Patent Publication Number: US-2023160348-A1

Title: System and method for reconfiguring a bleed system

Description:
BACKGROUND 
     The subject matter disclosed herein relates to a gas turbine system and, more particularly, a bleed system for a compressor of the gas turbine system. 
     A gas turbine system includes a compressor, a combustor, and a turbine. The compressor compresses an intake air in one or more stages to produce a compressed air. The combustor mixes the compressed air with fuel and combusts the fuel with the compressed air to generate hot combustion gases. The turbine directs the hot combustion gases through one or more turbine stages to drive rotation of a shaft, which may be coupled to the compressor and a load. Additionally, the gas turbine system may bleed a portion of the compressed air through a conduit of a bleed system to a target location different from the combustor. Unfortunately, the target location may be different in various configurations of the gas turbine system, which may result in the need for different conduit designs to accommodate each of the various configurations of the gas turbine system. Accordingly, a need exists for a bleed system configured to move between different configurations and associated target locations in the gas turbine system, thereby reducing part count inventory. 
     BRIEF DESCRIPTION 
     Certain embodiments commensurate in scope with the originally claimed subject matter are summarized below. These embodiments are not intended to limit the scope of the claimed subject matter, but rather these embodiments are intended only to provide a brief summary of possible forms of the subject matter. Indeed, the subject matter may encompass a variety of forms that may be similar to or different from the embodiments set forth below. 
     In certain embodiments, a system includes a bleed system configured to direct a bleed flow from a compressor section to an exhaust section of a gas turbine engine. The bleed system includes a first bleed conduit section configured to couple to the compressor section, a second bleed conduit section configured to couple to the exhaust section, and a first rotatable joint coupling together adjacent conduits of the first and second bleed conduit sections. The second bleed conduit section is configured to rotate between a plurality of orientations relative to the first bleed conduit section and the compressor section via the first rotatable joint. The plurality of orientations correspond to a plurality of exhaust outlet orientations of the exhaust section. 
     In certain embodiments, a method includes coupling together, via a first rotatable joint, adjacent conduits of first and second bleed conduit sections of a bleed system configured to direct a bleed flow from a compressor section to an exhaust section of a gas turbine engine, wherein the first bleed conduit section is configured to couple to the compressor section, and the second bleed conduit section is configured to couple to the exhaust section. The method further includes rotating, via the first rotatable joint, the second bleed conduit section between a plurality of orientations relative to the first bleed conduit section and the compressor section, wherein the plurality of orientations correspond to a plurality of exhaust outlet orientations of the exhaust section. 
     In certain embodiments, a system includes a compressor section of a gas turbine engine, an exhaust section of the gas turbine engine, and a bleed system configured to direct a bleed flow from the compressor section to the exhaust section. The bleed system includes a first bleed conduit section coupled to the compressor section, a second bleed conduit section coupled to the exhaust section, and a first rotatable joint coupling together adjacent conduits of the first and second bleed conduit sections. The second bleed conduit section is configured to rotate between a plurality of orientations relative to the first bleed conduit section and the compressor section via the first rotatable joint, wherein the plurality of orientations correspond to a plurality of exhaust outlet orientations of the exhaust section. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       These and other features, aspects, and advantages of the present disclosure will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein: 
         FIG.  1    is a schematic diagram of an embodiment of a gas turbine system having a bleed system configured to reorient in a plurality of different positions to accommodate different configurations of an exhaust section; 
         FIG.  2    is a schematic side view of an embodiment of the bleed system of  FIG.  1   , illustrating a plurality of orientations of a second bleed conduit section relative to a first bleed conduit section coupled to a compressor section; 
         FIG.  3    is a schematic cross-sectional view of an embodiment of a rotatable joint configured to enable rotation between the first and second bleed conduit sections of the bleed system of  FIGS.  1  and  2   ; 
         FIG.  4    is a cross-sectional view of an embodiment of the rotatable joint of  FIG.  3   , further illustrating details of an annular clamp configured to enable loosening, tightening, rotation, and separation of adjacent conduits connected at the rotatable joint; 
         FIG.  5    is a schematic view of an embodiment of a valve assembly and a mounting bracket configured to be disconnected and reconnected in different configurations via rotatable joints and removable flanges; 
         FIG.  6    is a partial perspective view of an embodiment of the bleed system coupled to the exhaust section of the gas turbine system of  FIG.  1   , further illustrating details of the second bleed conduit section in a first configuration relative to the first bleed conduit section; and 
         FIG.  7    is a partial perspective view of an embodiment of the bleed system of  FIG.  6   , further illustrating a reorientation of the second bleed conduit section relative to the first bleed conduit section to accommodate a different configuration of the exhaust section. 
     
    
    
     DETAILED DESCRIPTION 
     One or more specific embodiments of the present disclosure will be described below. In an effort to provide a concise description of these embodiments, all features of an actual implementation may not be described in the specification. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers&#39; specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that such a development effort might be complex and time consuming, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure. 
     When introducing elements of various embodiments of the present disclosure, the articles “a,” “an,” “the,” and “said” are intended to mean that there are one or more of the elements. The terms “comprising,” “including,” and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements. 
     A variety of systems, such as compressors, pumps, turbines, and various turbomachines may use a bleed system to bleed a fluid from one location to another. The bleed system may receive a bleed flow from a high pressure region and direct the bleed flow to a low pressure region. As discussed in detail below, the present bleed system includes a single set of components, which are configured to move between a plurality of different configurations, such as different exhaust outlet orientations (e.g., left hand exhaust outlet, right hand exhaust outlet, and top exhaust outlet) of an exhaust section. In other words, rather than using a different bleed system for each exhaust outlet orientation, the disclosed embodiments use the same bleed system (e.g., a single assembly of components) in multiple configurations of the same components, thereby providing a universal bleed system that can accommodate 2, 3, 4, 5, or more different configurations of the exhaust section. 
     Specifically, the present bleed system includes one or more rotational joints, which enable conduit sections to rotate about an axis. The bleed system also includes one or more mounting flanges, which can be reconfigured in different mounting configurations. A first bleed conduit section of the bleed system may remain in a fixed position relative to a compressor section of the gas turbine system, whereas a second bleed conduit section (or multiple bleed conduit sections) may be moved (e.g., rotated) and/or reconfigured to change a target location for delivering a bleed flow. The bleed system also includes a plurality of flexible and/or movable structures (e.g., gimbals, spring hangers, hinges, flexible conduits, and/or rotatable joints) configured to enable freedom of movement to accommodate thermal expansion and contraction and to provide flexibility when reconfiguring the bleed system between a plurality of configurations (e.g., different exhaust outlet orientations). Details of the bleed system are discussed in further detail below with reference to  FIGS.  1 - 7   . 
       FIG.  1    is a block diagram of an embodiment of a gas turbine system  10  having a gas turbine engine  12  to which a bleed system  14  is coupled. In the illustrated embodiment, the bleed system  14  extends between a high pressure region  16  and a low pressure region  18  of the gas turbine system  10 . The bleed system  14  is configured to route a bleed flow between the high pressure region  16  and the low pressure region  18  in a variety of configurations of the gas turbine engine  12 . In particular, the bleed system  14  is configured to move (e.g., rotate) between a plurality of orientations (e.g., angular orientations) about a central axis  20  of the gas turbine system  10 , thereby enabling the same bleed system  14  to be used with various configurations of the gas turbine system  10 , such as different configurations of an exhaust section  22  (e.g., different exhaust outlet orientations, such as exhaust outlets  82  directed crosswise to the central axis  20 ). Without the disclosed embodiments of the bleed system  14 , a different bleed system may be necessary for each different configuration of the exhaust section  22 , which would result in substantially greater manufacturing costs. The disclosed embodiments reduce the number of different bleed systems by incorporating a multi-configuration (e.g., multi-orientation) feature into the design of the bleed system  14 . 
     The gas turbine engine  12  includes an air intake section  24 , a compressor section  26 , a combustion section  28 , a turbine section  30 , the exhaust section  22 , and a load  32 , such as an electrical generator. The gas turbine engine  12  also may include one or more controllers  34  having one or more processors  36 , memory  38 , and instructions  40  stored on the memory  38  and executable by processors  36  to perform various control functions of the gas turbine system  10  and the bleed system  14 . For example, the controller  34  may be configured to control one or more valves of the bleed system  14  to control a bleed flow between the high and low pressure regions  16  and  18 . The air intake section  24  may include one or more air filters, fluid injection systems (e.g., heated fluids and/or cooled fluids), anti-icing systems, silencer baffles, or any combination thereof. The air intake section  24  routes an air flow  42  into one or more compressor stages  44  of a compressor section  26 . 
     The compressor section  26  includes a compressor casing  46 , one or more vanes  48  extending inwardly from the compressor casing  46  in each of the compressor stages  44 , one or more blades  50  extending outwardly from a shaft  52  in each of the compressor stages  44 , and connections  54  with the bleed system  14 . The shaft  52  is configured to rotate a plurality of circumferentially spaced blades  50  in each of the compressor stages  44 , while a plurality of circumferentially spaced vanes  48  remain stationary in each of the compressor stages  44 . The connections  54  may include fluid conduit connections with the bleed system  14 , such as connections  54  at one or more of the compressor stages  44 . The connections  54  may be disposed on opposite sides (e.g., diametrically opposite sides) of the compressor casing  46 , or in any suitable location on the compressor casing  46 . The compressor section  26  outputs a compressed air flow  56  into one or more combustors  58  of the combustion section  28 . 
     Each combustor  58  includes one or more fuel nozzles  60 , which are configured to route the compressed air  56  and fuel  62  from a fuel supply system  64  into a combustion chamber  66  of the combustor  58 . The fuel  62  and the compressed air  56  mix and combust within the combustion chamber  66 , thereby producing hot combustion gases  68  that are routed into the turbine section  30 . In certain embodiments, the combustion section  28  has a single annular combustor  58  disposed circumferentially about a central axis of the gas turbine system  10 . However, in some embodiments, the combustion section  28  includes a plurality of combustors  58  (e.g., combustor cans) spaced circumferentially about the central axis of the gas turbine system  10 . The fuel nozzles  60  may include 1, 2, 3, 4, 5, 6, or more fuel nozzles, which may be configured to operate on one or more fuel circuits. The fuel circuits may be designed to deliver the same fuel or different fuels, such as liquid and gas fuels. Regardless, once the fuel combusts, the hot combustion gases  68  are used to drive the turbine section  30 . 
     The turbine section  30  includes a plurality of turbine stages  70  configured to gradually expand the hot combustion gases  68  and drive components of the gas turbine system  10 . The turbine section  30  includes a turbine casing  72 , one or more turbine vanes  74  extending inwardly from the turbine casing  72  in each of the turbine stages  70 , and one or more turbine blades  76  extending outwardly from a turbine shaft  78  in each of the one or more turbine stages  70 . The turbine shaft  78  is driven to rotate by the hot combustion gases  68  flowing against a plurality of circumferentially spaced turbine blades  76  in each of the turbine stages  70 , while a plurality of circumferentially spaced turbine vanes  74  remain stationary in each of the turbine stages  70 . The hot combustion gases  68  expand through the turbine section  30  while driving rotation of the turbine blades  76  and turbine shaft  78  and then discharge through the exhaust section  22 . 
     The exhaust section  22  includes an exhaust plenum  80  disposed downstream from the turbine section  30 , and the exhaust plenum  80  includes an exhaust outlet  82 . The exhaust outlet  82  may be positioned in a variety of exhaust outlet orientations depending on the particular configuration of the gas turbine system  10 . In the illustrated embodiment, the exhaust outlet  82  is arranged in a right-hand orientation or configuration  84  on a right-hand side of the exhaust plenum  80  (when viewed from an aft end of the gas turbine system  10 ), thereby directing an exhaust flow in a right hand direction as indicated by arrows  86 . However, the exhaust outlet  82  may be arranged in other configurations (shown in phantom lines in  FIG.  1   ), such as a top orientation or configuration  88  to direct a vertical flow of the exhaust gas, or a left-hand orientation or configuration  90  configured to direct the exhaust flow in a left-hand direction as indicated by arrows  92 . As discussed in further detail below, the bleed system  14  may be rotated or moved between the right-hand configuration  84 , the top configuration  88 , and/or the left-hand configuration  90  to accommodate different exhaust outlet orientations of the exhaust outlet  82  while using the same components of the bleed system  14 . 
     In operation, the gas turbine engine  12  receives air through the air intake section  24 , compresses the air in one or more compressor stages  44  via rotation of a plurality of compressor blades  50  in each of the compressor stages  44 , and then routes the compressed air  56  into one or more combustors  58  of the combustion section  28 . The combustors  58  combust the fuel  62  with the compressed air  56  via injection through the fuel nozzles  60  and combustion within the combustion chamber  66 , and then route the hot combustion gases  68  into one or more turbine stages  70 . The turbine stages  70  use the energy of the hot combustion gases  68  to drive a plurality of turbine blades  76  in each of the turbine stages  70 , thereby driving rotation of the turbine shaft  78 . In turn, the turbine shaft  78  drives rotation of a common shaft  94  between the turbine section  30  and the compression section  26 , thereby driving the shaft  52  of the compressor section  26 . The rotation of the turbine shaft  78  also drives rotation of a shaft  96  coupled to the load  32 , which may be an electrical generator to generate electricity for a local facility or the power grid. In operation, the controller  34  is configured to control a fuel flow from the fuel supply system  64 , a bleed flow through the bleed system  14 , and other aspects of the gas turbine system  10 . 
     The bleed system  14  is configured to route a compressed air stream from the high pressure region  16 , which may include the compressor section  26 , to the low pressure region  18 , which may include the exhaust plenum  80  of the exhaust section  22 . However, the bleed system  14  may be used between other high and low pressure regions of the gas turbine system  10 . In the illustrated embodiment, the bleed system  14  includes a first bleed conduit section  100  fluidly coupled to the compressor section  26  via the connections  54 , and a second bleed conduit section  102  movably (e.g., rotatably) coupled to the first bleed conduit section  100  and movably coupled to the exhaust section  22 . The first and second bleed conduit sections  100  and  102  may include a plurality of flexible and/or movable structures, which are configured to provide freedom of movement in one or more directions (e.g., rotational direction, horizontal direction, and/or vertical direction). The flexible and/or movable structures may include, for example, one or more gimbals  104 , one or more spring hangers  106 , one or more flexible conduits or hoses, and one or more rotatable joints  108 . The flexible and/or movable structures (e.g.,  104 ,  106 , and  108 ) may be configured to enable freedom of movement to accommodate thermal expansion and contraction in the bleed system  14  and between components of the gas turbine system  10 , and to provide flexibility when reconfiguring the bleed system  14  between a plurality of configurations (e.g., different orientations of the second bleed conduit section  102  according to the exhaust section  26  configuration, such as configurations  84 ,  88 , and  90  of the exhaust outlet  82 ). Additionally, the first and second bleed conduit sections  100  and  102  may include one or more mounting brackets  110 , a staged expansion conduit  112 , an outlet section  114 , one or more straight conduits  116  between the various components, and one or more bending conduits or elbows  118  between the various components. 
     As discussed in further detail below, the first bleed conduit section  100  may have a U-shaped conduit configuration  120  configured to partially extend around opposite sides of the compressor section  26  before fluidly connecting with the internal fluid flow through the compressor section  26  via the connections  54 . The U-shaped conduit configuration  120  of the first bleed conduit section  100  includes a central straight section or straight conduit  124  generally centered and oriented crosswise relative to the central axis  20 , gimbals  126  and  128  coupled to opposite ends of the straight conduit  124 , bending conduits or elbows  130  and  132  coupled to the respective gimbals  126  and  128 , gimbals  134  and  136  coupled to the respective bending conduits or elbows  130  and  132 , and the connections  54  between the gimbals  134  and  136  and the compressor casing  46  of the compressor section  26 . In the illustrated embodiment, the U-shaped conduit configuration  120  may remain in a fixed orientation once mounted to the compressor casing  46 , while the J-shaped conduit configuration  122  of the second bleed conduit section  102  may be reoriented or rotated about the central axis  20  to accommodate the different configurations  84 ,  88 , and  90  of the exhaust outlet  82 . 
     Additionally, the second bleed conduit section  102  may include a J-shaped conduit configuration  122 , which extends from the first bleed conduit section  100  and turns toward and connects with the exhaust plenum  80  of the exhaust section  22  at the staged expansion conduit  112  and the outlet section  114 . The J-shaped conduit configuration  122  of the second bleed conduit section  102  includes a straight conduit  138  coupled to the central straight conduit  124  in a generally crosswise orientation along the central axis  20  and a rotational joint  140  coupled to the straight conduit  138 . The J-shaped conduit configuration  122  also includes a bending conduit or elbow  142  coupled to the rotational joint  140 , a gimbal  144  coupled to the bending conduit or elbow  142  via an intermediate straight conduit  146 , and a straight conduit  148  coupled to the gimbal  144  opposite the intermediate straight conduit  146 . The J-shaped conduit configuration  122  also includes a bending conduit or elbow  150  coupled to the straight conduit  148 , one or more spring hangers  152  coupled to one or both of the conduits  148  and  150 , and a gimbal  154  coupled to the bending conduit or elbow  150 . The J-shaped conduit configuration  122  also includes a straight conduit  156  coupled to (and extending between) the gimbal  154  and a gimbal  158  and a plurality of spring hangers  160  coupled to the straight conduit  156  via an intermediate bracket  162 . The J-shaped conduit configuration  122  also includes a rotatable joint  164  removably coupled between a straight conduit  166  coupled to the gimbal  158  and a straight conduit  168  coupled to a valve assembly  170 . The J-shaped conduit configuration  122  also includes a rotatable joint  172  removably coupled between a straight conduit  174  coupled to the valve assembly  170  and a straight conduit  176  coupled to a gimbal  178 . The J-shaped conduit configuration  122  also includes a straight conduit  180  coupled to the gimbal  178  opposite the straight conduit  176 , and the staged expansion conduit  112  is coupled to the straight conduit  180  and extends to the outlet section  114  in the exhaust section  22 . 
     The valve assembly  170  may include one or more valves  182  driven by an actuator  184 , which is communicatively coupled to and controlled by the controller  34 . For example, the valve  182  may include a gate valve, a ball valve, a flapper valve, or any combination thereof. The actuator  184  may include an electric drive or motor, a solenoid, a pneumatic drive, a hydraulic drive, or any combination thereof. Accordingly, the controller  34  may control the actuator  184  to open and close the valve  182 , thereby controlling a bleed flow through the bleed system  14 , including the bleed flow through both the first and second conduit sections  100  and  102  between the high pressure region  16  in the compressor section  26  and the low pressure region  18  in the exhaust section  22 . The valve assembly  170  also may include a protective shield, a tray to collect fluid spills or leaks, and/or a wall structure  186  at least partially or entirely extending around the valve  182  and/or the actuator  184 . 
     The shield  186  of the valve assembly  170  also may be coupled to an enclosure  188  of the gas turbine engine  12  via a mounting bracket  190 . In certain embodiments, the mounting bracket  190  may extend between and couple with the enclosure  188  and the valve assembly  170 , the straight conduit  168 , the straight conduit  174 , and/or some other portion of the second bleed conduit section  102 . The enclosure  188  may substantially or completely surround the compressor section  26 , the combustion section  28 , and the turbine section  30  of the gas turbine engine  12 , and the mounting bracket  190  may rigidly support the valve assembly  170  and the second bleed conduit section  102  relative to a sidewall  192  of the enclosure  188 . The mounting bracket  190  may include a plurality of bracket sections  194  coupled together with intermediate flanges  196 . For example, the flanges  196  may be bolted together with a plurality of threaded fasteners, such as threaded bolts and nuts. 
     As discussed in detail below, the mounting bracket  190  may be removed, reoriented, and reinstalled when moving the J-shaped conduit configuration  122  of the second bleed conduit section  102  between different configurations for the different configurations  84 ,  88 , and  90  of the exhaust outlet  82 . In  FIG.  1   , the bleed system  14  is illustrated in an alternative configuration  198  as indicated by dashed lines. The alternative configuration  198  corresponds to the left-hand configuration  90  of the exhaust outlet  82  of the exhaust section  22 . In particular, as discussed in detail below, the J-shaped conduit configuration  122  of the second bleed conduit section  102  is configured to rotate from the illustrated bleed conduit orientation or configuration  200  shown in solid lines to the alternative bleed conduit orientation or configuration  198  shown in dashed lines via rotation about the rotatable joint  140  disposed along the central axis  20 , thereby enabling the J-shaped conduit configuration  122  to provide a similar or substantially identical configuration for either the right-hand configuration  84  of the exhaust outlet  82  and the left-hand configuration  90  of the exhaust outlet  82 . In certain embodiments, one of the illustrated configurations  198  and  200  may be used for multiple configurations of the exhaust outlet  82 , such as both the right-hand configuration  84  and the top configuration  88 . The different configurations of the J-shaped conduit configuration  122  are discussed in greater detail below with reference to  FIG.  2   . 
     As further illustrated in  FIG.  1   , the staged expansion conduit  112  includes a plurality of alternating constant-diameter conduits  202  and expanding-diameter conduits  204 , thereby defining a plurality of stages of expansion and depressurization. In particular, the illustrated staged expansion conduit  112  includes, in series, an expanding conduit  206 , a constant conduit  208 , an expanding conduit  210 , a constant conduit  212 , and an expanding conduit  214 . The conduits  206 ,  208 ,  210 ,  212 , and  214  progressively increase in diameter and cross-sectional area, wherein each constant conduit  208  and  212  has a constant diameter and cross-sectional area, and each expanding conduit  206 ,  210 , and  214  has a gradually increasing diameter and cross-sectional area in a direction of bleed flow. The expanding conduit  214  is coupled to an end wall  216  of the exhaust section  122  between the enclosure  188  and the exhaust plenum  80 . The expanding conduit  214  also leads into the outlet section  114 , which is disposed inside of the exhaust plenum  80 . At a connection between the staged expansion conduit  112  and the end wall  216 , the bleed system  14  may enable freedom of movement in one or more directions, such axial, radial, and/or rotational directions of movement relative to the end wall  216 . The outlet section  114  includes a plurality of outlets  218  disposed in an annular housing  220 , wherein the outlets  218  are configured to distribute or diffuse the bleed flow from the bleed system  14  into the exhaust plenum  80 . For example, the outlets  218  may be disposed along a sidewall  222  (e.g., annular sidewall) and an end wall  224  (e.g., axially facing end wall) of the annular housing  220 . In certain embodiments, the connection between the end wall  216  and the staged expansion conduit  112  and/or the outlet section  114  may include a moveable joint configured to enable axial movement and/or rotation therebetween. 
     The staged expansion conduit  112  is configured to gradually depressurize the bleed flow to reduce the vibration and/or noise of the bleed system  14 , such as vibration of a bleed valve. The staged expansion conduit  112  may have at least two stages configured to gradually (e.g., incrementally) depressurize the bleed flow. Each stage of the staged expansion conduit  112  may have an expansion section and/or a diffuser plate. The number of stages may be determined at least in part on the difference in pressure between the high pressure region  16  and the low pressure region  18 . More stages may be used for large pressure differences than for small pressure differences. The expansion sections increase the dimension of the staged expansion conduit  112  to at least reduce the static pressure of the bleed flow. The diffuser plates partially obstruct the bleed flow and permit passage of the bleed flow through orifices. The diffuser plates are configured to at least reduce the kinetic energy or dynamic pressure of the bleed flow. The characteristics of the expansion sections (e.g., expansion percentage, size, cross-sectional shape, length) and diffuser plates (e.g., orifice size, orifice quantity, orifice shape, orifice configuration, diffuser plate size) affect the vibration of the bleed system  14 . 
     Vibration and thermal expansion/contraction of the bleed system  14  may cause the bleed system  14  to move. Certain mounting and coupling features may be utilized to accommodate the movements of the bleed system  14 . For example, the various components of the bleed system  14  may be configured to allow for movement in one or more directions, such as an axial direction along an axis of the conduit, rotationally about the axis of the conduit, in a horizontal direction, a vertical direction, or any combination thereof. Each gimbal  104  may be configured to allow for axial movement, rotational movement, or any combination thereof, relative to an axis of the adjacent conduits. The rotatable joints  108  are configured to enable rotation about an axis of the adjacent conduits. The rotatable joints  108  also may be configured to enable separation and reattachment of the adjacent conduits. The spring hangers  106  are configured to enable movement along an axis of the spring portion of the spring hangers, which may be oriented in a vertical direction, a horizontal direction, or any other suitable angular direction between horizontal and vertical within the enclosure  188  of the gas turbine engine  12 . For example, each of the spring hangers  106  may be hung from a top wall or ceiling of the enclosure  188 , thereby allowing some vertical movement of the various conduits and sections of the bleed system  14 . Additionally, as discussed above, the gimbals  104 , the rotatable joints  108 , and the spring hangers  106  (e.g., flexible and/or movable structures) are configured to help enable reconfiguration of the bleed system  14  between different configurations, such as different orientations of the second bleed conduit section  102  to accommodate the different exhaust outlet orientations (e.g., 86, 88, and 90). 
     In the illustrated embodiment, when reconfiguring the bleed system  14  between the configurations  198  and  200  of the J-shaped conduit configuration  122  of the second bleed conduit section  102 , the rotatable joint  140  may be loosened to enable rotation of the second bleed conduit section  102  about the central axis  20 , such that the second bleed conduit section  102  moves from the configuration  200  to the configuration  198  (or vice versa). Additionally, the rotatable joints  164  and  172  may be loosened and disconnected to allow reorientation of the valve assembly  170  and the mounting bracket  190 , thereby enabling the valve assembly  170  and the mounting bracket  190  to be oriented in a proper configuration to mount against the sidewall  192  of the enclosure  188  on the opposite side of the enclosure  188 , as illustrated by the alternative configuration  198 . In the illustrated embodiment, the rotatable joint  140  is aligned with the central axis  20  (e.g., in a common vertical plane with the central axis  20 ), thereby enabling the J-shaped conduit configuration  122  of the second bleed conduit section  102  to rotate between a plurality of symmetrical configurations, such as the configurations  198  and  200 . 
       FIG.  2    is a schematic view of an embodiment of the gas turbine engine  12  and the bleed system  14  taken in a plane perpendicular to the central axis  20  of  FIG.  1   , further illustrating details of the different configurations of the bleed system  14 . In the illustrated embodiment, the first bleed conduit section  100  has the gimbals  126 ,  128 ,  134 , and  136 , and the conduits  124 ,  130 ,  132  arranged in the U-shaped conduit configuration  120 , which partially wraps around opposite sides of the compressor casing  46  of the compressor  26 . The U-shaped conduit configuration  120  may be symmetric relative to the rotatable joint  140  and/or the plane perpendicular to the central axis  20  (e.g., the plane through the central axis  20  and the rotatable joint  140 ). The connections  54  include conduits  230  fluidly and mechanically coupled to the compressor casing  46  via mounting flanges  232 . The mounting flanges  232  may be coupled to the compressor casing  46  via one or more fasteners, such as threaded fasteners (e.g., bolts), welded joints, brazed joints, clamps, dovetail joints, or other removable or fixed joints. 
     The first bleed conduit section  100  is configured to receive a bleed flow  234  (e.g., a compressed air flow) from the high pressure region  16  inside the compressor section  26  and to route the bleed flow through the various conduits  230 ,  130 ,  132 , and  124  into the second bleed conduit section  102 , which connects with the first bleed conduit section  100  via the rotatable joint  140 . Again, each of the gimbals  104 , including gimbals  126 ,  128 ,  134 , and  136 , is configured to enable movement (e.g., expansion and contraction) in an axial direction relative to the adjacent conduits, rotation about the axis of the adjacent conduits, or any combination thereof. 
     When reconfiguring the bleed system  14  between different configurations, the second bleed conduit section  102  is configured to rotate about the rotatable joint  140  as indicated by the bleed conduit orientations or configurations  198 ,  200 ,  236 ,  238 , and  240 . The configurations  198  and  200  correspond to the configurations shown and described above with reference to  FIG.  1   . The configuration  236  is oriented midway between the configurations  198  and  200 , such that the second bleed conduit section  102  is substantially perpendicular relative to the second bleed conduit sections  102  in the configurations  198  and  200 . The configurations  238  and  240  are approximately midway between the configurations  200  and  236  and the configurations  198  and  236 , respectively. However, the second bleed conduit section  102  may be rotated about the rotational joint  140  to any angular orientation as indicated by arrows  242 . In  FIG.  2   , the various components of the second bleed conduit section  102  are removed for simplicity; however, the second bleed conduit section  102  may include each of the components discussed above with reference to  FIG.  1   . For example, the flexible and/or movable structures (e.g., gimbals  104 , spring hangers  106 , and rotatable joints  108 ) are configured to provide flexibility in the first and second bleed conduit sections  100  and  102  when reconfiguring (e.g., rotating) the second bleed conduit section  102  as illustrated in  FIG.  2   . 
       FIG.  3    is a schematic cross-sectional side view of one of the rotatable joints  108 , such as the rotatable joints  140 ,  164 , and  172 , of the second bleed conduit section  102  of  FIG.  1   . The rotatable joint  108  may include an annular clamp  250  disposed about a male joint portion  252  inserted within a female joint portion  254 . The male joint portion  252  is disposed at an end portion  256  of a conduit  258 , while the female joint portion  254  is disposed on an end portion  260  of a conduit  262 . The male joint portion  252  may include an annular outer lip  264  protruding radially outwardly from the conduit  258 , and an axially extending annular portion  266  projecting at the end portion  256 . The female joint portion  254  may include an annular outer lip  268  protruding radially outwardly from the conduit  262  and an axially recessed annular portion or cavity  270  disposed inwardly into the end portion  260 . The male joint portion  252  has the axially extending annular portion  266  inserted into the axially recessed annular portion  270 , while the annular clamp  250  extends circumferentially around both of the annular outer lips  264  and  268 . 
     The annular clamp  250  is configured to compressively secure the annular outer lips  264  and  268  and to hold together the connection between the axially extending annular portion  266  and the axially recessed annular portion  270 . When the annular clamp  250  is tightened about the annular outer lips  264  and  268 , the rotatable joint  108  may be held in a fixed rotational position between the conduits  258  and  262 , such that the conduits  258  and  262  cannot rotate relative to one another. However, the annular clamp  250  may be loosened and/or removed to enable movement (e.g., rotation) between and/or separation of the conduits  258  and  262 . For example, by loosening the annular clamp  258 , the conduits  258  and  262  may be rotated relative to one another as indicated by arrows  272  about a central axis  274  of the rotatable joint  108 . As discussed above and in further detail below, the rotatable joint  108  is configured to enable rotation between the different configurations  198 ,  200 ,  236 ,  238 , and  240  of the second bleed conduit section  102  relative to the first bleed conduit section  100 , and also to enable reconfiguration of the valve assembly  170  and the mounting bracket  190 . 
       FIG.  4    is a cross-sectional side view of the rotatable joint  108  as illustrated in  FIG.  3   , further illustrating details of the annular clamp  250  disposed about the male joint portion  252  and the female joint portion  254  of the conduits  258  and  262 . As illustrated, the annular clamp  250  includes a plurality of clamp sections, such as semi-annular clamp sections  280  and  282  (e.g., C-shaped clamp sections). The semi-annular clamp sections  280  and  282  are disposed about the male and female joint portions  252  and  254 , and the semi-annular clamp sections  280  and  282  are coupled together via fasteners  284  disposed in adjacent flanges  286  and  288  of the respective semi-annular clamp sections  280  and  282 . The fasteners  284  may include threaded bolts  290  extending through bolt holes  292  and  294  in the respective flanges  286  and  288 , through which the threaded bolts  290  connect with threaded nuts  296  to compressively secure the flanges  286  and  288  together. In the illustrated embodiment, the annular clamp  250  includes the two semi-annular clamp sections  280 , and two sets of mating flanges  286  and  288 . In some embodiments, the annular clamp  250  may include a split-ring clamp having a single set of flanges  286  and  288  at a single break in the annular clamp  250 , or the annular clamp  250  may include a greater number (e.g., 3, 4, 5, or more) of clamp sections and associated flanges  286  and  288 . 
     The fasteners  284  are configured to compressively couple together the semi-annular clamp sections  280  and  282  about the male and female joint portions  252  and  254 , thereby limiting rotational movement between the conduits  258  and  262 . However, the fasteners  284  may be loosened to enable movement (e.g., rotation movement) between the male and female joint portions  252  and  254  and thus rotational movement between the conduits  258  and  262 . When reconfiguring the second bleed conduit section  102  between the different configurations  198 ,  200 ,  236 ,  238 , and  240 , the fasteners  284  may be loosened sufficiently to enable easier rotation of the second bleed conduit section  102  about the rotational joint  140 . Likewise, the rotational joints  164  and  172  may be loosened via loosening of the fasteners  284 , thereby enabling reorientation of the valve assembly  170  and the mounting bracket  190  between the different configurations of the second bleed conduit section  102 . 
       FIG.  5    is a schematic view of an embodiment of the valve assembly  170 , the mounting bracket  190 , and the rotational joints  164  and  172  disposed between the straight conduits  166  and  168  and the straight conduits  174  and  176 . The valve assembly  170  may be moved between a plurality of orientations via disconnection and/or rotational movement at the rotatable joints  164  and  172  when reconfiguring the second bleed conduit section  102  relative to the first bleed conduit section  100 . In the illustrated embodiment, the reorientation of the valve assembly  170  is performed by loosening and/or disconnecting each of the rotatable joints  164  and  172 , which may have the features of the rotatable joint  108  as discussed above with reference to  FIGS.  3  and  4   . For example, the valve assembly  170  may be rotated about an axis of the straight conduits  166 ,  168 ,  174 , and  176 , such as rotation between 0 and 360 degrees about the axis. 
     The valve assembly  170  also may be reoriented along with the mounting bracket  190 . The mounting bracket  190  includes a mounting bracket or arm  300  coupled to the shield  186  of the valve assembly  170 , wherein the mounted bracket or arm  300  includes a flange  302  having fastener receptacles  304 . The mounting bracket  190  also includes a mounting bracket or arm  306  having flanges  308  and  310  on opposite ends of the arm  306 . The flange  308  includes fastener receptacles  312 , while the flange  310  includes fastener receptacles  314 . The flanges  302  and  308  of the arms  300  and  306  are configured to removably couple together via threaded fasteners  316  (e.g., threaded bolts) extending through the fastener receptacles  304  and  312  and connecting with mating threaded fasteners  318  (e.g., threaded nuts). Similarly, the flange  310  is configured to mount to the side wall  192  of the enclosure  188  of the gas turbine engine  12  as illustrated in  FIG.  1    by extending threaded fasteners  320  (e.g., threaded bolts) through the fastener receptacles  314  into the sidewall  192 . 
     The illustrated fasteners  316 ,  318 , and  320  are removable threaded fasteners, which may include any number of threaded bolts and nuts. In certain embodiments, the fasteners  316 ,  318 , and  320  may include other types of threaded fasteners and/or removable fasteners, such as fastening clamps, spring-loaded fasteners, dovetail joints, hinged joints, or any combination thereof. Accordingly, the removability of the fasteners  316 ,  318 , and  320  is configured to enable reconfiguration of the mounting bracket  190  when changing the valve assembly  170  and the entire second bleed conduit section  102  between the different configurations, such as configurations  198 ,  200 ,  236 ,  238 , and  240 . As further illustrated in  FIG.  5   , the controller  34  is configured to operate the actuator  184  to open and close the valve  182  in the valve assembly  170 . The valve  182  may include a valve element  320  (e.g., ball, gate, flapper, etc.) coupled to the actuator  184  via a valve stem  322 . For example, the actuator  184  may rotate and/or axially move the valve stem  322  to move the valve element  320  between open and closed positions between the straight conduits  168  and  174 . 
       FIG.  6    is a partial perspective view of the gas turbine system  10  and the bleed system  14  of  FIGS.  1 - 5   , further illustrating details of the bleed system  14  coupled to the exhaust section  22  in the configuration  200  of the second bleed conduit section  102  and the right-hand configuration  84  of the exhaust outlet  82 . In certain embodiments, the configuration  200  of the second bleed conduit section  102  as illustrated in  FIG.  6    also may be used for the top configuration  88  of the exhaust outlet  82  as illustrated in  FIG.  1   . However, any number of alternative configurations of the bleed system  14  may be achieved to accommodate different orientations of the exhaust outlet  82 . 
     As illustrated in  FIG.  6   , the first bleed conduit section  100  has the U-shaped conduit configuration  120  disposed in a fixed configuration relative to the central axis  20 , while the J-shaped conduit configuration  122  of the second bleed conduit section  102  is disposed in the configuration  200  via rotation relative to the rotatable joint  140 . The gimbals  104 , the spring hangers  106 , the rotatable joints  108 , the staged expansion conduit  112 , the straight conduits  116 , and the bending conduits or elbows  118  of the second bleed conduit section  102  and the first bleed conduit section  100  are substantially the same as described in detail above. However, in the illustrated configuration, the rotatable joint  172  is disposed between the gimbal  178  and the staged expansion conduit  112  rearward of the gimbal  178 , and the rotatable joint  164  is disposed partially within the shield  186  of the valve assembly  170 . Furthermore, the illustrated mounting bracket  190  has the mounting bracket or arm  300  coupled to the straight conduit  174  rather than the shield  186 . 
     When changing the configuration of the bleed system  14  and the exhaust outlet  82 , the second bleed conduit section  102  is rotated about the rotatable joint  140 , which is disposed along the central axis  20 . One or both of the rotatable joints  164  and  172  may be loosened and/or disconnected to allow reorientation of the valve assembly  170  and the mounting bracket  190 . Additionally, the mounting brackets or arms  300  and  306  may be disconnected at the flanges  302 ,  308 , and  310 , and then reconfigured for the alternative configuration  198  as illustrated in  FIG.  1    and further illustrated in  FIG.  7   . 
       FIG.  7    is a partial perspective view of the gas turbine system  10  and the bleed system  14  of  FIGS.  1 - 6   , further illustrating details of the bleed system  14  coupled to the exhaust section  22  in the configuration  198  of the second bleed conduit section  102  and the left-hand configuration  90  of the exhaust outlet  82 . Again, the bleed system  14  has substantially the same components as  FIGS.  1 - 6   , including the gimbals  104 , the spring hangers  106 , the rotatable joints  108 , the mounting bracket  190 , the staged expansion conduit  112 , the straight conduits  116 , and the bending conduits or elbows  118 . However, in the illustrated embodiment of  FIG.  7   , the bleed system  14  has the same modifications as discussed above with reference to  FIG.  6   . 
     As illustrated in  FIG.  7   , the second bleed conduit section  102  has been rotated approximately 180 degrees about the central axis  20  via the rotatable joint  140  as compared with the configuration  200  of  FIG.  6   . In the illustrated configuration  198 , the second bleed conduit section  102  extends toward the exhaust section  22  with the exhaust outlet  82  in the left-hand configuration  90 . Again, the rotatable joints  164  and/or  172  may be loosened or disconnected to facilitate the reorientation of the valve assembly  170  and the mounting bracket  190 . Additionally, the mounting bracket  190  may be reconfigured by disconnecting the mounting brackets or arms  300  and  306  at the flanges  302 ,  308 , and  310 . As illustrated in  FIG.  7   , the mounting bracket  190  is directly coupled to the straight conduit  168  rather than the shield  186  of the valve assembly  170 . In particular, the mounting bracket or arm  300  is directly coupled to the straight conduit  168 . After the second bleed conduit section  102  has been rotated from the configuration  200  of  FIG.  6    to the configuration  198  of  FIG.  7   , the rotatable joint  140  may be retightened and secured in its rotational position, and the rotational rotatable joints  164  and  172  may be reconnected and retightened to secure the rotational position between the straight conduits  166 ,  168 ,  174  and  176 . Although  FIGS.  6  and  7    illustrate only the configurations  198  and  200  of the second bleed conduit section  102  relative to the first bleed conduit section  100 , the bleed system  14  may be reconfigured into a plurality of positions as discussed above with reference to  FIG.  2   . 
     Technical effects of the disclosed embodiments include a reconfigurable bleed system, which can be used with a plurality of different orientations of an exhaust section (e.g., left, right, and top exhaust outlet orientations). In particular, the bleed system is reconfigurable via a rotatable joint along a central axis, such that the bleed system can rotate between a plurality of different orientations taking advantage of the symmetry about the rotatable joint. The bleed system also includes various flexible and/or movable structures, such as gimbals, spring hangers, and rotatable joints, configured to provide freedom of movement of the bleed system. 
     The subject matter described in detail above may be defined by one or more clauses, as set forth below. 
     A system includes a bleed system configured to direct a bleed flow from a compressor section to an exhaust section of a gas turbine engine. The bleed system includes a first bleed conduit section configured to couple to the compressor section, a second bleed conduit section configured to couple to the exhaust section, and a first rotatable joint coupling together adjacent conduits of the first and second bleed conduit sections. The second bleed conduit section comprises a set of components configured to rotate between a plurality of orientations relative to the first bleed conduit section and the compressor section via the first rotatable joint. The plurality of orientations correspond to a plurality of exhaust outlet orientations of the exhaust section. 
     The system of the preceding clause, wherein the first rotatable joint extends along a central axis of the gas turbine engine, and the plurality of orientations includes different angular orientations about the central axis. 
     The system of any preceding clause, including the gas turbine engine having the compressor section, the exhaust section, a turbine section, and a combustor section. 
     The system of any preceding clause, wherein each of the plurality of exhaust outlet orientations is oriented crosswise to a central axis of the gas turbine engine. 
     The system of any preceding clause, wherein the plurality of exhaust outlet orientations includes at least one of a left-hand exhaust orientation, a right-hand exhaust orientation, or a top exhaust orientation. 
     The system of any preceding clause, wherein the set of components in the second bleed conduit section is common for each orientation of the plurality of orientations. 
     The system of any preceding clause, wherein the first bleed conduit section includes a U-shaped conduit configuration. 
     The system of any preceding clause, wherein the U-shaped conduit configuration includes a central straight conduit extending between first and second bending conduits, and the central straight conduit is coupled to the first rotatable joint. 
     The system of any preceding clause, wherein the first bleed conduit section includes a plurality of gimbals disposed along one or more of the central straight conduit, the first bending conduit, or the second bending conduit. 
     The system of any preceding clause, wherein the second bleed conduit section includes a J-shaped conduit configuration. 
     The system of any preceding clause, wherein the second bleed conduit section includes one or more gimbals and one or more spring hangers. 
     The system of any preceding clause, wherein the second bleed conduit section includes a staged expansion conduit having a plurality of expanding conduits arranged in stages along a direction of a bleed flow through the bleed system. 
     The system of any preceding clause, wherein the second bleed conduit section includes a mounting bracket configured to mount the second bleed conduit section to a wall of an enclosure of the gas turbine engine. 
     The system of any preceding clause, wherein the second bleed conduit section includes a second rotatable joint and a third rotatable joint disposed along a conduit of the second bleed conduit section upstream and downstream of the mounting bracket, respectively. 
     The system of any preceding clause, wherein the conduit includes a valve configured to adjust a bleed flow through the bleed system, wherein the valve is disposed between the second and third rotatable joints. 
     The system of any preceding clause, wherein the mounting bracket includes first and second mounting arms removably coupled together at mating flanges, the first mounting arm is coupled to the second bleed conduit section, and the second mounting arm is configured to couple to the wall of the enclosure of the gas turbine engine. 
     A method includes coupling together, via a first rotatable joint, adjacent conduits of first and second bleed conduit sections of a bleed system configured to direct a bleed flow from a compressor section to an exhaust section of a gas turbine engine, wherein the first bleed conduit section is configured to couple to the compressor section, and the second bleed conduit section comprises a set of components configured to couple to the exhaust section. The method further includes rotating, via the first rotatable joint, the second bleed conduit section between a plurality of orientations relative to the first bleed conduit section and the compressor section, wherein the plurality of orientations corresponds to a plurality of exhaust outlet orientations of the exhaust section, and wherein the set of components in the second bleed conduit section is the same for each orientation of the plurality of orientations. 
     The method of the preceding clause, wherein the first rotatable joint extends along a central axis of the gas turbine engine, and the plurality of orientations includes different angular orientations about the central axis. 
     A system includes a compressor section of a gas turbine engine, an exhaust section of the gas turbine engine, and a bleed system configured to direct a bleed flow from the compressor section to the exhaust section. The bleed system includes a first bleed conduit section coupled to the compressor section, a second bleed conduit section coupled to the exhaust section, and a first rotatable joint coupling together adjacent conduits of the first and second bleed conduit sections. The second bleed conduit section is configured to rotate between a plurality of orientations relative to the first bleed conduit section and the compressor section via the first rotatable joint, wherein the plurality of orientations corresponds to a plurality of exhaust outlet orientations of the exhaust section, and wherein the set of components in the second bleed conduit section is the same for each orientation of the plurality of orientations. 
     The system of the preceding clause, wherein the first rotatable joint extends along a central axis of the gas turbine engine, and the plurality of orientations includes different angular orientations about the central axis. 
     This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.