  90  via the fuel nozzle outlet orifice  148  and into the combustion chamber  54  for subsequent ignition and combustion. 
     Within the fuel gallery  98  of  FIG.  11   , the fuel flows circumferentially in a (e.g., counterclockwise) direction from the gallery first end  116  to the gallery second end  118  and is (e.g., substantially equally) distributed to each of the exit passage orifices  134 . Since the fuel gallery  98  tapers (e.g., its cross-sectional area decreases) as the fuel gallery  98  extends from the gallery first end  116  to the gallery second end  118 , a velocity of the fuel at and/or about each exit passage orifice  134  may be substantially equal. For example, the velocity of the fuel flowing within the fuel gallery  98  at and/or about the exit passage orifice  134 A may be approximately equal to (e.g., within +/−5% or 10%) the velocity of the fuel flowing within the fuel gallery  98  at and/or about the exit passage orifice  134 D. The fuel gallery  98 , more particularly, is tailored to maintain an approximately uniform fuel velocity within the fuel gallery  98 . By maintaining a relatively high velocity of fuel flowing through the fuel gallery  98 , there is less time for the fuel flowing through the fuel gallery  98  to heat up and possibly coke (e.g., form hardened deposits, sediment) along walls of the fuel gallery  98 . 
     By contrast,  FIG.  12    illustrates a prior art fuel gallery  1200  with a constant cross-sectional geometry. With such a configuration, velocity of the fuel about each orifice (e.g.,  1202 A, B, C) is greater than the velocity of the fuel about each downstream orifice (e.g.,  1202 B, C, D) since some of the fuel is directed out of the fuel gallery  1200  at the upstream orifice (e.g.,  1202 A, B, C) and the flow area of the fuel gallery  1200  does not change. The fuel downstream of the upstream orifice (e.g.,  1202 A, B, C) is therefore subject to an increased likelihood of coking since that fuel spends more time flowing within the fuel gallery  1200  and being heated before exiting. 
     The fuel gallery  1200  of  FIG.  12    has an annular (full hoop) configuration. Since the fuel may tend to flow in a certain direction about an axis  1204 , a low flow/dead area  1206  may develop circumferentially between an inlet  1208  to the fuel gallery  1200  and the downstream-most outlet orifice  1202 D. The fuel within this dead area  1206  may have a relatively low velocity and/or may recirculated within this dead area  1206 . The fuel within the dead area  1206  may thereby be subject to an even higher likelihood of coking within the fuel gallery  1200 . By contrast, the fuel gallery  98  of the  FIG.  11    has an arcuate configuration to eliminate or substantially reduce a size of such a dead area. 
     As turbine engines are designed to continuously increase in efficiency and thrust capabilities while decrease in size and weight, fuel injectors may be designed to flow/inject less and less fuel. Decreasing fuel flow to the fuel injectors may consequently decrease fuel flow velocity to the fuel injectors. As discussed above, the longer fuel remains in a relatively hot environment such as a fuel nozzle, the more likely that fuel is to coke within the fuel nozzle. The fuel nozzle configuration of the present disclosure is particularly suited for accommodating such lower velocity fuel flows as discussed above. 
     The fuel nozzle  80  of  FIGS.  7  and  8   , for example, is also particularly suited for accommodating fuel system designs with limited fuel pressure available to each fuel injector  64 ; see  FIG.  4   . For example, by providing the fuel nozzle circuit  96  of  FIGS.  7  and  8    with two or more of the feed passages  100 , a smaller fuel pressure drop between the fuel conduit  88  and the fuel gallery  98  can be provided as compared to a fuel nozzle circuit with a similarly sized, single feed passage; e.g., see  FIG.  12   . Note, as fuel injectors and their nozzles are designed with smaller and smaller sizes, sizes of corresponding passages within the fuel injectors and their nozzles are also decreased, particularly when utilizing traditional manufacturing processes such as casting and/or machining. By providing the fuel injector  64  and its fuel nozzle  80  of the present disclosure with relatively low, decreased fuel pressure drop requirements, the fuel system  58  may be configured with one or more additional fuel injectors  64  without requiring additional fuel pressure. 
     Referring to  FIG.  13   , to further decrease pressure drop requirements, the fuel gallery  98  may be configured with a double tapered configuration. With such a configuration, the gallery first end  116  may be configured as a first downstream end of the fuel gallery  98  and the gallery second end  118  may be configured as a second downstream end of the fuel gallery  98 . The exit passage orifices  134  may be generally arranged about the axis  106  as described above; however, the one or more feed passage orifices  128  may be arranged circumferentially intermediately between the gallery ends  116  and  118 . The one or more feed passage orifices  128  of  FIG.  13   , for example, are located at (e.g., on, adjacent or proximate) an intermediate location  154  (e.g., a circumferential midpoint) circumferentially along the fuel gallery  98  between the gallery first end  116  and the gallery second end  118 . The feed passage orifices  128  of  FIG.  13   , for example, are disposed on opposing circumferential sides of the intermediate location  154 , and slightly circumferentially spaced from the intermediate location  154 . The present disclosure, however, is not limited to such an exemplary feed passage orifice arrangement. For example, in other embodiments, the feed passage orifices  128  may be circumferentially aligned (but radially spaced) at the intermediate location  154 . In addition, or alternatively, one of the feed passages  100  may be omitted such that the fuel nozzle  80  includes a single one of the feed passages  100  and a respective single one of the feed passage orifices  128 . 
     The size of the fuel gallery  98  of  FIG.  13    is configured to continuously (or intermittently) change as the fuel gallery  98  extends in a circumferential first direction (e.g., clockwise) from or about the intermediate location  154  to or about the gallery first end  116 . The size of the fuel gallery  98  of  FIG.  13    is also configured to continuously (or intermittently) change as the fuel gallery  98  extends in a circumferential second direction (e.g., counterclockwise) from or about the intermediate location  154  to or about the gallery second end  118 , where the second direction is circumferentially opposite the first direction. The size of the first section  156 A (e.g., first half) of the fuel gallery  98  and the size of the second section  156 B (e.g., second half) of the fuel gallery  98  may change in uniform (the same) but opposite manners. The gallery second section  156 B, for example, may be substantially a mirror image of the gallery first section  156 A; however, the present disclosure is not limited to such a mirror image configuration. The size of each gallery section  156 A,  156 B (generally referred to as “ 156 ”) may change, for example, as described above. For example, the axial length  122  (see  FIGS.  7  and  8   ), the radial height  124  (see  FIG.  9   ) and/or a geometry (e.g., shape) of each gallery section  156  may change (e.g., decrease) as that section  156  extends from or about the intermediate location  154  to or about the respective gallery end  116 ,  118 . 
     A set of one or more of the exit passages  102  (e.g.,  102 A and  102 B) and their orifices  134  (e.g.,  134 A and  134 B) are arranged circumferentially between the intermediate location  154  (as well as the one or more feed passages  100 ) and the gallery first end  116 . A set of one or more of the exit passages  102  (e.g.,  102 C and  102 D) and their orifices  134  (e.g.,  134 C and  134 D) are arranged circumferentially between the intermediate location  154  (as well as the one or more feed passages  100 ) and the gallery second end  118 . 
     As similarly discussed above, the fuel gallery  98  of  FIG.  13    is tailored to maintain an approximately uniform fuel velocity within the fuel gallery  98 . In addition, by positioning the feed passage orifices  128  intermediately (e.g., midway or about midway) between the gallery first end  116  and the gallery second end  118 , the fuel gallery  98  is configured to reduce a maximum (e.g., circumferential) distance the fuel travels through the fuel gallery  98 , for example, by about half as compared to the fuel gallery  98  of  FIG.  6   . By reducing this distance of travel, the fuel gallery  98  of  FIG.  13    may reduce the fuel flow pressure drop across the fuel gallery  98 , for example, by about half. Thus, the fuel gallery  98  of  FIG.  13    may further reduce fuel pressure requirements of the fuel nozzle  80 . 
     Referring to  FIGS.  14  and  15   , the fuel pressure requirements of the fuel nozzle  80  may be alternatively or further reduced by configuring the fuel nozzle  80  with more than one of the fuel galleries  98 . For example, a single annular (or substantially annular) gallery may essentially be divided into two (or more) discrete arcuate fuel galleries  98 . Each of these fuel galleries  98  may be generally configured as described above; however, each fuel gallery  98  may extend circumferentially within the fuel nozzle  80  less than one-hundred and eighty degrees (180°) around the axis  106  to its respective gallery ends  116  and  118 . For example, each fuel gallery  98  may extend between one-hundred and thirty-five degrees (135°) and one-hundred and seventy-five degrees (175°). In another example, each fuel gallery  98  may extend between ninety degrees (90°) and one-hundred and thirty-five degrees (135°). In still another example, each fuel gallery  98  may extend between forty-five degrees (45°) and ninety degrees (90°). The present disclosure, of course, is not limited to the foregoing exemplary ranges. 
     In some embodiments, referring to  FIG.  4   , each fuel nozzle  80  may be configured with one or more air passages  158  and  160 . Each air passage  158 ,  160  of  FIG.  4    is configured to direct compressed air from the diffuser plenum  84  into the combustion chamber  54 . Each air passage  158 ,  160  of  FIG.  4    is further configured to promote mixing of the compressed air with the fuel injected into the combustion chamber  54 . 
     In some embodiments, each fuel nozzle  80  may be configured with a supplemental fuel circuit  162 . This supplemental fuel circuit  162  may include a central fuel exit passage  163  along the axis  106 . The supplemental fuel circuit  162  may be configured as a pilot fuel circuit, which may receive and inject fuel during turbine engine startup. The supplemental fuel circuit  162  may also or alternatively receive and inject fuel during high power turbine engine operation; e.g., during aircraft takeoff or high thrust maneuvers. Of course, in other embodiments, one or more or each of the fuel nozzles  80  may be configured without any additional fuel circuits. 
     In some embodiments, each fuel nozzle  80  may be formed as a monolithic body. 
     At least the fuel nozzle  80  or the entire fuel injector  64 , for example, may be additively manufactured, metal injection molded (MIM), cast, machined and/or otherwise formed as a single, unitary body; e.g., from a single mass of metal. Alternatively, each of the fuel nozzles  80  may be formed from a plurality of discretely formed components which are subsequently assembly together (e.g., via mechanical attachment, bonding, etc.) to provide the respective fuel nozzle  80 . For example, referring to  FIG.  16   , the fuel nozzle  80  may include at least a fuel nozzle body  164 , a fuel nozzle insert  166  and a fuel nozzle head body  168 . At least these fuel nozzle components  164 ,  166  and  168  may collectively form the fuel nozzle circuit  96  within the fuel nozzle  80 . For example, at least the fuel nozzle body  164  may form the feed passages  100 . The fuel nozzle body  164  and the fuel nozzle insert  166  may collectively form the fuel gallery  98  axially therebetween. The fuel nozzle body  164 , for example, may form the fuel gallery sidewalls (e.g.,  108 ,  112  and  114 ). The fuel nozzle insert  166  may form the fuel gallery sidewall (e.g.,  110 ). The fuel nozzle insert  166  may form the exit passages  102 . The fuel nozzle insert  166  and the fuel nozzle head body  168  may collectively form the fuel film passage  104  therebetween. The fuel nozzle insert  166 , for example, may form the film passage inner surface  150 . The fuel nozzle head body  168  may form the film passage outer surface  152 . The present disclosure, however, is not limited to the foregoing exemplary segmented (e.g., non-monolithic) fuel nozzle configuration. 
     The combustor  56  is described above as an annular combustor. However, in other embodiments, the fuel system  58  may be configured to deliver fuel to one or more non-annular combustors; e.g., CAN-type combustors. 
     The fuel system  58  and/or one or more of its fuel injectors  64  may be included in various turbine engines other than the one described above. The fuel system  58 , for example, may be included in a geared turbine engine where a gear train connects one or more shafts to one or more rotors in a fan section, a compressor section and/or any other engine section. Alternatively, the fuel system  58  may be included in a turbine engine configured without a gear train; e.g., a direct drive turbine engine. The fuel system  58  may be included in a geared or non-geared turbine engine configured with a single spool, with two spools (e.g., see  FIG.  1   ), or with more than two spools. The turbine engine may be configured as a turbofan engine, a turbojet engine, a propfan engine, a pusher fan engine, an auxiliary power unit (APU) or any other type of turbine engine. The present disclosure therefore is not limited to any particular types or configurations of turbine engines. In addition, while the turbine engine is described above for use in an aircraft application, the present disclosure is not limited to such aircraft applications. For example, the turbine engine may alternatively be configured as an industrial gas turbine engine, for example, for a land based power plant. 
     While various embodiments of the present disclosure have been described, it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the disclosure. For example, the present disclosure as described herein includes several aspects and embodiments that include particular features. Although these features may be described individually, it is within the scope of the present disclosure that some or all of these features may be combined with any one of the aspects and remain within the scope of the disclosure. Accordingly, the present disclosure is not to be restricted except in light of the attached claims and their equivalents.