Patent Publication Number: US-2023137513-A1

Title: Joint assembly and method of manufacturing thereof

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application claims priority pursuant to 35 U.S.C. 119(a) to United Kingdom patent application number GB 2115760.7 filed on Nov. 3, 2021, the entire contents of which is incorporated herein by reference. 
     BACKGROUND 
     Field of the Disclosure 
     The present disclosure generally relates to a joint assembly and a method of manufacturing the joint assembly. 
     Description of the Related Art 
     Gas turbine engines generally include duct assemblies that provide conduits for flow of various operating fluids to and from the gas turbine engine. For example, high-pressure air from the gas turbine engine may be routed through an aircraft to serve multiple purposes, including starting additional engines, pressurizing a cabin, de-icing of wings, nacelles, and empennage, and supporting air conditioning units of the aircraft, along with various other systems. 
     Duct assemblies that carry the high-pressure air must therefore be capable of withstanding high pressures, high temperatures, as well as stresses of vibration, impact, acceleration, deceleration, aircraft component deflection and momentum. Thus, the duct assemblies typically include flexible joints (e.g., gimbals) that allow for angular movements between the connected ducts/pipes. 
     Gimbals are generally manufactured using traditional extrusion and forming processes which require welds to connect various pins, bellows and flanges. Current welding methods fail to adequately resist stresses that the gimbal is subjected to. Repair or replacement of a failed gimbal may require skilled personnel and partial dismantling of the engine at a suitable location. In addition, a manufacturing and installation cost of conventional gimbals may be typically high. 
     SUMMARY OF THE DISCLOSURE 
     According to a first aspect there is provided a joint assembly for joining a first component to a second component. The joint assembly includes a first liner configured to be coupled to the first component. The joint assembly further includes a second liner configured to be coupled to the second component. The joint assembly further includes a bellows fixedly coupled to each of the first liner and the second liner. The joint assembly further includes a first clevis fixedly coupled to the first liner and at least partially enclosing the first liner and the bellows. The first clevis includes a plurality of first extensions and a plurality of first clevis apertures corresponding to the plurality of first extensions. Each first extension defines a corresponding first clevis aperture from the plurality of first clevis apertures therethrough. The joint assembly further includes a second clevis fixedly coupled to the second liner and at least partially enclosing the second liner and the bellows. The second clevis includes a plurality of second extensions angularly spaced apart from each of the plurality of first extensions of the first clevis and a plurality of second clevis apertures corresponding to the plurality of second extensions. Each second extension defines a corresponding second clevis aperture from the plurality of second clevis apertures therethrough. The joint assembly further includes a ring at least partially surrounding the first clevis and the second clevis and including a plurality of ring apertures extending therethrough. The plurality of ring apertures includes a set of first ring apertures corresponding to the plurality of first clevis apertures and a set of second ring apertures corresponding to the plurality of second clevis apertures. Each first ring aperture is aligned with a corresponding first clevis aperture from the plurality of first clevis apertures of the first clevis. Each second ring aperture is aligned with a corresponding second clevis aperture from the plurality of second clevis apertures of the second clevis. The joint assembly further includes a plurality of pins corresponding to the plurality of ring apertures of the ring and configured to rotatably couple the ring to each of the first clevis and the second clevis. Each pin includes a head portion received at least partially in a corresponding ring aperture from the plurality of ring apertures. The head portion is coupled to the ring by a corresponding weld. Each pin further includes a shaft portion extending from the head portion and received at least partially within the corresponding ring aperture. The joint assembly further includes a plurality of first bearing inserts fixedly coupled to the first clevis. Each first bearing insert is at least partially received within a corresponding first clevis aperture from the plurality of first clevis apertures. The joint assembly further includes a plurality of second bearing inserts fixedly coupled to the second clevis. Each second bearing insert is at least partially received within a corresponding second clevis aperture from the plurality of second clevis apertures. The shaft portion of each pin is coupled to the ring by a corresponding interference fit. The shaft portion of each pin is further at least partially received in the corresponding first bearing insert or the corresponding second bearing insert that is received in the corresponding first clevis aperture or the corresponding second clevis aperture aligned with the corresponding ring aperture. The shaft portion of each pin is coupled to the corresponding first bearing insert or the corresponding second bearing insert by a corresponding clearance fit, such that the shaft portion is rotatable relative to the corresponding first bearing insert or the corresponding second bearing insert. 
     The joint assembly includes the ring including the plurality of ring apertures extending therethrough and the plurality of pins configured to rotatably couple the ring to each of the first clevis and the second clevis. The shaft portion of each pin is coupled to the ring by the corresponding interference fit. The interference fit may allow an increase in load transfer between the ring and the first clevis or the second clevis while also improving an efficiency of the load transfer. Further, the head portion of each pin is coupled to the ring by the corresponding weld. Thus, the interference fit is located away from the corresponding weld. This displaces a heat affected zone of the weld with weakened material properties away from a load path between the ring and the first clevis or the second clevis that results in a more robust design of the joint assembly. Additionally, the interference fit may reduce a bending moment on the pin that allows for a smaller, lighter pin or a higher load capacity of the joint assembly. 
     The joint assembly includes the plurality of first bearing inserts and the plurality of second bearing inserts fixedly coupled to the first clevis and the second clevis, respectively. The bearing inserts may allow suitable materials to be selected separately for the bearing insert and for the first or second clevises. For example, suitable bearing materials may be selected based on a desired stiffness of the joint assembly, mechanical strength and wear resistance of the bearing materials, and friction between the pin and the first clevis or the second clevis. Further, suitable clevis material may be selected based on ease of manufacturing and desirable strength. This may reduce an overall cost and weight of the joint assembly as well as improve a service life of the joint assembly. Additionally, the first and second bearing inserts may be replaced upon wear and the first or second clevises may be reused. 
     In some embodiments, the weld between the head portion and the ring includes an electron beam weld or a laser beam weld. The electron beam weld or the laser beam weld may allow a repeatable and desirable weld penetration to be achieved as compared to conventional joining techniques, such as arc welding. Electron beam welding and laser beam welding are generally low heat input processes as compared to arc welding. Thus, the amount of material that is heat affected (or the heat affected zone) during the welding process is substantially less as compared to arc welding. This may enable a lighter design of the joint assembly due to a larger amount of material retaining its original properties after the welding process. 
     In some embodiments, the head portion has a minimum head diameter and the shaft portion has a maximum shaft diameter less than the minimum head diameter of the head portion. Thus, the pin may have a substantially T-shaped cross-section. Such a design of the pin may shift a location of the heat affected zone of the weld away from the interference fit, and thus, the load path between the ring and the first clevis or the second clevis. This may enhance reliability of the joint assembly. 
     In some embodiments, each ring aperture includes a wide aperture portion configured to at least partially receive the head portion of the corresponding pin and a narrow aperture portion disposed adjacent to the wide aperture portion and configured to at least partially receive the shaft portion of the corresponding pin. 
     In some embodiments, the shaft portion includes a wide shaft section disposed adjacent to the head portion and having a minimum wide diameter. The wide shaft section is at least partially received in the corresponding ring aperture. In some embodiments, the shaft portion further includes a narrow shaft section disposed adjacent to the wide shaft section opposite to the head portion and having a maximum narrow diameter less than the minimum wide diameter of the wide shaft section. The narrow shaft section is at least partially received in the corresponding first bearing insert or the corresponding second bearing insert. In some embodiments, the shaft portion further includes a step disposed between the wide and narrow shaft sections. 
     The narrow shaft section of the shaft portion may align the corresponding ring aperture with the corresponding first bearing insert or the corresponding second bearing insert during manufacture of the joint assembly. This may enable a quick and lean assembly process that eliminates scrappage due to any misalignment between the ring, the pin, and the first clevis or the second clevis. 
     In some embodiments, the shaft portion includes a uniform shaft section disposed adjacent to the head portion and having a substantially uniform shaft diameter. The uniform shaft section is at least partially received in the corresponding ring aperture and in the corresponding first bearing insert or the corresponding second bearing insert. In some embodiments, the shaft portion further includes a tapered shaft section disposed adjacent to the uniform shaft section opposite to the head portion and tapering away from the uniform shaft section. The tapered shaft section has an average diameter less than the uniform shaft diameter of the uniform shaft section. The tapered shaft section at least partially extends out of the corresponding first clevis aperture or the corresponding second clevis aperture aligned with the corresponding ring aperture. 
     The tapered shaft section of the shaft portion may align the corresponding ring aperture with the corresponding first bearing insert or the corresponding second bearing insert during manufacture of the joint assembly. This may enable a quick and lean assembly process that eliminates scrappage due to any misalignment between the ring, the pin, and the first clevis or the second clevis. 
     In some embodiments, each pin further includes an aid guide removably attached to an end of the shaft portion distal to the head portion. The aid guide tapers away from the end of the shaft portion, such that the aid guide is configured to align the corresponding ring aperture with the corresponding first bearing insert or the corresponding second bearing insert as the shaft portion is at least partially received through the corresponding ring aperture and through the corresponding first bearing insert or the corresponding second bearing insert. 
     The aid guide may align the corresponding ring aperture with the corresponding first bearing insert or the corresponding second bearing insert during manufacture of the joint assembly. The aid guide may be removed after the assembly process. 
     In some embodiments, each of the pluralities of first and second bearing inserts has an annular shape. 
     In some embodiments, each of the first and second clevises is made of a clevis material. Each of the pluralities of first and second bearing inserts is made of a bearing material different from the clevis material. A hardness of the clevis material is different from a hardness of the bearing material. Thus, appropriate bearing material and clevis material may be chosen separately based on application requirements. This may reduce an overall cost and weight of the joint assembly as well as improve a service life of the joint assembly. 
     In some embodiments, each first bearing insert is fixedly coupled to the first clevis by a corresponding first insert weld or a corresponding first interference fit. 
     In some embodiments, each second bearing insert is fixedly coupled to the second clevis by a corresponding second insert weld or a corresponding second interference fit. 
     In some embodiments, the first clevis is fixedly coupled to the first liner by one or more first clevis welds. 
     In some embodiments, the second clevis is fixedly coupled to the second liner by one or more second clevis welds. 
     In some embodiments, the bellows is fixedly coupled to the first liner by one or more first bellows welds. 
     In some embodiments, the bellows is fixedly coupled to the second liner by one or more second bellows welds. 
     According to a second aspect, there is provided gas turbine engine including a first component, a second component and a joint assembly. The joint assembly joins the first component to the second component. 
     According to a third aspect, there is provided a method of manufacturing a joint assembly. The method includes providing a first clevis including a plurality of first extensions and a plurality of first clevis apertures corresponding to the plurality of first extensions. Each first extension defines a corresponding first clevis aperture from the plurality of first clevis apertures therethrough. The method further includes providing a second clevis including a plurality of second extensions angularly spaced apart from the plurality of first extensions of the first clevis and a plurality of second clevis apertures corresponding to the plurality of second extensions. Each second extension defines a corresponding second clevis aperture from the plurality of second clevis apertures therethrough. The method further includes at least partially surrounding the first clevis and the second clevis with a ring including a plurality of ring apertures extending therethrough, such that each of a set of first ring apertures from the plurality of ring apertures aligns with a corresponding first clevis aperture from the plurality of first clevis apertures of the first clevis and each of a set of second ring apertures from the plurality of ring apertures aligns with a corresponding second clevis aperture from the plurality of second clevis apertures of the second clevis. The method further includes fixedly coupling a plurality of first bearing inserts to the first clevis, such that each first bearing insert is at least partially received within a corresponding first clevis aperture from the plurality of first clevis apertures. The method further includes fixedly coupling a plurality of second bearing inserts to the second clevis, such that each second bearing insert is at least partially received within a corresponding second clevis aperture from the plurality of second clevis apertures. The method further includes inserting a plurality of pins through the plurality of ring apertures, such that a head portion of each pin is at least partially received in a corresponding ring aperture from the plurality of ring apertures and a shaft portion of each pin is at least partially received in the corresponding ring aperture. The shaft portion of each pin is fixedly coupled to the ring by a corresponding interference fit. The method further includes at least partially receiving the shaft portion of each pin in a corresponding first bearing insert or a corresponding second bearing insert that is received in the corresponding first clevis aperture or the corresponding second clevis aperture aligned with the corresponding ring aperture. The shaft portion of each pin is rotatably coupled to the corresponding first bearing insert or the corresponding second bearing insert by a corresponding clearance fit, such that each of the first and second clevises is rotatably coupled to the ring. The method further includes fixedly coupling the head portion of each pin to the ring by electron beam welding or laser beam welding. 
     In some embodiments, the method further includes fixedly coupling a bellows to a first liner by one or more first bellows welds. The first liner is configured to be coupled to a first component. In some embodiments, the method further includes fixedly coupling the bellows to a second liner by one or more second bellows welds. The second liner is configured to be coupled to a second component. In some embodiments, the method further includes fixedly coupling the first clevis to the first liner by one or more first clevis welds. In some embodiments, the method further includes fixedly coupling the second clevis to the second liner by one or more second clevis welds. 
     In some embodiments, each first bearing insert is fixedly coupled to the first clevis by a corresponding first insert weld or a corresponding first interference fit. In some embodiments, each second bearing insert is fixedly coupled to the second clevis by a corresponding second insert weld or a corresponding second interference fit. 
     In some embodiments, the method further includes removably attaching an aid guide to an end of the shaft portion of each pin distal to the head portion. The aid guide tapers away from the end of the shaft portion, such that the aid guide is configured to align the corresponding ring aperture with the corresponding first bearing insert or the corresponding second bearing insert as the shaft portion is at least partially received through the corresponding ring aperture and through the corresponding first bearing insert or the corresponding second bearing insert. 
     The skilled person will appreciate that except where mutually exclusive, a feature or parameter described in relation to any one of the above aspects may be applied to any other aspect. Furthermore, except where mutually exclusive, any feature or parameter described herein may be applied to any aspect and/or combined with any other feature or parameter described herein. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       Embodiments will now be described by way of example only, with reference to the Figures, in which: 
         FIG.  1    is a sectional side view of a gas turbine engine; 
         FIG.  2    is a close up sectional side view of an upstream portion of a gas turbine engine; 
         FIG.  3    is a partially cut-away view of a gearbox for a gas turbine engine; 
         FIG.  4    is a schematic perspective view of a joint assembly, according to an embodiment of the present disclosure; 
         FIG.  5    is a schematic exploded perspective view of the joint assembly of  FIG.  4   , according to an embodiment of the present disclosure; 
         FIG.  6 A  is a schematic top view of the joint assembly of  FIG.  4   , according to an embodiment of the present disclosure; 
         FIG.  6 B  is a schematic sectional view of the joint assembly taken along a section line B-B′ as shown in  FIG.  6 A , according to an embodiment of the present disclosure; 
         FIG.  7 A  is a schematic side view of the joint assembly of  FIG.  4   , according to an embodiment of the present disclosure; 
         FIG.  7 B  is a schematic sectional view of the joint assembly taken along a section line C-C′ as shown in  FIG.  7 A , according to an embodiment of the present disclosure; 
         FIG.  8 A  is a schematic sectional exploded view of a pin, a ring, and a first clevis or a second clevis, according to an embodiment of the present disclosure; 
         FIG.  8 B  is a detailed schematic sectional view of the pin, the ring, and the first clevis or the second clevis of  FIG.  8 A  in an assembled state, according to an embodiment of the present disclosure; 
         FIG.  9 A  is a schematic sectional exploded view of the pin, the ring, and the first clevis or the second clevis, according to another embodiment of the present disclosure; 
         FIG.  9 B  is a detailed schematic sectional view of the pin, the ring, and the first clevis or the second clevis of  FIG.  9 A  in an assembled state, according to an embodiment of the present disclosure; 
         FIG.  10 A  is a schematic sectional exploded view of the pin, the ring, and the first clevis or the second clevis, according to yet another embodiment of the present disclosure; 
         FIG.  10 B  is a detailed schematic sectional view of the pin, the ring, and the first clevis or the second clevis of  FIG.  10 A  in an assembled state, according to an embodiment of the present disclosure; and 
         FIG.  11    is a flow chart illustrating a method of manufacturing a joint assembly, according to an embodiment of the present disclosure. 
     
    
    
     DETAILED DESCRIPTION OF THE DISCLOSURE 
     Aspects and embodiments of the present disclosure will now be discussed with reference to the accompanying figures. Further aspects and embodiments will be apparent to those skilled in the art. 
       FIG.  1    illustrates a gas turbine engine  10  having a principal rotational axis  9 . The engine  10  comprises an air intake  12  and a propulsive fan  23  that generates two airflows: a core airflow A and a bypass airflow B. The gas turbine engine  10  comprises an engine core  11  that receives the core airflow A. The engine core  11  comprises, in axial flow series, a low pressure compressor  14 , a high-pressure compressor  15 , combustion equipment  16 , a high-pressure turbine  17 , a low pressure turbine  19  and a core exhaust nozzle  20 . A nacelle  21  surrounds the gas turbine engine  10  and defines a bypass duct  22  and a bypass exhaust nozzle  18 . The bypass airflow B flows through the bypass duct  22 . The fan  23  is attached to and driven by the low pressure turbine  19  via a shaft  26  and an epicyclic gearbox  30 . 
     In use, the core airflow A is accelerated and compressed by the low pressure compressor  14  and directed into the high-pressure compressor  15  where further compression takes place. The compressed air exhausted from the high-pressure compressor  15  is directed into the combustion equipment  16  where it is mixed with fuel and the mixture is combusted. The resultant hot combustion products then expand through, and thereby drive, the high pressure and low pressure turbines  17 ,  19  before being exhausted through the core exhaust nozzle  20  to provide some propulsive thrust. The high pressure turbine  17  drives the high-pressure compressor  15  by a suitable interconnecting shaft  27 . The fan  23  generally provides the majority of the propulsive thrust. The epicyclic gearbox  30  is a reduction gearbox. 
     An exemplary arrangement for a geared fan gas turbine engine  10  is shown in  FIG.  2   . The low pressure turbine  19  (see  FIG.  1   ) drives the shaft  26 , which is coupled to a sun wheel, or sun gear,  28  of the epicyclic gear arrangement  30 . Radially outwardly of the sun gear  28  and intermeshing therewith is a plurality of planet gears  32  that are coupled together by a planet carrier  34 . The planet carrier  34  constrains the planet gears  32  to process around the sun gear  28  in synchronicity whilst enabling each planet gear  32  to rotate about its own axis. The planet carrier  34  is coupled via linkages  36  to the fan  23  in order to drive its rotation about the rotational axis  9 . Radially outwardly of the planet gears  32  and intermeshing therewith is an annulus or ring gear  38  that is coupled, via linkages  40 , to a stationary supporting structure  24 . 
     Note that the terms “low pressure turbine” and “low pressure compressor” as used herein may be taken to mean the lowest pressure turbine stages and lowest pressure compressor stages (i.e., not including the fan  23 ), respectively, and/or the turbine and compressor stages that are connected together by the interconnecting shaft  26  with the lowest rotational speed in the engine (i.e. not including the gearbox output shaft that drives the fan  23 ). In some literature, the “low pressure turbine” and “low pressure compressor” referred to herein may alternatively be known as the “intermediate pressure turbine” and “intermediate pressure compressor”. Where such alternative nomenclature is used, the fan  23  may be referred to as a first, or lowest pressure, compression stage. 
     The epicyclic gearbox  30  is shown by way of example in greater detail in  FIG.  3   . Each of the sun gear  28 , planet gears  32  and ring gear  38  comprise teeth about their periphery to intermesh with the other gears. However, for clarity only exemplary portions of the teeth are illustrated in  FIG.  3   . There are four planet gears  32  illustrated, although it will be apparent to the skilled reader that more or fewer planet gears  32  may be provided within the scope of the claimed invention. Practical applications of a planetary epicyclic gearbox  30  generally comprise at least three planet gears  32 . 
     The epicyclic gearbox  30  illustrated by way of example in  FIGS.  2  and  3    is of the planetary type, in that the planet carrier  34  is coupled to an output shaft via linkages  36 , with the ring gear  38  fixed. However, any other suitable type of epicyclic gearbox  30  may be used. By way of further example, the epicyclic gearbox  30  may be a star arrangement, in which the planet carrier  34  is held fixed, with the ring (or annulus) gear  38  allowed to rotate. In such an arrangement the fan  23  is driven by the ring gear  38 . By way of further alternative example, the gearbox  30  may be a differential gearbox in which the ring gear  38  and the planet carrier  34  are both allowed to rotate. 
     It will be appreciated that the arrangement shown in  FIGS.  2  and  3    is by way of example only, and various alternatives are within the scope of the present disclosure. Purely by way of example, any suitable arrangement may be used for locating the gearbox  30  in the engine  10  and/or for connecting the gearbox  30  to the engine  10 . By way of further example, the connections (such as the linkages  36 ,  40  in the  FIG.  2    example) between the gearbox  30  and other parts of the engine  10  (such as the input shaft  26 , the output shaft and the fixed structure  24 ) may have any desired degree of stiffness or flexibility. By way of further example, any suitable arrangement of the bearings between rotating and stationary parts of the engine (for example, between the input and output shafts from the gearbox and the fixed structures, such as the gearbox casing) may be used, and the disclosure is not limited to the exemplary arrangement of  FIG.  2   . For example, where the gearbox  30  has a star arrangement (described above), the skilled person would readily understand that the arrangement of output and support linkages and bearing locations would typically be different to that shown by way of example in  FIG.  2   . 
     Accordingly, the present disclosure extends to a gas turbine engine having any arrangement of gearbox styles (for example, star or planetary), support structures, input and output shaft arrangement, and bearing locations. 
     Optionally, the gearbox may drive additional and/or alternative components (e.g., the intermediate pressure compressor and/or a booster compressor). 
     Other gas turbine engines to which the present disclosure may be applied may have alternative configurations. For example, such engines may have an alternative number of compressors and/or turbines and/or an alternative number of interconnecting shafts. By way of further example, the gas turbine engine shown in  FIG.  1    has a split flow nozzle  18 ,  20  meaning that the flow through the bypass duct  22  has its own nozzle  18  that is separate to and radially outside the core exhaust nozzle  20 . However, this is not limiting, and any aspect of the present disclosure may also apply to engines in which the flow through the bypass duct  22  and the flow through the core  11  are mixed, or combined, before (or upstream of) a single nozzle, which may be referred to as a mixed flow nozzle. One or both nozzles (whether mixed or split flow) may have a fixed or variable area. Whilst the described example relates to a turbofan engine, the disclosure may apply, for example, to any type of gas turbine engine, such as an open rotor (in which the fan stage is not surrounded by a nacelle) or turboprop engine, for example. In some arrangements, the gas turbine engine  10  may not comprise a gearbox  30 . 
     The geometry of the gas turbine engine  10 , and components thereof, is defined by a conventional axis system, comprising an axial direction (which is aligned with the rotational axis  9 ), a radial direction (in the bottom-to-top direction in  FIG.  1   ), and a circumferential direction (perpendicular to the page in the  FIG.  1    view). The axial, radial and circumferential directions are mutually perpendicular. 
     In addition, the present invention is equally applicable to aero gas turbine engines, marine gas turbine engines, and land-based gas turbine engines. 
     Generally, the gas turbine engine  10  produces very high-pressure air which is ducted in pipe systems for use in various parts of the gas turbine engine  10  and/or in applications external to the gas turbine engine  10 . Applications may typically include engine bleed air system (EBAS) ducts, starter air system ducts, and anti-icing ducts. 
     The pipe system may require flexible joints to accommodate irregular internal passages of the aircraft, and/or other applications in which the pipe system is used. During operation of the gas turbine engine  10 , high temperatures and fluctuations in air pressure inside the pipe system may cause stresses on the pipes and joints of the pipe system. Sections of the pipe system may therefore be connected to each other through gimbals. Typically, gimbals are joints that allow a limited amount of movement between sections of the pipe system to accommodate stresses that result from the pipes/ducts moving during operation of the engine and to provide the required amount of flexibility for installation and operation of the pipe system. 
       FIG.  4    illustrates a joint assembly  100  for joining a first component  102  to a second component  104 , according to an embodiment of the present disclosure. Specifically,  FIG.  4    illustrates a gimbal for joining the first component  102  to the second component  104 . The gas turbine engine  10  (shown in  FIG.  1   ) includes the first and second components  102 ,  104 . Specifically, the first and second components  102 ,  104  may be respective pipe sections of the pipe system of the gas turbine engine  10  (shown in  FIG.  1   ). In some embodiments, the joint assembly  100  is substantially linear such that various components of the joint assembly  100  are arranged along an axis X-X′. 
     The joint assembly  100  includes a first clevis  110 , a second clevis  120 , and a ring  130  at least partially surrounding the first clevis  110  and the second clevis  120 . In some embodiments, the first clevis  110  and the second clevis  120  are pivotally connected to the ring  130  such that the first clevis  110  is rotatable with respect to the ring  130  about an axis Y-Y′ and the second clevis  120  is rotatable with respect to the ring  130  about an axis Z-Z′. Various parts and components of the joint assembly  100  will be described hereinafter in greater detail. In some embodiments, the axes X-X′, Y-Y′, Z-Z′ may be mutually orthogonal to each other. 
       FIG.  5    illustrates an exploded view of the joint assembly  100  along the axis X-X′, according to an embodiment of the present disclosure. Referring now to  FIGS.  4  and  5   , the joint assembly  100  further includes a first liner  202  configured to be coupled to the first component  102 . The joint assembly  100  further includes a second liner  204  configured to be coupled to the second component  104 . In some embodiments, the first and second liners  202 ,  204  are coupled to the first and second components  102 ,  104 , respectively, through welding. In some embodiments, the first and second liners  202 ,  204  may be cylindrical in cross-section to assist in providing fluid-tight connections to pipes or ducts that are also typically cylindrical in cross-section. 
     The joint assembly  100  further includes a bellows  210  fixedly coupled to each of the first liner  202  and second liner  204 . In some embodiments, the bellows  210  is fixedly coupled to the first liner  202  and second liner  204  through respective sealing rings  262 ,  264  (also shown in  FIGS.  6 B and  7 B ). In some embodiments, the bellows  210  provides a degree of stiffness to the joint assembly  100  such that a possible relative movement of the first liner  202  and second liner  204  of the joint assembly  100  may be controlled to within known limits. Further, the bellows  210  may be coupled to each of the first liner  202  and second liner  204  such that the bellows  210  may provide an internal passage through which the contents of the first and second components  102 ,  104 , that are connected to the joint assembly  100 , may pass through. In some embodiments, the first and second clevises  110 ,  120  may at least partially protect the bellows  210  and the first and second liners  202 ,  204 , respectively, from an external environment. 
     The joint assembly  100  further includes the first clevis  110  fixedly coupled to the first liner  202  and at least partially enclosing the first liner  202  and the bellows  210 . In some embodiments, a first clevis end portion  212  of the first clevis  110  is fixedly coupled to an end portion  206  of the first liner  202 . The first clevis  110  includes a plurality of first extensions  214  and a plurality of first clevis apertures  216  corresponding to the plurality of first extensions  214 . Each of the plurality of first extensions  214  extends from the first clevis end portion  212  of the first clevis  110  away from the first component  102  (shown in  FIG.  4   ). In some embodiments, the first clevis  110  and the first extensions  214  may be integrally formed as one-piece component. 
     Each first extension  214  defines a corresponding first clevis aperture  216  from the plurality of first clevis apertures  216  therethrough. Further, the first clevis  110  includes a pair of first extensions  214  and a pair of corresponding first clevis apertures  216 , however, it should be understood that the first clevis  110  may include any number of first extensions  214  and the corresponding first clevis apertures  216 . In the illustrated embodiment of  FIGS.  4  and  5   , the pair of first extensions  214  are disposed diametrically opposite to each other. 
     The joint assembly  100  further includes a plurality of first bearing inserts  218  fixedly coupled to the first clevis  110 . Each first bearing insert  218  is at least partially received within a corresponding first clevis aperture  216  from the plurality of first clevis apertures  216 . In some embodiments, each first bearing insert  218  may be fully received within the corresponding first clevis aperture  216 . In some other embodiments, one or more of the first bearing inserts  218  may at least partially protrude from the corresponding first clevis apertures  216 . 
     The joint assembly  100  further includes the second clevis  120  fixedly coupled to the second liner  204  and at least partially enclosing the second liner  204  and the bellows  210 . In some embodiments, a second clevis end portion  222  of the second clevis  120  is fixedly coupled to an end portion  208  of the second liner  204 . 
     The second clevis  120  includes a plurality of second extensions  224  angularly spaced apart from each of the plurality of first extensions  214  of the first clevis  110  and a plurality of second clevis apertures  226  corresponding to the plurality of second extensions  224 . Each of the plurality of second extensions  224  extend from the second clevis end portion  222  of the second clevis  120  away from the second component  104  (shown in  FIG.  4   ). In some embodiments, the second clevis  120  and the second extensions  224  may be integrally formed as one-piece component. 
     In some embodiments, the first clevis end portion  212  and the second clevis end portion  222  may provide a protective shield for at least a portion of the bellows  210 , for example, the portion of the bellow  210  that is not protected, or only partially protected, by the plurality of first and second extensions  214 ,  224 . It should be understood that the first clevis end portion  212  and the second clevis end portion  222  may take various forms to fulfil the intended purpose. For example, the first clevis end portion  212  and/or the second clevis end portion  222  may be annular to maximise protective cover for the bellows  210 . Further, a length and/or a shape of the first and second clevis end portions  212 ,  222  may vary based on application requirements. The first clevis end portion  212  and/or the second clevis end portion  222  may be arranged to complement the configuration of the first and second extensions  214 ,  224 , for example, to maximise protective shielding for the bellows  210  of the joint assembly  100 . 
     Each second extension  224  defines a corresponding second clevis aperture  226  from the plurality of second clevis apertures  226  therethrough. Further, the second clevis  120  includes a pair of second extensions  224  and a pair of corresponding second clevis apertures  226 , however, it should be understood that the second clevis  120  may include any number of second extensions  224  and the corresponding second clevis apertures  226 . In the illustrated embodiment of  FIGS.  4  and  5   , the second extensions  224  are disposed diametrically opposite to each other. 
     In some embodiments, the plurality of first extensions  214  and the plurality of second extensions  224  are equally spaced around the axis X-X′ of the joint assembly  100 . In some embodiments, the first and second devises  110 ,  120  may have a common shape. Further, the plurality of first extensions  214  extend generally axially in a first direction A 1  and the plurality of second extensions  224  extend generally axially in a second direction A 2  opposite to the first direction A 1 . 
     The joint assembly  100  further includes a plurality of second bearing inserts  228  fixedly coupled to the second clevis  120 . Each second bearing insert  228  is at least partially received within a corresponding second clevis aperture  226  from the plurality of second clevis apertures  226 . In some embodiments, each of the second bearing insert  228  may be fully received within the corresponding second clevis aperture  226 . In some other embodiments, one or more of the second bearing inserts  228  may at least partially protrude from the corresponding second clevis apertures  226 . 
     In some embodiments, each of the pluralities of first and second bearing inserts  218 ,  228  has an annular shape, such that outer surfaces of the pluralities of first and second bearing inserts  218 ,  228  engage with inner surfaces of the corresponding first and second bearing apertures  216 ,  226 . 
     Fully functional joint assemblies  100  may be made with various numbers of devises, however, in the illustrated embodiment of  FIGS.  4  and  5   , the joint assembly  100  includes a pair of devises (i.e., the first and second devises  110 ,  120 ) angularly spaced around the axis X-X′ of the joint assembly  100  that balances a structural strength and a structural simplicity of the joint assembly  100 . However, in some other embodiments, the joint assembly  100  may include multiple devises arranged along the axis X-X′. 
     The joint assembly  100  further includes the ring  130  at least partially surrounding the first clevis  110  and the second clevis  120 . The ring  130  includes a plurality of ring apertures  232  extending therethrough. In some embodiments, the ring  130  may be integrally formed in one-piece. The plurality of ring apertures  232  includes a set of first ring apertures  234  corresponding to the plurality of first clevis apertures  216  and a set of second ring apertures  236  corresponding to the plurality of second clevis apertures  226 . Each first ring aperture  234  is aligned with a corresponding first clevis aperture  216  from the plurality of first clevis apertures  216  of the first clevis  110 . Each second ring aperture  236  is aligned with a corresponding second clevis aperture  226  from the plurality of second clevis apertures  226  of the second clevis  120 . 
     The joint assembly  100  further includes a plurality of pins  240  corresponding to the plurality of ring apertures  232  of the ring  130  and configured to rotatably couple the ring  130  to each of the first clevis  110  and the second clevis  120 . Specifically, the first clevis  110  is rotatably coupled to the ring  130  through the plurality of pins  240  and the plurality of first extensions  214 . Similarly, the second clevis  120  is rotatably coupled to the ring  130  through the plurality of pins  240  and the plurality of second extensions  224 . Thus, the first clevis  110  and the second clevis  120  are able to pivot about the respective axes Y-Y′ and Z-Z′ through the plurality of pins  240 , thereby enabling the joint assembly  100  to accommodate angular movements of the first and second components  102 ,  104  that are connected through the joint assembly  100 . 
     In other words, the first clevis  110  and the second clevis  120  may move relative to each other by pivoting about the plurality of pins  240 . The joint assembly  100  may therefore allow a limited amount of movement between the first component  102  and the second component  104  to accommodate stresses that result from movements of the first component  102  and/or the second component  104 . The first clevis  110 , the second clevis  120 , and the ring  130  of the joint assembly  100  may function as a single unitary component, i.e., the joint assembly  100  is made and used as a single, one-piece component. 
     In some embodiments, the pin  240  may have a substantially T-shaped cross-section. Each pin  240  includes a head portion  242  received at least partially in a corresponding ring aperture  232  from the plurality of ring apertures  232 . Each pin  240  further includes a shaft portion  244  extending from the head portion  242  and received at least partially within the corresponding ring aperture  232 . The shaft portion  244  of each pin  240  is further at least partially received in the corresponding first bearing insert  218  or the corresponding second bearing insert  228  that is received in the corresponding first clevis aperture  216  or the corresponding second clevis aperture  226  aligned with the corresponding ring aperture  232 . 
     Specifically, the shaft portion  244  of some of the pins  240  is at least partially received in the corresponding first ring aperture  234  from the set of first ring apertures  234  and the corresponding first bearing insert  218  that is received in the corresponding first clevis aperture  216  to rotatably couple the first clevis  110  to the ring  130 . Similarly, the shaft portion  244  of some of the pins  240  is at least partially received in the corresponding second ring aperture  236  from the set of second ring apertures  236  and the corresponding second bearing insert  228  that is received in the corresponding second clevis aperture  226  to rotatably couple the second clevis  120  to the ring  130 . 
       FIG.  6 A  illustrates a schematic top view of the joint assembly  100 . As shown in  FIG.  6 A , one of the pins  240  is configured to rotatably couple the ring  130  to the first clevis  110 . The head portion  242  of the pin  240  is coupled to the ring  130  by a corresponding weld  302 . 
     In some embodiments, the weld  302  between the head portion  242  and the ring  130  includes an electron beam weld or a laser beam weld. The aforementioned welding techniques (i.e., electron and laser beam welding) may allow a repeatable and desirable weld penetration to be achieved as compared to conventional joining techniques, such as arc welding. Electron beam welding or laser beam welding are generally low heat input processes as compared to arc welding. Thus, the amount of material that is heat affected (or a weld heat affected zone) during the welding process is much less. This may allow for a lighter design (e.g., a lighter head portion  242 ) of the joint assembly  100  due to a larger amount of material retaining its original properties after the welding process. 
     It should be understood that the present disclosure is not restricted to the aforementioned welding techniques only, and generally any beam welding technique may be utilized for coupling the head portion  242  of the pin  240  to the ring  130 . Further, the aforementioned welding techniques are equally applicable to all the pins  240  of the joint assembly  100  that rotatably coupled the ring  130  to each of the first clevis  110  and the second clevis  120 . 
       FIG.  6 B  illustrates a schematic sectional view of the joint assembly  100  taken long a section line B-B′ shown in  FIG.  6 A . The shown cross-section is only through an upper portion of the joint assembly  100  and the cross-section through the lower portion, which would be substantially similar and symmetric to the upper portion, is not shown. As shown in  FIG.  6 B , the bellows  210  is fixedly coupled to the first liner  202  and the second liner  204  through the respective sealing rings  262 ,  264 . In some embodiments, the sealing rings  262 ,  264  may be coupled to ends of the bellows  210 , for example, through welding. 
     In some embodiments, the bellows  210  is fixedly coupled to the first liner  202  by one or more first bellows welds  304 . Similarly, the bellows  210  is fixedly coupled to the second liner  204  by one or more second bellows welds  306 . The sealing rings  262 ,  264  may protect the bellows  210  by providing extra thickness at the ends of the bellows  210  as the bellows  210  is welded to the first liner  202  or the second liner  204 . It should be understood that the bellows  210  may be coupled to the first liner  202  or the second liner  204  through any other suitable arrangements based on application requirements. 
     In some embodiments, the first clevis  110  is fixedly coupled to the first liner  202  by one or more first clevis welds  308 . In some embodiments, the second clevis  120  is fixedly coupled to the second liner  204  by one or more second clevis welds  310 . For example, the first and second clevises  110 ,  120  may be welded to the first and second liners  202 ,  204  through tungsten inert gas (TIG) welding, solid state welding, etc. The first liner  202  or the second liner  204  may transfer angular movements of the first component  102  (shown in  FIG.  4   ) and the second component  104  (shown in  FIG.  4   ) to the first and second clevises  110 ,  120  through the first clevis weld  308  and the second clevis weld  310 , respectively. The first and second clevises  110 ,  120  may pivot about the plurality of pins  240  with respect to the ring  130  to accommodate the angular movements of the first component  102  (shown in  FIG.  4   ) and the second component  104  (shown in  FIG.  4   ). 
     The shaft portion  244  of each pin  240  is coupled to the ring  130  by a corresponding interference fit  312 . The shaft portion  244  of some of the pins  240  is coupled to the corresponding first bearing insert  218  by a corresponding clearance fit  314 , such that the shaft portion  244  is rotatable relative to the first bearing insert  218 . Further, in some embodiments, each first bearing insert  218  is fixedly coupled to the first clevis  110  by a corresponding first insert weld  316  or a corresponding first interference fit  318 . In should be understood that each first bearing insert  218  may be fixedly coupled to the first clevis  110  through any other known joining methods, such as, for example, brazing, adhesively bonding, screwing, bolting, and/or the like. In some embodiments, each first bearing insert  218  may be fixedly coupled to the first clevis  110  through a threaded connection. 
       FIG.  7 A  illustrates a schematic side view of the joint assembly  100 . As shown in  FIG.  7 A , the pin  240  is configured to rotatably couple the ring  130  to the second clevis  120 . The head portion  242  of the pin  240  is coupled to the ring  130  by a corresponding weld  402 . In some embodiments, the weld  402  between the head portion  242  and the ring  130  includes an electron beam weld or a laser beam weld. 
       FIG.  7 B  illustrates a schematic sectional perspective view of the joint assembly  100  taken long a section line C-C′ shown in  FIG.  7 A . The shown cross-section is only through an upper portion of the joint assembly  100  and the cross-section through the lower portion, which would be substantially similar and symmetric to the upper portion, is not shown. 
     The shaft portion  244  of some of the pins  240  is coupled to the corresponding second bearing insert  228  by a corresponding clearance fit  404 , such that the shaft portion  244  is rotatable relative to the second bearing insert  228 . Further, in some embodiments, each second bearing insert  228  is fixedly coupled to the second clevis  120  by a corresponding second insert weld  406  or a corresponding second interference fit  408 . In should be understood that the second bearing insert  228  may be fixedly coupled to the second clevis  120  through any other known joining methods, such as, for example, brazing, adhesively bonding, screwing, bolting, and/or the like. In some embodiments, each second bearing insert  228  may be fixedly coupled to the second clevis  120  through a threaded connection. 
     Referring to  FIGS.  6 B and  7 B , in some embodiments, each of the first and second bearing inserts  218 ,  228  may be a bushing or a cartridge bearing. In the latter case, the cartridge bearing may further eliminate static friction between the pin  240  and the first clevis  110  or the second clevis  120 , thereby reducing bending stiffness and interface loads between the pin  240  and the corresponding first bearing insert  218  or the corresponding second bearing insert  228 . 
     Referring now to  FIGS.  6 A,  6 B,  7 A and  7 B , in some embodiments, the pin  240  may transfer load (e.g., a load path) between the ring  130  and the first clevis  110  or the second clevis  120  through the corresponding interference fit  312 . The interference fit  312  may allow increase in load transfer between the ring  130  and the first clevis  110  or the second clevis  120  while also improving an efficiency of the load transfer. Thus, a joint assembly without the interference fit between the ring  130  and the first clevis  110  or the second clevis  120  may require a thicker and heavier ring. 
     The weld  302  (shown in  FIG.  6 A ) or the weld  402  (shown in  FIG.  7 A ) that couples the head portion  242  of the corresponding pin  240  to the ring  130  is located away from the corresponding interference fit  312  due to the specific shape of the pin  240  (i.e., substantially T-shaped design). This may displace the weld heat affected zone with weakened material properties away from the corresponding interference fit  312  that results in a robust design of the joint assembly  100 . Additionally, the interference fit  312  may reduce a bending moment on the pin  240  that allows for a smaller, lighter pin or a higher load capacity of the joint assembly  100 . This arrangement may also significantly reduce stresses on the welds  302 ,  402  (or other joints) between the head portion  242  of the pin  240  and the ring  130  that improves a fatigue life of the joint assembly  100 . 
     In some embodiments, each of the first and second clevises  110 ,  120  is made of a clevis material (e.g., a nickel chromium-based alloy). Each of the pluralities of first and second bearing inserts  218 ,  228  is made of a bearing material different from the clevis material. For example, the bearing material may include a metal, an alloy, a composite material, or a polymeric material, such as rubber, polyurethane, silicone or equivalents. Suitable polymeric material may be chosen for dampening vibrations of the joint assembly  100 . In some examples, the bearing material may have a relatively greater hardness of the one or more polymeric materials around a circumference of the pin  240  to achieve higher stiffness of material close to the pin  240  for resisting forces of the bellows  210 . 
     In some embodiments, the polymetric material may need to be co-moulded between two support rings, such that the polymetric material may be press-fitted into the corresponding first clevis aperture  216  or the corresponding second clevis aperture  226 , or even co-moulded into the corresponding first clevis aperture  216  or the corresponding second clevis aperture  226  itself. This may also provide the necessary abrasion resistance to the polymetric material. Further, in an application that requires reduction in stiffness of the joint assembly  100 , polymetric material with low stiction or frictional properties may be utilised, such as polytetrafluoroethylene (PTFE). 
     In some embodiments, a hardness of the clevis material is different from a hardness of the bearing material. Further, in some embodiments, the hardness of the bearing material is greater than the hardness of the clevis material. This may allow use of relatively cheaper materials for the first clevis  110  or the second clevis  120  as compared to the bearing material for the first bearing insert  218  or the second bearing insert  228 . Further, suitable bearing materials may be selected based on a desired stiffness of the joint assembly  100 , desired mechanical strength and wear resistance of the bearing materials, and friction between the pin  240  and the first clevis  110  or the second clevis  120 , while suitable clevis material may be selected for the first clevis  110  or the second clevis  120  based on ease of welding and machining. This may reduce an overall cost and weight of the joint assembly  100  as well as improve a service life of the joint assembly  100 . Additionally, the joint assembly  100  of the present disclosure may allow replacement of the first and second bearing inserts  218 ,  228  during maintenance while reusing the first and second clevises  110 ,  120 . 
       FIG.  8 A  illustrates a schematic sectional exploded view of an embodiment of the pin  240 , the ring  130 , and the first clevis  110  or the second clevis  120  of the joint assembly  100 .  FIG.  8 B  illustrates a detailed schematic sectional view of an embodiment of an assembly of the pin  240 , the ring  130  and the first clevis  110  or the second clevis  120  of the joint assembly  100 . In  FIGS.  8 A and  8 B , the first and second clevises  110 ,  120  and the first and second bearing inserts  218 ,  228  are shown together as a single component for illustrative and descriptive purposes. 
     Referring now to  FIGS.  8 A and  8 B , each pin  240  includes the head portion  242  and the shaft portion  244  extending from the head portion  242 . In some embodiments, the head portion  242  has a minimum head diameter  502  and the shaft portion  244  has a maximum shaft diameter  504  less than the minimum head diameter  502  of the head portion  242 . Thus, the pin  240  may have a substantially T-shaped cross section. In some embodiments, the shaft portion  244  includes a wide shaft section  510  disposed adjacent to the head portion  242  and having a minimum wide diameter  512 . 
     Further, each ring aperture  232  includes a wide aperture portion  506  configured to at least partially receive the head portion  242  of the corresponding pin  240  and a narrow aperture portion  508  disposed adjacent to the wide aperture portion  506  and configured to at least partially receive the shaft portion  244  of the corresponding pin  240 . The wide shaft section  510  of the shaft portion  244  of the pin  240  is at least partially received in the corresponding ring aperture  232 . 
     In some embodiments, a diameter  509  of the narrow aperture portion  508  is larger than the minimum wide diameter  512  of the wide shaft section  510  of the corresponding pin  240 . In some embodiments, the diameter  509  of the narrow aperture portion  508  is just large enough to at least partially receive the wide shaft section  510  of the shaft portion  244  of the corresponding pin  240  to provide the corresponding interference fit  312 . Further, a diameter  507  of the wide aperture portion  506  is larger than a maximum head diameter  503  to at least partially receive the head portion  242  of the corresponding pin. 
     In some embodiments, the shaft portion  244  further includes a narrow shaft section  514  disposed adjacent to the wide shaft section  510  opposite to the head portion  242  and having a maximum narrow diameter  516  less than the minimum wide diameter  512  of the wide shaft section  510 . The narrow shaft section  514  is at least partially received in the corresponding first bearing insert  218  or the corresponding second bearing insert  228 . In some embodiments, the maximum narrow diameter  516  of the narrow shaft section  514  of the pin  240  is smaller than an inner diameter  518  of the corresponding first bearing insert  218  or the corresponding second bearing insert  228  to form the corresponding clearance fit  314 ,  404  therewith. In some embodiments, the shaft portion  244  further includes a step  520  disposed between the wide and narrow shaft sections  510 ,  514 . In some embodiments, the step  520  separates the wide shaft section  510  from the narrow shaft section  514 . 
     The various sections of the shaft portion  244 , i.e., the wide shaft section  510 , the narrow shaft section  514 , and the step  520 , may allow for a quick and clean assembly of the pin  240 , the ring  130  and the corresponding first bearing inert  218  or the corresponding second bearing insert  228 . The narrow shaft section  514  may allow manual alignment of the ring  130  with the corresponding first bearing inert  218  or the corresponding second bearing insert  228  until the corresponding pin  240  is pressed through a pressing machine and the wide shaft section  510  forms the corresponding interference fit  312  with the narrow aperture portion  508  of the corresponding ring aperture  232 . This may eliminate damage to the ring  130  or the first and second clevises  110 ,  120  during assembly due to misalignment, which in turn reduces scrappage during manufacture of the joint assembly  100 . 
       FIG.  9 A  illustrates a detailed schematic sectional exploded view of a pin  602 , the ring  130 , and the first clevis  110  or the second clevis  120  of the joint assembly  100 , according to another embodiment of the present disclosure.  FIG.  9 B  illustrates a detailed schematic sectional view of the pin  602 , the ring  130 , and the first clevis  110  or the second clevis  120  of the joint assembly  100  in an assembled state. In the illustrated embodiments of  FIGS.  9 A and  9 B , the joint assembly  100  includes the pin  602  instead of the pin  240  (shown in  FIGS.  4 - 8 B ). In  FIGS.  9 A and  9 B , the first and second clevises  110 ,  120  are shown together as a single component and the first and second bearing inserts  218 ,  228  are shown together as a single component for illustrative and descriptive purposes. 
     Referring now to  FIGS.  9 A and  9 B , the pin  602  includes a head portion  606  and a shaft portion  604  extending from the head portion  606 . The shaft portion  604  of the pin  602  includes a uniform shaft section  608  disposed adjacent to the head portion  606  and having a substantially uniform shaft diameter  610 . The uniform shaft section  608  is at least partially received in the corresponding ring aperture  232  and in the corresponding first bearing insert  218  or the corresponding second bearing insert  228 . 
     In some embodiments, the diameter  509  of the narrow aperture portion  508  is just large enough to at least partially receive the uniform shaft section  608  of the shaft portion  604  of the corresponding pin  602  to form a corresponding interference fit  612 . Further, the uniform shaft section  608  forms a clearance fit  614  with the corresponding first bearing insert  218  or the corresponding second bearing insert  228 . In some embodiments, the uniform shaft diameter  610  of the uniform shaft section  608  of the pin  240  is smaller than the inner diameter  518  of the corresponding first bearing insert  218  or the corresponding second bearing insert  228  to form the corresponding clearance fit  614  therewith. 
     In some embodiments, the shaft portion  604  further includes a tapered shaft section  616  disposed adjacent to the uniform shaft section  608  opposite to the head portion  606  and tapering away from the uniform shaft section  608 . The tapered shaft section  616  has an average diameter  618  less than the uniform shaft diameter  610  of the uniform shaft section  608 . The tapered shaft section  616  at least partially extends out of the corresponding first clevis aperture  216  or the corresponding second clevis aperture  226  aligned with the corresponding ring aperture  232 . The tapered shaft section  616  may align the ring  130  with the corresponding first bearing insert  218  or the corresponding second bearing insert  228  as the pin  602  is at least partially received through the corresponding ring aperture  232  and through the corresponding first bearing inert  218  or the corresponding second bearing insert  228 . 
       FIG.  10 A  illustrates a detailed schematic sectional exploded view of a pin  702 , the ring  130 , and the first clevis  110  or the second clevis  120  of the joint assembly  100 , according to yet another embodiment of the present disclosure.  FIG.  10 B  illustrates a detailed schematic sectional view of the pin  702 , the ring  130 , and the first clevis  110  or the second clevis  120  of the joint assembly  100  in an assembled state. In the illustrated embodiments of  FIGS.  10 A and  10 B , the joint assembly  100  includes the pin  702  instead of the pin  240  (shown in  FIGS.  4 - 8 B ). In  FIGS.  10 A and  10 B , the first and second clevises  110 ,  120  are shown together as a single component and the first and second bearing inserts  218 ,  228  are shown together as a single component for illustrative and descriptive purposes. 
     Referring now to  FIGS.  10 A and  10 B , the pin  702  includes a head portion  706  and a shaft portion  704  extending from the head portion  706 . Each pin  702  further includes an aid guide  708  removably attached to an end  710  of the shaft portion  704  distal to the head portion  706 . The aid guide  708  tapers away from the end  710  of the shaft portion  704 , such that the aid guide  708  is configured to align the corresponding ring aperture  232  with the corresponding first bearing insert  218  or the corresponding second bearing insert  228  as the shaft portion  704  is at least partially received through the corresponding ring aperture  232  and through the corresponding first bearing insert  218  or the corresponding second bearing insert  228 . 
     In some embodiments, the aid guide  708  may be removably coupled (e.g., through adhesives, screws, etc.) to the end  710  of the shaft portion  704  such that the aid guide  708  may be removed after final assembly of the joint assembly  100 . 
       FIG.  11    is a flow chart illustrating a method  800  of manufacturing a joint assembly. The joint assembly may be similar to the joint assembly  100  of  FIGS.  4 - 10 B . 
     In some embodiments, the method  800  includes fixedly coupling the bellows  210  to the first liner  202  by one or more first bellows welds  304 . The first liner  202  is configured to be coupled to the first component  102 . In some embodiments, the method  800  further includes fixedly coupling the bellows  210  to the second liner  204  by one or more second bellows welds  306 . The second liner  204  is configured to be coupled to the second component  104 . 
     At step  802 , the method  800  further includes providing the first clevis  110  including the plurality of first extensions  214  and the plurality of first clevis apertures  216  corresponding to the plurality of first extensions  214 . Each first extension  214  defines the corresponding first clevis aperture  216  from the plurality of first clevis apertures  216  therethrough. In some embodiments, the method  800  further includes fixedly coupling the first clevis  110  to the first liner  202  by one or more first clevis welds  308 . 
     At step  804 , the method  800  further includes providing the second clevis  120  including the plurality of second extensions  224  angularly spaced apart from the plurality of first extensions  214  of the first clevis  110  and the plurality of second clevis apertures  226  corresponding to the plurality of second extensions  224 . Each second extension  224  defines the corresponding second clevis aperture  226  from the plurality of second clevis apertures  226  therethrough. In some embodiments, the method  800  further includes fixedly coupling the second clevis  120  to the second liner  204  by one or more second clevis welds  310 . 
     At step  806 , the method  800  further includes at least partially surrounding the first clevis  110  and the second clevis  120  with the ring  130  including the plurality of ring apertures  232  extending therethrough, such that each of the set of first ring apertures  234  from the plurality of ring apertures  232  aligns with the corresponding first clevis aperture  216  from the plurality of first clevis apertures  216  of the first clevis  110  and each of the set of second ring apertures  236  from the plurality of ring apertures  232  aligns with the corresponding second clevis aperture  226  from the plurality of second clevis apertures  226  of the second clevis  120 . 
     At step  808 , the method  800  further includes fixedly coupling the plurality of first bearing inserts  218  to the first clevis  110 , such that each first bearing insert  218  is at least partially received within the corresponding first clevis aperture  216  from the plurality of first clevis apertures  216 . In some embodiments, each first bearing insert  218  is fixedly coupled to the first clevis  110  by the corresponding first insert weld  316  or the corresponding first interference fit  318 . 
     At step  810 , the method  800  further includes fixedly coupling the plurality of second bearing inserts  228  to the second clevis  120 , such that each second bearing insert  228  is at least partially received within the corresponding second clevis aperture  226  from the plurality of second clevis apertures  226 . In some embodiments, each second bearing insert  228  is fixedly coupled to the second clevis  120  by the corresponding second insert weld  406  or the corresponding second interference fit  408 . 
     At step  812 , the method  800  further includes inserting the plurality of pins  240 ,  602 ,  702  through the plurality of ring apertures  232 , such that the head portion  242 ,  606 ,  706  of each pin  240 ,  602 ,  702  is at least partially received in the corresponding ring aperture  232  from the plurality of ring apertures  232 , and the shaft portion  244 ,  604 ,  704  of each pin  240 ,  602 ,  702  is at least partially received in the corresponding ring aperture  232 . The shaft portion  244 ,  604 ,  704  of each pin  240 ,  602 ,  702  is fixedly coupled to the ring  130  by the corresponding interference fit  312 . 
     In some embodiments, the method  800  further includes removably attaching the aid guide  708  to the end  710  of the shaft portion  704  of each pin  702  distal to the head portion  706 . The aid guide  708  tapers away from the end  710  of the shaft portion  704 , such that the aid guide  708  is configured to align the corresponding ring aperture  232  with the corresponding first bearing insert  218  or the corresponding second bearing insert  228  as the shaft portion  704  is at least partially received through the corresponding ring aperture  232  and through the corresponding first bearing insert  218  or the corresponding second bearing insert  228 . 
     At step  814 , the method  800  further includes at least partially receiving the shaft portion  244 ,  604 ,  704  of each pin  240 ,  602 ,  702  in the corresponding first bearing insert  218  or the corresponding second bearing insert  228  that is received in the corresponding first clevis aperture  216  or the corresponding second clevis aperture  226  aligned with the corresponding ring aperture  232 . The shaft portion  244 ,  604 ,  704  of each pin  240 ,  602 ,  702  is rotatably coupled to the corresponding first bearing insert  218  or the corresponding second bearing insert  228  by the corresponding clearance fit  314 ,  404 ,  614  such that each of the first and second clevises  110 ,  120  is rotatably coupled to the ring  130 . 
     At step  816 , the method  800  further includes fixedly coupling the head portion  242 ,  606 ,  706  of each pin  240 ,  602 ,  702  to the ring  130  by electron beam welding or laser beam welding. 
     It will be understood that the invention is not limited to the embodiments above-described and various modifications and improvements can be made without departing from the concepts described herein. Except where mutually exclusive, any of the features may be employed separately or in combination with any other features and the disclosure extends to and includes all combinations and sub-combinations of one or more features described herein.