Improved patching and usage

Abstract

To provide improved patch rings and related methods.SOLUTION: A shaft assembly 60 includes a first shaft having a first rabbet 62 annularly defined therein. The first rabbet includes a first axially extending face 66 and a first radially extending face 68. A second shaft is coupled to the first shaft. The second shaft includes a second rabbet 64 annularly defined therein and positioned opposite the first rabbet 62. The second rabbet 64 includes a second axially extending face 70 and a second radially extending face 72. A patch ring is mounted between the first rabbet 62 and the second rabbet 64. The patch ring includes a main body positioned between and in contact with the first axially extending face 66 and the second axially extending face 70. A first arm 104 extends radially outward from the main body, and a second arm 106 extends radially inward from the main body.SELECTED DRAWING: Figure 3

Description

[Technical field]

[0001] FIELD OF THE DISCLOSURE The present disclosure relates generally to an improved patch ring and related methods, and more particularly, to an improved patch ring for use in a marriage joint of a turbomachine. [Background technology]

[0002] Turbomachines are utilized in various industries and applications for the purpose of energy transfer. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of a working fluid entering the gas turbine engine and supplies the compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed in the combustion section and combusted in a combustion chamber to generate high-pressure and high-temperature combustion gases. The combustion gases flow from the combustion section to the turbine section, where they expand to generate work. For example, the expansion of the combustion gases in the turbine section can rotate a rotor shaft connected to, for example, a generator to generate electricity. The combustion gases then exit the gas turbine via the exhaust section.

[0003] During operation of a turbomachine, various components of the turbomachine endure various forms of wear. Such wear can lead to damage and / or failure of the individual components and the turbomachine in general. In particular, the compressor shaft and turbine shaft, which rotate during operation of the turbomachine, are subject to wear. For example, a modern compressor and turbine shaft may be expected to operate for approximately 144,000 hours and start up approximately 5,000 times. Furthermore, in many cases, certain wear-sensitive locations on a component, such as rabbet flanges, may tend to wear out faster than other locations. These wear-sensitive locations may limit the life of the associated compressor shaft and / or turbine shaft.

[0004] A drawback of compressor and turbine shafts is the need to repair them to maintain the design intent. Currently, compressor and turbine shafts are repaired by post-operation machining of the contact surfaces defined between the two shafts to restore the design specified interference between the two shafts. However, machining the rabbet joint over multiple service intervals may adversely affect the desired contact interference between the compressor and turbine shafts.

[0005] Accordingly, improved methods and apparatus for repairing turbomachinery joints are desired in the art, and in particular, improved methods and apparatus for repairing rabbet joints between compressor and turbine shafts. Summary of the Invention

[0006] Aspects and advantages of the shaft assembly, turbomachine, and method of servicing a turbomachine according to the present disclosure will be set forth in part in the description which follows, or will be obvious from the description, or may be learned by practice of the present teachings.

[0007] According to one embodiment, a shaft assembly is provided. The assembly includes a first shaft having a first rabbet annularly defined therein. The first rabbet includes a first axially extending surface and a first radially extending surface. A second shaft is coupled to the first shaft. The second shaft includes a second rabbet annularly defined therein and positioned opposite the first rabbet. The second rabbet includes a second axially extending surface and a second radially extending surface. A patch ring is mounted between the first rabbet and the second rabbet. The patch ring includes a body positioned between and in contact with the first axially extending surface and the second axially extending surface. A first arm extends radially outward from the body and a second arm extends radially inward from the body.

[0008] According to another embodiment, a turbomachine is provided. The turbomachine includes a compressor section, a combustor section, and a turbine section. The turbomachine further includes a compressor shaft at least partially disposed in the compressor section. The compressor shaft has a first rabbet annularly defined therein. The first rabbet includes a first axially extending surface and a first radially extending surface. The turbomachine further includes a turbine shaft at least partially disposed in the turbine section and coupled to the compressor shaft. The turbine shaft has a second rabbet annularly defined therein and positioned opposite the first rabbet. The second rabbet includes a second axially extending surface and a second radially extending surface. A patch ring is mounted between the first rabbet and the second rabbet.

[0009] According to yet another embodiment, a method of servicing a turbomachine is provided. The method includes machining a first rabbet in an aft end of a compressor shaft. The first rabbet includes a first axially extending surface and a first radially extending surface. The first rabbet is annularly defined in the aft end of the compressor shaft. The method further includes machining a second rabbet in a forward end of a turbine shaft. The second rabbet includes a second axially extending surface and a second radially extending surface. The second rabbet is annularly defined in the forward end of the turbine shaft and is positioned opposite the first rabbet. The method further includes installing a patch ring between the first rabbet and the second rabbet.

[0010] These and other features, aspects, and advantages of the present shaft assembly, turbomachine, and method of servicing a turbomachine will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present technology and, together with the description, serve to explain the principles of the technology.

[0011] A full and enabling disclosure of the present shaft assembly, turbomachine, and method of servicing a turbomachine, including the best mode of making and using the present systems and methods, directed to one of ordinary skill in the art, is set forth in this specification, which makes reference to the accompanying drawings. [Brief description of the drawings]

[0012] [Figure 1] 1 is a schematic diagram of a turbomachine according to an embodiment of the present disclosure; [Diagram 2] FIG. 13 is a cross-sectional view of a shaft assembly prior to installation of a patch ring according to an embodiment of the present disclosure. [Diagram 3] FIG. 13 is a cross-sectional view of a shaft assembly showing a patch ring positioned therein, according to an embodiment of the present disclosure. [Figure 4] FIG. 13 is a cross-sectional view of a shaft assembly showing a patch ring positioned therein, according to an embodiment of the present disclosure. [Diagram 5] FIG. 1 is a side view of a patch ring according to an embodiment of the present disclosure. [Figure 6] FIG. 6 is an enlarged perspective view of the patch ring shown in FIG. 5 according to an embodiment of the present disclosure. [Figure 7] FIG. 1 is a side view of a patch ring according to an embodiment of the present disclosure. [Figure 8] FIG. 8 is an enlarged perspective view of the patch ring shown in FIG. 7 according to an embodiment of the present disclosure. [Figure 9] 1 illustrates a method of servicing a turbomachine according to an embodiment of the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0013] Reference will now be made in detail to the embodiments of the present shaft assembly, turbomachine, and method of servicing a turbomachine, one or more examples of which are illustrated in the drawings. The examples are provided by way of explanation of the present technology, not as limitations of the technology. Indeed, it will be apparent to those skilled in the art that modifications and variations can be made in the present technology without departing from the scope or spirit of the claimed technology. For example, features illustrated or described as part of one embodiment can be used in another embodiment to yield still further embodiments. Thus, the present disclosure is intended to cover such modifications and variations that come within the scope of the appended claims and their equivalents.

[0014] The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description are used to refer to like or similar parts of the invention. As used herein, the terms "first", "second", and "third" may be used interchangeably to distinguish one component from another, and are not intended to denote the location or importance of the individual components.

[0015] As used herein, the terms "upstream" (or "forward") and "downstream" (or "aft") refer to relative directions with respect to the flow of fluid in a fluid pathway. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows. The term "radially" refers to a relative direction that is substantially perpendicular to the axial centerline of a particular component, the term "axially" refers to a relative direction that is substantially parallel and / or coaxially aligned with the axial centerline of a particular component, and the term "circumferentially" refers to a relative direction that extends around the axial centerline of a particular component. Approximate terms such as "generally," or "about" include values ​​within plus or minus 10 percent of the stated value. When used in the context of an angle or direction, such terms include a range of plus or minus 10 degrees of the stated angle or direction. For example, "generally vertical" includes a direction within 10 degrees of vertical in any direction, e.g., clockwise or counterclockwise.

[0016] Referring now to the drawings, Figure 1 shows a partial cross-sectional view of one embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine 10. Although an industrial or land-based gas turbine is shown and described herein, the present disclosure is not limited to land-based and / or industrial gas turbines unless otherwise stated in the claims. For example, the invention described herein may be used with any type of turbomachine, including, but not limited to, a steam turbine, an aircraft gas turbine, or a marine gas turbine.

[0017] As shown, the illustrated gas turbine 10 is separated at a turbine centerline 12. As shown, the gas turbine 10 includes a compressor section 14, a combustor section 16 disposed downstream from the compressor section 14, and a turbine section 18 disposed downstream from the combustor section 16. The compressor section 14 may generally be configured to compress air entering the gas turbine 10. A portion of the compressed air or working fluid then enters the combustor section 16 where the air is mixed with fuel and combusted. The hot combustion gases then flow along an annular hot gas path through a transition piece 20 to the turbine section 18 to drive the gas turbine 10 to generate power.

[0018] In some embodiments, the compressor section 14 may include an axial compressor 22 having multiple compressor stages characterized by alternating rows of rotor blades 24 and stator vanes 26. Specifically, each compressor stage may include a row of circumferentially spaced rotor blades 24 mounted on a compressor rotor wheel 28 and a row of circumferentially spaced stator vanes 26 mounted on a static compressor casing 30. The alternating rows of rotor blades 24 and stator vanes 26 may generally be configured to progressively increase the pressure of the air flowing through the compressor 22 to enable a desired pressure increase. The compressor rotor wheel 28, together with the rotor blades 24, may generally comprise the rotating components of the compressor 22, thus forming a compressor rotor assembly 32. For example, in some embodiments, the compressor rotor disks 28 may be axially stacked on one another about the turbine centerline 12 such that torque may be transferred between the rotor disks 28.

[0019] The combustion section 16 of the gas turbine 10 may generally include a number of combustors 34 (one of which is shown) arranged in an annular array about the turbine centerline 12. Each combustor 34 may generally be configured to receive a portion of the compressed air discharged from the compressor 22, mix the air with fuel to form an air / fuel mixture, and combust the mixture to generate hot combustion gases. As indicated above, the hot combustion gases may then flow from each combustor 34 through a transition piece 20 to the turbine section 18 of the gas turbine 10.

[0020] The turbine section 18 may generally include multiple turbine stages characterized by alternating rows of turbine nozzles 36 and turbine buckets 38. In particular, each turbine stage may include a row of circumferentially spaced turbine nozzles 36 mounted to a static turbine casing 40 and a row of circumferentially spaced turbine buckets 38 mounted to a turbine rotor wheel 42. The alternating rows of turbine nozzles 36 and buckets 38 may generally be configured to progressively convert energy of hot combustion gases into work generated by rotation of a turbine rotor disk 42. The turbine rotor wheels 42, along with the turbine buckets 38, may generally comprise the rotating components of the turbine section 18 and thus form a turbine rotor assembly 44. Similar to the compressor rotor wheels 28, the turbine rotor wheels 42 may generally be stacked together axially along the turbine centerline 12. 1, the turbine rotor wheels 42 may be spaced apart from one another by spacer wheels 46, where the rotor wheels 42 and spacer wheels 46 are axially stacked together so that torque may be transferred between the rotor disks 42. Spacer wheels may additionally or alternatively space the compressor rotor wheels 28.

[0021] 1, the gas turbine 10 may define an axial direction A and a circumferential direction C extending about the axial direction A. The gas turbine 10 may also define a radial direction R perpendicular to the axial direction A.

[0022] As further shown in FIG. 1 and with reference to FIG. 2 , the gas turbine 10 may further include a compressor shaft 50 at least partially disposed within the compressor section 14 and a turbine shaft 52 at least partially disposed within the turbine section 18. The shafts 50, 52 may couple the compressor rotor assembly 32 and the turbine rotor assembly 44 together. As shown, the compressor shaft 50 may include an aft end 51 that couples to a forward end 53 of the turbine shaft 52. Each shaft 50, 52 may include one or more rabbets, for example, a first rabbet 62 and a second rabbet 64. The first rabbet 62 may be annularly defined within the aft end 51 of the compressor shaft 50. Similarly, the second rabbet 64 may be annularly defined within the forward end 53 of the turbine shaft 52. In many embodiments, the compressor shaft 50 may extend axially outward from the compressor section 14 and terminate at the first rabbet 62 defined within the aft end 51 of the compressor shaft 50. Similarly, the turbine shaft 52 may extend axially inward from the turbine section 18 and terminate in a second rabbet 64 defined in the forward end 53 of the turbine shaft 52. The rabbets 62, 64 may form a marriage joint 58 that couples the compressor rotor assembly 32 to the turbine rotor assembly 44 and functions to maintain coaxial alignment between the compressor shaft 50 and the turbine shaft 52.

[0023] FIG. 2 illustrates a cross-sectional view of a shaft assembly 60 before service maintenance has been performed thereon and before a patch ring 100 (shown in FIGS. 3-8 ) has been installed therein. In various embodiments, the shaft assembly 60 illustrated in FIG. 2 may be before or after operation of the gas turbine 10. As shown, the shaft assembly 60 may include a compressor shaft 50 coupled to a turbine shaft 52 to form a marriage joint 58 therebetween. As shown, the compressor shaft 50 may include a first pre-machined rabbet 54. Similarly, the turbine shaft 52 may include a second pre-machined rabbet 56 opposite the first pre-machined rabbet 54. The first pre-machined rabbet 54 may include a first axially extending surface 55, and the second pre-machined rabbet 56 may include a second axially extending surface 57. As shown, prior to installation of patch ring 100, first axially extending surface 55 of first pre-machined rabbet 54 is in direct contact with second axially extending surface 57 of second pre-machined rabbet 56.

[0024] During disassembly of a turbomachine for maintenance or repair, the turbine shaft 52 is disconnected from the compressor shaft 50 and inspected. The turbine shaft 52 and compressor shaft 50 can be damaged during this process, which can result from operational wear or from the actual disassembly process itself. The first rabbet 62 and the second rabbet 64 (FIG. 1) are common places where this damage can occur.

[0025] 3 and 4 show enlarged cross-sectional views of the shaft assembly 60 with a patch ring 100 in place, for example, after maintenance of the gas turbine 10, according to an embodiment of the present disclosure. As shown, the shaft assemblies 60 may each include a compressor shaft 50, a turbine shaft 52 coupled to the compressor shaft 50, and a marriage joint 58 defined therebetween. The compressor shaft 50 may include a first rabbet 62 annularly defined therein. Similarly, the turbine shaft 52 may include a second rabbet 64 annularly defined therein. For example, the first rabbet 62 and the second rabbet 64 may be machined in the shafts 50, 52 in the circumferential direction C. The patch ring 100 may be disposed between the first rabbet 62 of the compressor shaft 50 and the second rabbet 64 of the turbine shaft 52.

[0026] In many embodiments, the first rabbet 62 may be positioned opposite the second rabbet 64. For example, in the embodiment shown in Figures 3 and 4, the first rabbet 62 of the compressor shaft 50 may be disposed radially inward of the second rabbet 64 of the turbine shaft 52. However, in other embodiments (not shown), the first rabbet 62 of the compressor shaft 50 may be disposed radially outward of the second rabbet 64 of the turbine shaft 52.

[0027] As shown in Figures 3 and 4, the first rabbet 62 may include a first axially extending surface 66 and a first radially extending surface 68. Similarly, the second rabbet 64 may include a second axially extending surface 70 and a second radially extending surface 72. As shown in Figures 3 and 4, the axially extending surfaces 66, 70 and the radially extending surfaces 68, 72 may be substantially flat surfaces. Additionally, as shown, the axially extending surfaces 66, 70 and the radially extending surfaces 68, 72 may be the outermost surfaces of the rabbet 62, 64.

[0028] As used herein, "axially extending" refers to components and / or surfaces that extend along a relative direction that is substantially parallel and / or coaxially aligned with the axial direction A of the gas turbine 10. Similarly, "radially extending" refers to components and / or surfaces that extend along a relative direction that is substantially perpendicular to the axial direction A of the gas turbine 10.

[0029] As shown, the first axially extending surface 66 may be radially spaced from the second axially extending surface 70, and the patch ring 100 may be positioned therebetween. In some embodiments, the patch ring 100 may be mounted between the first rabbet 62 and the second rabbet 64 to advantageously provide a design-required interference between the first axially extending surface 66 and the second axially extending surface 70. Additionally, the patch ring 100 may also reduce or prevent damaging axial movement between the axially extending surfaces 66, 70 during operation of the gas turbine 10.

[0030] In many embodiments, as shown in Figures 3 and 4, the first rabbet 62 and the second rabbet 64 may axially overlap one another. For example, the first radially extending surface 68 of the first rabbet 62 may extend axially beyond the second radially extending surface 72 of the second rabbet 64. Specifically, the first radially extending surface 68 may extend axially outwardly beyond the second radially extending surface 72. In such embodiments, the first axially extending surface 66 may face, overlap, and / or be parallel to the second axially extending surface 70.

[0031] The patch ring 100 may include a body 102, a first arm 104, and a second arm 106. In the embodiment shown in FIGS. 3 and 4, the body 102 of the patch ring 100 may be positioned radially between the first axially extending surface 66 of the compressor shaft 50 and the second axially extending surface 70 of the turbine shaft 52. For example, the body 102 of the patch ring 100 may function to radially space the first axially extending surface 66 of the first rabbet 62 from the second axially extending surface 70 of the second rabbet 64 to provide proper alignment between the compressor shaft 50 and the turbine shaft 52. As shown in FIGS. 3 and 4, the body 102 may be in direct contact with both the first axially extending surface 66 and the second axially extending surface 70.

[0032] In the embodiment shown in FIG. 3, the first arm 104 and the second arm 106 can extend radially away from the body 102. For example, as shown, the first arm 104 can extend radially outward from the body 102 of the patch ring 100, and the second arm 106 can extend radially inward from the body of the patch ring 100. As shown in FIG. 3, the first arm 104 can extend radially outward from the body 102, beyond the second axially extending surface 70, and at least partially along the second radially extending surface 72. Similarly, the second arm 106 can extend radially inward from the body 102, beyond the first axially extending surface 66, and at least partially along the first radially extending surface 68. In many embodiments, the first arm 104 and the second arm 106 can be in direct contact with the second rabbet 64 and the first rabbet 62, respectively.

[0033] 3, the first arm 104 can be axially spaced apart from the second arm 106, i.e., positioned on opposite sides of the body. In some embodiments, the first arm 104 and the second arm 106 can extend in opposite radial directions and on opposite axial sides of the body 102, forming a generally "S"-like shape.

[0034] The first arm 104 and the second arm 106 can each include a bearing surface 108, 110, as shown. For example, the bearing surface 108 of the first arm 104 can be a substantially flat surface in direct contact with the second radially extending surface 72. Similarly, the bearing surface 110 of the second arm 106 can be a substantially flat surface in direct contact with the first radially extending surface 68. For example, the bearing surface 108 of the first arm 108 and the bearing surface 110 of the second arm 106 can be substantially flat surfaces in direct contact with the second radially extending surface 72 and the first radially extending surface 68, respectively. The bearing surfaces 108, 110 of the arms 104, 106 can function to inhibit movement and / or sliding of the patch ring 100 within the marriage joint 58.

[0035] 3, each of the first arm 104 and the second arm 106 may also include an outer surface 112, 114. The outer surface 112 of the first arm may be located axially inward of the support surface 108. Similarly, the outer surface 114 of the second arm may be located axially outward of the support surface 110. As shown, the outer surfaces 112, 114 may be longer in the radial direction than the support surfaces 108, 110.

[0036] As shown in FIGS. 3 and 4 , the first rabbet 62 of the compressor shaft 50 and the second rabbet 64 of the turbine shaft 52 may each further include an outer surface 116, 118. For example, the outer surfaces 116, 118 may be substantially arcuate outer surfaces axially spaced apart from the radially extending surfaces 68, 72 to define gaps 120, 122 therebetween. As shown, the outer surface 116 of the first rabbet 62 may be disposed axially inward of the second radially extending surface 72 to define the gap 120 therebetween. Similarly, the outer surface 118 of the second rabbet 64 may be disposed axially outward of the second radially extending surface 72 to define the gap 122 therebetween. In many embodiments, the first rabbet 62 may extend at least partially into the second gap 122 and the second rabbet 64 may extend at least partially into the first gap 120.

[0037] 3 , the first arm 104 of the patch ring 100 may extend at least partially into the gap 120, and the second arm 106 may extend at least partially into the gap 122. The gaps 120, 122 may serve to provide an axial space between the first arm 104 and the second arm 106 to allow for thermal expansion during operation of the gas turbine 10. The outer surfaces 112, 114 may advantageously act as an interface surface to prevent the outer surfaces 116, 118 from contacting the radially extending surfaces 68, 72 due to thermal expansion during operation of the gas turbine 10.

[0038] 4 illustrates another embodiment of the patch ring 100. As shown, the first arm 104 may be coaxially aligned with the second arm 106, i.e., positioned on the same side of the body 102 and sharing the same axial centerline. In some embodiments, the first arm 104 and the second arm 106 may extend in opposite radial directions from one another, forming a generally "T"-like shape.

[0039] In the embodiment shown in FIG. 4, the second rabbet 64 may further include a radial notch 212 sized to receive the first arm 104 of the patch ring 100 therein. The radial notch 212 may function to limit axial movement of the patch ring 100 within the marriage joint 58. For example, the first arm 104 may be axially positioned between and in contact with the support surface 108 and the outer surface 118 during operation of the gas turbine 10, thereby limiting axial movement of the patch ring 100 within the marriage joint 58. As shown, the radial notch 212 may further include a notch support surface 214. The first arm 104 and the second arm 106 may each include a support surface 108, 110, as shown. In many embodiments, the support surface 108 of the first arm 104 may be a substantially flat surface that directly abuts the notch support surface 214. Similarly, the bearing surface 110 of the second arm 106 can be a substantially flat surface that directly abuts the first radially extending surface 68. The bearing surfaces 108, 110 of the arms 104, 106 can function to inhibit movement and / or sliding of the patch ring 100 within the marriage joint 58.

[0040] 5 and 6 show various views of a patch ring 100 according to an embodiment of the present disclosure. As shown, the first arm 104 and the second arm 106 can each be one continuous annular member extending in a circumferential direction. The first arm 104 and the second arm 106 can be defined along a circumferential direction.

[0041] 7 and 8, the first arm 104 can be a plurality of first arms 104' spaced apart from one another along the body 102 in the circumferential direction C. Similarly, as shown, the second arm 106 can be a plurality of second arms 106' spaced apart from one another along the body 102 in the circumferential direction C.

[0042] As shown in Figures 7 and 8, the patch ring 100 may also include one or more grooves 124 circumferentially disposed between the plurality of first arms 104' and / or the plurality of second arms 106'. The grooves 124 may extend radially into the body 102 of the patch ring 100 and serve as passages for cooling and passing air from the compressor. For example, air from the compressor section 14 may purge stagnant air from the first rabbet 62 of the compressor shaft 50, the second rabbet 64 of the turbine shaft 52, and various cavities and gaps in the patch ring 100.

[0043] FIG. 9 provides a flow chart that graphically illustrates a method 300 of servicing a turbomachine, such as the gas turbine 10 described herein, in accordance with one or more additional exemplary embodiments of the present disclosure. As shown in FIG. 9, the method 300 may include a step 302 of machining a first rabbet 62 in the aft end 51 of the compressor shaft, such a step may occur, for example, after initial operation of the gas turbine 10. The first rabbet 62 may include a first axially extending surface 66 and a first radially extending surface 68. Further, the first rabbet may be annularly defined in the aft end 51 of the compressor shaft 50. The method 300 may further include a step 304 of machining a second rabbet 64 in the forward end 53 of the turbine shaft 52. The second rabbet 64 may include a second axially extending surface 70 and a second radially extending surface 72. Additionally, the second rabbet 64 may be annularly defined within the forward end 53 of the turbine shaft 52 and positioned opposite the first rabbet 62. The method 300 may also include installing 306 a patch ring radially between the first rabbet 62 and the second rabbet 64.

[0044] During operation of the gas turbine 10, the body 102 of the patch ring 100 can function to provide the designed-in interference between the first axially extending surface 66 and the second axially extending surface 70, even after the surfaces have undergone maintenance and / or machining. For example, the pre-machined rabbet 54, 56 shown in FIG. 2 may undergo wear during operation of the gas turbine 10, which requires various surfaces of the pre-machined rabbet 54, 56, e.g., the axially extending surfaces 55, 57, to be maintained to restore the required interference. The patch ring 100 provides the required interference between the rabbet 62, 64 (or the machined rabbet) after the gas turbine 10 has been maintained.

[0045] This specification uses examples to disclose the invention, including the best mode, and to enable any person skilled in the art to practice the invention, including making and using any device or system, 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 include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ insubstantial from the literal language of the claims. [Explanation of symbols]

[0046] 10 Gas Turbines / Turbomachinery 12 Turbine centerline 14 Compressor Section 16 Combustor section / Combustion section 18 Turbine Section 20 Transition Piece 22 Axial flow compressor 24 rotor blades 26 Stator vane 28 Compressor rotor wheel / Compressor rotor disk 30 Static compressor casing 32 Compressor rotor assembly 34 Combustor 36 Turbine Nozzle 38 Turbine bucket 40 Static Turbine Casing 42 Turbine rotor wheel / Turbine rotor disk 44 Turbine rotor assembly 46 Spacer wheel 50 Compressor shaft 51 Rear end 52 Turbine shaft 53 Front end 54 First pre-machined rabbet 55 first axially extending surface 56 Second pre-machined rabbet 57 second axially extending surface 58 Marriage Joint 60 Shaft Assembly 62 The First Lovett 64 The Second Lovett 66 first axially extending surface 68 first radially extending surface 70 second axially extending surface 72 second radially extending surface 100 Patch Ring 102 Main unit 104 First Arm 104' First Arm 106 Second Arm 106' Second Arm 108 Support surface 110 Support surface 112 Exterior 114 Exterior 116 External surface 118 External surface 120 First Gap 122 The Second Gap 124 Groove 212 Radial notch 214 Notched support surface 300 ways 302 Steps 304 Steps 306 Steps A axis direction C Circumferential direction R Radial direction

Claims

1. A turbomachine (10), comprising: A compressor section (14); a combustor section (16); A turbine section (18); a compressor shaft (50) at least partially disposed in the compressor section (14), the compressor shaft (50) having a first rabbet (62) annularly defined therein, the first rabbet (62) including a first axially extending surface (66) and a first radially extending surface (68); a turbine shaft (52) disposed at least partially in the turbine section (18) and coupled to the compressor shaft (50), the turbine shaft (52) having a second rabbet (64) defined annularly therein and positioned opposite the first rabbet (62), the second rabbet (64) including a second axially extending surface (70) and a second radially extending surface (72); a patch ring (100) mounted between the first rabbet (62) and the second rabbet (64); the patch ring (100) further includes a body (102), a first arm (104) extending radially outward from the body (102), and a second arm (106) extending radially inward from the body (102).

2. The turbomachine (10) of claim 1, wherein the first arm (104) and the second arm (106) of the patch ring (100) are axially spaced apart from one another.

3. The turbomachine (10) of claim 1, wherein the first arm (104) and the second arm (106) of the patch ring (100) are coaxially aligned with one another.

4. 2. The turbomachine of claim 1, wherein the body of the patch ring contacts the first axially extending surface of the compressor shaft and the second axially extending surface of the turbine shaft.

5. 2. The turbomachine of claim 1, wherein the body of the patch ring is positioned radially between the first axially extending surface and the second axially extending surface.

6. 3. The turbomachine (10) of claim 2, wherein the first rabbet (62) of the compressor shaft (50) and the second rabbet (64) of the turbine shaft (52) each include an outer surface (116, 118), the outer surface (116) of the first rabbet (62) being disposed axially inward of the second radially extending surface (72) of the second rabbet (64) and the outer surface (118) of the second rabbet (64) being disposed axially outward of the first radially extending surface (68) of the first rabbet (62).

7. 3. The turbomachine (10) of claim 2, wherein the first arm (104) of the patch ring (100) contacts the second radially extending surface (72) of the second rabbet (64) and the second arm (106) of the patch ring (100) contacts the first radially extending surface (68) of the first rabbet (62).

8. 7. The turbomachine (10) of claim 6, wherein a first gap (120) is defined axially between the first arm (104) of the patch ring (100) and the outer surface (116) of the first rabbet (62), and a second gap (122) is defined axially between the second arm (106) of the patch ring (100) and the outer surface (118) of the second rabbet (64).

9. A method (300) of servicing a turbomachine (10), the method comprising: a step (302) of machining a first rabbet (62) in an aft end (51) of a compressor shaft (50), said first rabbet (62) including a first axially extending surface (66) and a first radially extending surface (68), said first rabbet (62) being annularly defined in said aft end (51) of said compressor shaft (50); machining (304) a second rabbet (64) in a forward end (53) of a turbine shaft (52), the second rabbet (64) including a second axially extending surface (70) and a second radially extending surface (72), the second rabbet (64) being annularly defined in the forward end (53) of the turbine shaft (52) and positioned opposite the first rabbet (62); placing (306) a patch ring (100) between the first rabbet (62) and the second rabbet (64); wherein the patch ring (100) further comprises a body (102), a first arm (104) extending radially outward from the body (102), and a second arm (106) extending radially inward from the body (102).

10. The method of claim 9, wherein the first arm (104) and the second arm (106) of the patch ring (100) are axially spaced apart from one another.

11. 10. The method (300) of claim 9, wherein the body (102) of the patch ring (100) is positioned between and in contact with the first axially extending surface (66) of the compressor shaft (50) and the second axially extending surface (70) of the turbine shaft (52).

12. 11. The method (300) of claim 10, wherein the first arm (104) of the patch ring (100) contacts the second radially extending surface (72) of the second rabbet (64) and the second arm (106) of the patch ring (100) contacts the first radially extending surface (68) of the first rabbet (62).

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