JP6956511B2 - Systems and methods for diffuser rear plate assembly - Google Patents

Description

The subject matter disclosed herein relates to gas turbine engines such as an improved diffuser section.

Gas turbine systems generally include a compressor, a combustor, and a turbine. The compressor compresses the air from the air intake and then directs the compressed air to the combustor. The combustor burns a mixture of compressed air and fuel and produces high temperature combustion gas that is led to a turbine to perform tasks such as driving a generator.

The conventional diffuser section of a turbine is subject to high stress due to the structure of the diffuser section and the high temperatures associated with the exhaust gas. Therefore, conventional diffuser sections are subject to high stress, which increases wear on the diffuser section.

U.S. Patent Application Publication No. 2012/0063893

In one embodiment, the method comprises axially inserting the radial inner surface of the rear plate assembly into the circumferential groove of the inner barrel of the diffuser section of the gas turbine, the rear plate assembly relative to the circumferential groove. Inserted in a first circumferential orientation, the circumferential groove is located on the radial outer surface of the inner barrel. The method comprises rotating the rear plate assembly circumferentially in the circumferential groove from a first circumferential orientation to a second circumferential orientation, and the inner barrel has the rear plate assembly in a second circumferential orientation. It is configured to hold the rear plate assembly axially when placed.

In one embodiment, the system includes a diffuser section configured to receive exhaust gas from the turbine section, the diffuser section includes a rear plate assembly that includes a radial inner surface, and the radial inner surface is a first. Includes a notch and a first ridge. The diffuser section includes an inner barrel containing a circumferential groove located on the outer surface in the radial direction, and the circumferential groove includes an upstream lip and a downstream lip containing a second notch and a second ridge. including. The first ridge is configured to be placed in the circumferential groove when the rear plate assembly is placed in the first circumferential orientation and the second circumferential orientation with respect to the inner barrel. The ridge is axially aligned with the second notch in the first circumferential orientation, and the first ridge is circumferentially offset from the second notch in the second circumferential orientation. Will be done.

In one embodiment, the system includes a diffuser section configured to receive exhaust gas from the turbine section, the diffuser section including a front plate and a rear plate assembly that includes a radial inner surface, radially inside. The surface includes a first plurality of notches and a first plurality of ridges. The diffuser section includes an inner barrel containing a circumferential groove located on the outer surface in the radial direction, and the circumferential groove includes an upstream lip and a second notch and a second ridge. Includes downstream lip. The diffuser section includes a plurality of poles that are coupled between the anterior plate and the rear plate assembly when the rear plate assembly is placed in a second circumferential orientation with respect to the inner barrel, and a first plurality of ridges. The portions are configured to be arranged in the circumferential groove when the rear plate assembly is arranged in the first circumferential orientation and the second circumferential orientation with respect to the inner barrel, and the first plurality of ridges. Is axially aligned with the second plurality of notches in the first circumferential orientation, and the first plurality of ridges are from the second plurality of notches in the second circumferential orientation. It is offset in the circumferential direction.

These and other features, embodiments and advantages of the present invention should be better understood when deciphering the following detailed description with reference to the accompanying drawings, throughout which the same reference numerals represent the same parts.

FIG. 6 is a block diagram of an embodiment of a turbine system having a turbine including a modified diffuser section. It is a detailed view of the diffuser section of a turbine arranged in an exhaust plenum. It is a figure which shows the modified upper part of a diffuser. FIG. 5 is a cross-sectional view of a diffuser taken through a bracket along line 4-4 of FIG. It is a perspective view of the lap joint and the individual bracket along the line 5-5 of FIG. It is a perspective view of the lap joint and the individual bracket along the line 5-5 of FIG. 2 is an axial cross-sectional view of a circumferential groove in the inner barrel of the diffuser of FIGS. 2 and 3. FIG. 7 is an axial view of an embodiment of a rear plate assembly along line 8-8 of the diffuser of FIG. It is a partial cross-sectional view of a rear plate assembly. FIG. 6 is an axial view of an embodiment of the rear plate of the inner barrel along line 8-8 of the diffuser of FIG. FIG. 7 is an axial view of an embodiment of the rear plate assembly of the inner barrel along line 8-8 of the diffuser of FIG. It is a figure explaining the method of forming the rear plate segment by one Embodiment of this disclosure. It is a side view of one Embodiment of an outer barrel. It is a side view of the inner barrel. 13 is a diagram illustrating an exemplary device used to machine an inner barrel and an outer barrel into a desired continuous bend, as described in FIGS. 13 and 14. It is a figure which shows the method of forming the inner barrel and the outer barrel by a spinning process.

The system and method for improving the conventional diffuser section by utilizing the mechanical improvement of the diffuser section will be described in detail below. Mechanical improvements to the diffuser section contribute to the improved mechanical integrity of the diffuser by reducing the stress associated with traditional diffuser designs. Mechanical improvements to the diffuser include a rear plate assembly with notches and ridges to facilitate axial installation of the rear plate on the inner barrel. The rear plate can be inserted axially through the notch in the circumferential groove of the inner barrel of the diffuser section, and then circumferentially so that the ridges of the rear plate hold the rear plate assembly axially. It rotates in the circumferential direction in the groove. Other mechanical improvements were to make the desired bends in the diffuser section, to place multiple poles between the front and rear plates of the diffuser, and to be placed in the inner barrel to accommodate the rear plate. Circumferential grooves, circumferential lap joints on the outer barrel, multiple individual brackets located along the inner and / or outer barrel of the diffuser configured to connect the diffuser to the turbine outlet, or any combination thereof. including. The curved portion of the diffuser section is provided by mechanical processing such as a spinning step. The spinning process involves forming the appropriate material (eg, stainless steel, metal) to give the inner and outer barrels the desired shape (eg, curvature) by placing the material in a mold. Next, the material is formed into a desired shape by pushing the material into the mold using a roller and gradually forming a desired mold shape. In order to reduce the residual stress encountered by the spinning process, the inner and outer barrels may be formed from various axial segments (eg, first plurality of axial segments, second plurality of axial segments). good. Utilizing axial segments to form the inner and outer barrels reduces the deformation of the material to form the desired shape of the inner and outer barrels, thereby reducing the amount of residual stress generated. Can contribute to.

Once the inner and outer barrel axial segments (eg, first plurality of axial segments, second plurality of axial segments) are formed, the axial segments of each barrel join together. be able to. Axial segments are such that the axial segments (eg, the first plurality of axial segments, the second plurality of axial segments) have extra material so that the segments can be properly joined together. Can be disconnected. Axial segments can be joined together by welding, brazing, fusion, bolting, fastening, or any combination thereof.

The poles are placed between the inner and outer barrels and then around the turbine axis. The poles serve to connect the downstream end of the rear plate to the downstream end of the front plate via a plurality of poles and are arranged around the turbine axis at a circumferential distance. In some embodiments, the poles have different pole diameters. The pole diameter is based in part on the circumferential position of the pole position along the diffuser (eg, outer rear plate, inner rear plate). For example, the diameter of the pole closest to the top of the diffuser (eg, outer rear plate, inner rear plate) can have a larger diameter than the pole closest to the bottom of the diffuser. In some embodiments, the pole diameter is smaller due to its proximity to the exhaust gas flow. Therefore, a small pole diameter can be beneficial by reducing blockage of the exhaust flow path due to the small diameter. A pole located within the top of the diffuser section can be configured to support the load (eg, weight) of the diffuser section, such as during installation. For example, a pole located within the top of the diffuser section may be used to lift the diffuser section. In some embodiments, poles located within the top of the diffuser section hoists, lifts, cranes to move the diffuser section to the proper position (eg, migration for installation, removal, inspection, repair). , Or can be combined with other suitable lifters. The pole can reduce the vibration between the inner barrel and the outer barrel. The placement of the poles depends in part on the diameter of the poles. The pole closest to the top of the diffuser has a larger diameter to bypass the vortex emission frequency, which makes the exhaust gas velocity more uniform.

The circumferential groove is located at the end of the inner barrel. The rear plate can be inserted into the circumferential groove so as to be connected to the root portion of the circumferential groove. The circumferential groove can reduce stress by allowing the rear plate to move within the circumferential groove. Hoop stress can be reduced in the region by allowing slight movement between sections (eg, rear plate and circumferential groove). The stress reduction by providing the circumferential groove can reduce the hoop stress by about half as compared with the diffuser without the circumferential groove. In some embodiments, the posterior plate can be formed as a posterior plate assembly. For example, the rear plate assembly may include multiple rear plate segments arranged to form an annular rear plate assembly. The rear plate assembly can include multiple notches and ridges. The rear plate segment allows a portion of the exhaust gas to leak into the exhaust plenum through an opening (eg, a ridge). This leak can reduce the amount of thermal stress in the region by allowing a controlled leak of hot exhaust gas to pass through the opening. The rear plate assembly can be axially inserted in a first circumferential orientation with respect to the circumferential groove. The rear plate assembly can rotate circumferentially in the circumferential groove from a first circumferential orientation to a second circumferential orientation. The inner barrel can consist of ridges and notches to hold the rear plate assembly axially when the rear plate assembly is placed in a second circumferential orientation.

The circumferential lap joint is located between the downstream end of the outer wall of the turbine outlet and the upstream end of the outer barrel of the diffuser section. The circumferential lap joint is configured to facilitate axial movement of the outer barrel with respect to the outer wall, thereby relieving stress on the outer barrel. The upstream lip of the outer barrel (eg, the outer lip) can be radially placed within the downstream lip (eg, lip) of the outer wall to facilitate axial movement of the lap joint. The stress reduction due to the use of the upstream and downstream lips of the circumferential lap joint can be further enhanced by the use of individual brackets. The individual brackets can be coupled to the outer barrel and frame assembly (eg, the exhaust frame). Individual brackets (eg, individual brackets for the outer barrel) are configured to axially support the outer barrel. A subset of the individual brackets (eg, the individual inner brackets) can be arranged circumferentially around the inner barrel of the diffuser. Individual inner brackets (eg, inner barrel support brackets) can hold the diffuser (eg, inner barrel) in place and reduce axial movement. The movement of the diffuser (eg, inner and outer barrels) with respect to the turbine outlet can be reduced and / or constrained depending on where the lap joints and individual brackets are located along the outer barrel.

Next, moving to the drawing and first referring to FIG. 1, a block diagram of an embodiment of the gas turbine system 10 is shown. This figure includes a fuel nozzle 12, a fuel 14, and a combustor 16. As shown, the fuel 14 (eg, a gas fuel such as liquid fuel and / or natural gas) is sent through the fuel nozzle 12 to the turbine system 10 and into the combustor 16. The combustor 16 ignites the air-fuel mixture 34 to burn it, and then sends the high temperature pressurized exhaust gas 36 into the turbine 18. The exhaust gas 36 passes through the turbine blades of the turbine rotor of the turbine 18, thereby driving the turbine 18 to rotate about the shaft 28. In one embodiment, the modified diffuser 38 is coupled to the turbine 18. The turbine 18 is coupled to the turbine outlet, and the turbine outlet and diffuser 38 are configured to receive the exhaust gas 36 from the turbine 18 during operation. As discussed in detail below, embodiments of the turbine system 10 include specific structures and components within the diffuser 38 that improve the reliability associated with the manufacture of the diffuser 38 (eg, by reducing stress). include. Embodiments of the turbine system 10 may include specific structures and components of the diffuser 38 to improve the manufacturing time of the diffuser 38. Exhaust gas 36 in the combustion process can exit the turbine system 10 via the diffuser 38 and the exhaust outlet 20. In some embodiments, the diffuser 38 is disposed between the circumferential groove 40, one or more lap joints 42, one or more individual brackets 44, the rear plate 62 and the front plate 64 of the diffuser 38. It may include one or more poles 46, or any combination thereof. The rotating blades of the turbine 18 rotate the shaft 28 coupled to some other component (eg, compressor 22, load 26) throughout the turbine system 10.

In one embodiment of the turbine system 10, a compressor vane or blade is included as a component of the compressor 22. The blades in the compressor 22 can be coupled to the shaft 28 by the compressor rotor and rotate when the shaft 28 is driven by the turbine 18. The compressor 22 can take the oxidant (eg, air) 30 into the turbine system 10 via the air intake 24. Further, the shaft 28 may be coupled to the load 26, which may be powered by the rotation of the shaft 28. As will be appreciated, the load 26 may be any suitable device that produces power from the rotational output of the turbine system 10, such as a power plant or an external mechanical load. For example, the load 26 may include an external mechanical load such as a generator. The air intake 24 later introduces an oxidant (eg, air) 30 into the turbine system 10 via an appropriate mechanism such as a cold air intake to mix the air 30 with the fuel 14 via the fuel nozzle 12. Pull in. The oxidant (eg, air) 30 taken up by the turbine system 10 can be supplied by a rotating blade in the compressor 22 and compressed into pressurized air 32. The pressurized air 32 may then be supplied into one or more fuel nozzles 12. The fuel nozzle 12 can then mix the pressurized air 32 and the fuel 14 to generate an appropriate air-fuel mixture 34 for combustion.

FIG. 2 shows a detailed view of the diffuser 38 section of turbine 18. As shown, the diffuser section 38 can include an upper portion 52 and a lower portion 54 that are shown as being separated by a ventilation bearing tunnel 56. The ventilation bearing tunnel 56 can supply a cooling stream through the turbine outlet 20 and the diffuser section 38. It will be appreciated that the diffuser 38 has a substantially annular shape surrounding a portion of the bearing tunnel 56. The upper portion 52 of the diffuser 38 is coupled to the exhaust frame 58 and is arranged radially within the exhaust plenum 60. Exhaust gas 36 exits through the upper and lower sections 52, 54 of the diffuser 38 and enters the exhaust plenum 60. The rear plate 62 of the diffuser section 38 is also located at the plenum 60. The inner barrel 48 may be cooler than the outer barrel 50, especially along a portion of the inner barrel 48 that is partially separated from the turbine outlet 20 by the insulator applied to the inner barrel 48. Therefore, the rear plate 62 can absorb heat more quickly than the inner barrel 48, which contributes to the thermal gradient over the diffuser 38. This thermal gradient creates stress on the diffuser 38, which can affect the mechanical integrity of the diffuser 38.

The mechanical integrity of the diffuser 38 may also be affected by stresses related to the damping length from the diffuser 38 of the exhaust frame 58 and the airfoil 82 located within the longitudinal joints 74. The flow path of the hot exhaust gas 36 can further reduce the mechanical integrity of the diffuser 38 due to the effects of vibrational forces and temperature that fatigue the diffuser 38. Therefore, modifications to the diffuser 38 section described in more detail in the description of FIG. 3 can reduce these effects of the diffuser 38. Such modifications are to produce the desired curvature of the diffuser 38 section, to place a plurality of poles 46 between the front plate 64 and the rear plate 62 of the diffuser 38, and to accommodate the rear plate 62 inside. Circumferential grooves 40 arranged in barrel 48, one or more circumferential lap joints 42, arranged along the inner and outer barrels 50 of the diffuser 38 configured to couple the diffuser 38 to the exhaust frame 58. Includes a plurality of individual brackets 44, or any combination thereof. The circumferential lap joint 42 and the individual bracket 44 have specific directions (for example, circumferential 66, axial direction 76, longitudinal direction 78, lateral direction) depending on the situation in which the circumferential lap joint 42 and the individual bracket 44 are arranged. 80) is configured to reduce or facilitate movement (eg, circumferential 66, axial 76, longitudinal 78, lateral 80, radial 84).

FIG. 3 shows a modified upper portion 52 of the diffuser 38 according to the present disclosure. The diffuser 38 section can be manufactured such that the diffuser 38 begins to bend along the inner and outer barrels 50 of the diffuser 38 at the end closest to the turbine outlet 20. The curved portion 88 of the diffuser 38 can provide structural advantages over other diffuser shapes (eg, more linear diffusers). For example, the continuous bend 88 of the diffuser 38 can reduce the stress structurally generated by improving the aerodynamic properties of the diffuser 38 as compared to bringing it closer to the desired bend on a linear plate. can. As discussed in detail below, the curved portion of the diffuser 38 can be formed by a suitable step, such as a spinning step. In some embodiments, each of the inner barrel 48 and the outer barrel 50 of the diffuser 38 is formed from two or more cones. The cone can be an annular sheet made of a suitable material, as described in connection with FIG. For example, the inner barrel 48 may include two, three, or more conical parts. The outer barrel 50 may include two, three, four, five or more conical parts. The conical part will then undergo a spinning step to form the desired curve of the conical part. Each conical component is then integrally joined together (eg, by welding) to form an integral diffuser 38 section, as further described in connection with FIG. Both the inner barrel 48 and the outer barrel 50 conical components may be formed by a spinning process. The inner barrel 48 and the outer barrel 50 may be separate parts that can be joined together via the pole 46.

The correction part of the other turbine is arranged on the downstream side 104 of the curved portion of the diffuser 38. For example, the plurality of poles 46 may be arranged in the circumferential direction 66 between the front plate 64 and the rear plate 62 of the diffuser 38. The pole 46 can be coupled to the front plate 64 and the rear plate 62 by a plurality of gussets 68 to secure the pole 46 to the front plate 64 and the rear plate 62. The pole 46 is arranged in the circumferential direction 66 between the front plate 64 and the rear plate 62. The pole 46 can serve to reduce the vibrational behavior between the front plate 64 and the rear plate 62. The pole 46 can reduce the tendency of unwanted vibrations by reinforcing the front plate 64 and the rear plate 62, thereby reducing resonance during operation of the gas turbine 18. The pole 46 may have a different diameter 70 to adapt to the flow of exhaust gas 36. For example, the bottom of the diffuser outlet, the region of the diffuser outlet closest to the inner portion, comprises a pole 46 having a smaller diameter 70 that minimizes blockage of the exhaust gas 36.

Further, the downstream side 104 of the curved portion of the diffuser 38 is a circumferential groove 40. The circumferential groove 40 is arranged in the inner barrel 48. In some embodiments, the circumferential groove 40 may be located in the inner barrel 48 to receive the rear plate 62. The circumferential groove 40 can reduce stress in the region (eg, hoop stress) that can occur due to large temperature changes. As described above, the rear plate 62 is arranged in the exhaust plenum 60 so as to be exposed to substantially the same operating temperature as the front plate 64. The hub of the inner barrel 48 may be separated such that a portion of the inner barrel 48 is exposed to a lower operating temperature than the rear plate 62, thereby creating a large thermal gradient across the inner barrel 48 and the rear plate 62. Therefore, the resulting thermal gradient can create stress in the region due to thermal expansion of the inner barrel 48. The circumferential groove 40 can reduce stress by allowing the conical plate 72 of the rear plate 62 to move within the circumferential groove 40. Hoop stress can be reduced in the region by allowing slight radial movement between sections (eg, conical plate 72 and circumferential groove 40). As will be described in detail below, the stress reduction by providing the circumferential groove 40 can reduce the hoop stress by about half of the stress received by the conventional diffuser without the circumferential groove 40.

The arrangement of the lap joint 42 and the individual bracket 44 can be partially defined by a damping length of 100. The damping length 100 is partially defined by a plurality of airfoil portions 82 located within the turbine outlet 20. The airfoil portion 82 is arranged between the outer wall 106 of the turbine outlet 20 close to the downstream 104 end of the turbine outlet 20 and the inner wall 112 of the turbine outlet 20. If the damping length 100 from the airfoil portion 82 to the vertical joint 74 is short, the stress of the vertical joint 74 may be increased as compared with other configurations when the damping length 100 is long. The damping length 100 can help define the position where the circumferential lap joint 42 is located. For example, the lap joint 42 may be arranged at a distance substantially equal to the damping length 100 on the downstream side of the airfoil portion 82. In some embodiments, the damping length 100 is less than about 12 inches. The individual bracket 44 may reduce the movement of the diffuser 38 so that the movement in the axial direction 76, the longitudinal direction 78, and the lateral direction 80 is restricted depending on where the individual bracket 44 is located in the diffuser 38. can. As described in detail below, the individual brackets 44 arranged along the inner barrel 48 and the outer barrel 50 are oriented differently to hold the rear and front plates 64 of the diffuser 38 in place. Can be done.

Next, referring to the inner barrel 48, the upstream end 102 of the inner barrel 48 of the diffuser 38 section can be coupled to the downstream end 104 of the inner wall 112 of the turbine outlet 20 by the inner circumferential joint 114. The medial circumferential joint 114 may include a plurality of individual brackets (eg, bracket 47). The individual bracket is configured to connect the downstream end 104 of the inner wall 112 of the turbine outlet 20 to the upstream end 102 of the inner barrel 48. The inner individual bracket 47 is configured to support the inner barrel 48 in the axial direction 76.

In the inner barrel 48, a secondary flexible seal 101 (eg, a second circumferential seal) can be placed in the opening in the secondary flexible seal groove 102. The secondary flexible seal 101 can block the high temperature exhaust gas 36 from entering the ventilation bearing tunnel 56. The secondary flexible seal 101 may include one or more plate segments segmented in the circumferential direction for a 360 degree structure that can be bolted to the first end 103. Similar to the flexible seal 92 of the outer barrel 50, the secondary flexible seal 101 allows the secondary flexible seal 101 to move freely within the opening of the secondary flexible seal groove 102. It may be cut off on the opposite side of the first end 103.

FIG. 4 shows a cross-sectional view of the diffuser 38 taken through the bracket 44 along line 4-4 of FIG. The bend of the diffuser 38 can start after the portion of the diffuser 38 (eg, downstream) where the lap joint 42 and the individual brackets 44 are located. As described above, the lap joint 42 and the individual bracket 44 can be arranged around the outer barrel 50 of the diffuser 38 in the circumferential direction 66. The individual bracket 44 can be coupled to the outer barrel 50 and the frame assembly (eg, the exhaust frame 58). The individual bracket 44 (eg, the outer individual bracket 45) is configured to support the outer barrel 50 in the axial direction 76 and the circumferential direction 66.

Another set of individual brackets 44 can be arranged circumferentially 66 within the inner barrel 48 of the diffuser 38. For example, a subset of the individual brackets 44 can include a plurality of support brackets (eg, inner individual brackets 47). The inner individual bracket 47 can provide vertical 78 and / or lateral 80 support for the inner barrel 48 with respect to the turbine outlet 20. Both the outer individual bracket 45 and the inner individual bracket 47 may be arranged around the outer barrel 50 in a rotationally symmetrical arrangement.

The inner barrel 48 is exposed to a cooling stream flowing through the ventilation bearing tunnel 56. Thus, the inner individual bracket 47 located within the inner barrel 48 may be formed of a material that maintains yield strength at lower temperatures (eg, compared to the higher temperatures of the outer barrel 50). The individual bracket 44 (eg, the inner individual bracket 47) can hold the diffuser (eg, the inner barrel 48) in place and reduce axial 76 and / or lateral 80 movement. The inner barrel 48 includes a bolted joint at one end 49 to allow the diffuser 38 section (eg, the rear plate 62 of the diffuser and the front plate 64 of the diffuser) to be secured to the turbine outlet 20. The individual bracket 44 and the support pair of relay blocks (see FIG. 6) allow thermal growth in the radial direction 84.

The individual bracket 44 can be coupled to the outer barrel 50 and the inner barrel 48 at various positions. In some embodiments, the individual bracket 44 can be located at 12 o'clock position 118, 3 o'clock position 120, 6 o'clock position 122, 9 o'clock position 124, or any combination thereof. In some embodiments, the individual brackets 44 are placed in other positions (eg, 4 o'clock, 7 o'clock) so that the arrangement of the individual brackets 44 remains discrete (eg, non-continuous). May be good. Further, the position of the individual bracket 44 can be arranged according to the desired constraints of the outer barrel 50 and the inner barrel 48. In other words, the plurality of outer individual brackets 45 and the plurality of inner individual brackets 47 are arranged around the turbine axis 76 at intervals in the circumferential direction 66. The outer individual bracket 45 arranges the outer barrel 50 with respect to the outer wall 106 of the turbine outlet 20 and forms a circumferential lap joint 42 between the outer wall 106 of the turbine outlet 20 and the outer barrel 50 of the diffuser section 38. It is configured as follows. The circumferential lap joint 42 is continuous. The movement of the diffuser 38 (eg, the inner barrel 48 and the outer barrel 50) with respect to the turbine outlet 20 may be reduced and / or constrained depending on where the lap joint 42 and the individual bracket 44 are located along the outer barrel 50. .. For example, if the individual brackets 44 are placed at 3 o'clock position 120 and / or 9 o'clock position 124, the diffuser 38 (eg, inner barrel 48 and outer barrel 50) is constrained in axial 76 and longitudinal 78. For example, if the individual brackets 44 are placed at 12 o'clock position 118 and / or 6 o'clock position 122, the diffuser 38 (eg, inner barrel 48 and outer barrel 50) is constrained to axial 76 and lateral 80. The individual brackets 44 can be supported by support components (eg, pins) as further described in FIG. The support component can limit its movement in the circumferential direction 66.

FIG. 5 shows a perspective view of the lap joint 42 and the individual bracket 44 along line 5-5 of FIG. As mentioned above, the individual bracket 44 can be coupled to the outer barrel 50 and the frame assembly 58 (eg, diffuser frame 116). The individual bracket 44 is configured to support the outer barrel 50 in the axial direction 76, and at least a portion of the individual bracket 44 supports the outer barrel in the circumferential direction 66.

The circumferential lap joint 42 is located between the downstream end 104 of the outer wall 106 of the turbine outlet 20 and the upstream end 102 of the outer barrel 50 of the diffuser 38 section. The circumferential lap joint 42 is configured to facilitate axial movement of the outer barrel 50 with respect to the outer wall 106 of the turbine outlet 20, thereby relieving stress on the outer barrel 50. The upstream lip (eg, outer lip 96) of the outer barrel 50 is arranged radially 84 within the downstream lip (eg, lip 128) of the outer wall 106 to facilitate movement of the lap joint 42. The stress reduction due to the use of the upstream and downstream lips is further enhanced by the use of the individual bracket 44. The outer individual bracket 45 limits heat transfer from the exhaust frame 58 to the outer barrel 50. Therefore, thermal expansion and contraction are likely to occur at fewer locations than the continuous bracket interface, and thermal stress is primarily controlled by the bracket 45. For example, the diffuser 38 section may include a plurality of individual brackets 44 arranged along the outer barrel 50 (eg, outer individual brackets 45) of the diffuser 38 to reduce stress in the longitudinal joints 74 of the exhaust frame 58. can.

In some embodiments, the flexible seal 92 may be utilized in the lap joint 42 and individual bracket 44 assemblies. The flexible seal 92 can be placed in close proximity to the upstream lip 96 of the outer barrel 50. The flexible seal 92 can be placed between the insulator 126 arranged around the individual bracket 44 and the flexible seal groove 94 on the outer wall 106 of the turbine outlet 20. The flexible seal 92 may include one or more plate segments segmented in the circumferential direction for a 360 degree structure that can be bolted or fastened to the first end 93. The flexible seal 92 is free to move within the flexible seal groove 94 and is opposite to the flexible seal 92 and the bolted end (eg, the first end 93 of the flexible seal 92). It may remain detached on the opposite side of the first end 93 (eg, unbolted) so that the clearance space 95 between it and the side end can be sealed. The flexible seal 92 can prevent the cooling stream from flowing into the diffuser 38 along the outer surface of the turbine outlet 20 (eg, for clearance control). The slot 98 between the outer wall 106 of the turbine outlet 20 and the outer lip 96 of the outer barrel 50 can facilitate some degree of axial movement of the lap joint 42. The lip 96 can be connected to the outer lip 128 of the lap joint 42 in the radial direction 84.

As described above, the hot exhaust gas 36 flowing through the turbine 18 and the diffuser 38 is accepted by the exhaust plenum 60. The flexible seal 92 can separate the high temperature exhaust gas 36 and the cooling stream (for example, at the exhaust frame) on the downstream side 104 of the flexible seal 92. The primary flow path 130 can extend from the turbine outlet 20 to the diffuser outlet of the diffuser 38 section through the internal region 134 of the diffuser 38. The inner region 134 exists radially 84 within the outer wall 106 and the outer barrel 50 between the outer barrel 50 and the inner barrel 48. The diffuser outlet is configured to guide the exhaust stream 36 to the exhaust plenum 60. The secondary flow path 136 can extend from the exhaust plenum 60 to the internal region 134 through slot 98 between the downstream lip 128 of the outer wall 106 and the upstream lip 96 of the outer barrel 50. The secondary flow path 136 can extend through the circumferential lap joint 42. In some embodiments, the secondary flow path 136 may include a non-zero portion of the exhaust flow 36 of the internal region 134.

FIG. 6 shows a perspective view of the lap joint 42 and the individual bracket 44 along line 5-5 of FIG. In some embodiments, the individual bracket 44 may be supported by a pin 86, a flange 116, and a pair of relay blocks 90 that extend axially 76 through the flange 116 of the outer barrel 50. The pin 86 can be arranged to support the individual bracket 44 through the flange 116 and the relay block 90. The pins 86 are configured to allow the outer barrel 50 to move (eg, by sliding) in the radial direction 84 with respect to each bracket 44. As mentioned above, the plurality of outer individual brackets 45 include a plurality of circumferential support brackets 44 (eg, a subset of the plurality of individual brackets). Each support bracket 44 of the plurality of individual outer brackets 45 utilizes a pin 86 to allow the outer barrel 50 to move in the radial direction 84 with respect to each support bracket 45. The relay block 90 and the support bracket 47 limit the movement in the circumferential direction 66.

Similar to the individual outer brackets 44, the plurality of inner individual brackets 47 each utilize their respective pins 86 to extend axially 76 through the respective flanges of the inner sidewall 112 and the inner barrel 48. A directional support bracket can be included. The pin 86 is configured to allow the inner barrel 48 to move in the radial direction 84 for each inner support bracket while limiting its movement in the circumferential direction 66.

FIG. 7 shows an axial cross-sectional view of the circumferential groove 40 in the inner barrel 48 of the diffuser 38 of FIGS. 2 and 3. The rear plate 62 is connected to the inner barrel 48 of the diffuser 38 by a circumferential groove 40. As mentioned above, the inner barrel 48 and the outer barrel 50 are arranged around the turbine axis 76. The rear plate 62 is located at least partially within the exhaust plenum 60 and is located downstream 104 of the inner barrel 48.

The circumferential groove 40 can reduce stress in the region (eg, hoop stress) that can occur due to a large thermal gradient. The rear plate 62 and the front plate 64 are at least partially located within the exhaust plenum 60. The hub of the inner barrel 48 may be separated to be exposed to a lower operating temperature than the rear plate 62, thereby providing different temperatures for the rear plate 62 and the hub of the inner barrel 48. The temperature difference between the rear plate 62 and the hub of the inner barrel 48 creates a large thermal gradient across the hub of the inner barrel 48 and the rear plate 62. The resulting thermal gradient creates stress in the region due to thermal expansion / contraction. Hoop stress can be reduced in the region by allowing slight movement (ie, upstream movement, downstream movement) between sections (eg, conical plate 72 and circumferential groove 40). The stress reduction by providing the circumferential groove 40 can reduce the hoop stress by about half. For example, the stress in the region of the rear plate 62 can be reduced from about 413 MPa when the circumferential groove 40 is present in the inner barrel 48 to about 207 MPa when the circumferential groove 40 is not present in the inner barrel 48.

The sealing interface 140 located at the downstream 104 end of the inner barrel 48 and the rear plate 62 includes a circumferential groove 40. In some embodiments, the seal interface 140 is mechanically coupled (eg, welded, fused, brazed, bolted, fastened) to the downstream end 104 of the inner barrel 48. In some embodiments, the seal interface 140 is formed at the downstream end of the inner barrel 48. The seal interface 140 can include a first circumferential groove 142 and a second circumferential groove 144. The first circumferential groove 142 is configured to receive the rear plate 62. Therefore, the first circumferential groove 142 opens in the first direction 146 (for example, downstream side 104) away from the turbine axis 76. The secondary flexible seal 101 is configured to isolate the exhaust plenum 60 from the ventilation bearing tunnel 56. The second circumferential groove 144 opens in the second direction 150 (for example, on the upstream side) toward the turbine axis 76.

The first circumferential groove 142 and the second circumferential groove 144 allow some degree of upstream and downstream movement of the inner barrel 48 with respect to the rear plate 62, thereby reducing stress in the region. In the illustrated embodiment, the rear plate 62 is configured to connect to the root portion 160 of the first circumferential groove 142 at the 12 o'clock position 118 of the seal interface 140. The seal interface 140 reduces the space between the first circumferential groove 142 and the root 160 so that no gap is formed at the 12 o'clock position 118. The sealing interface 140 also contributes to stress reduction of the pole 46 by allowing a portion of the longitudinal load of the rear plate 62 to be supported at the sealing interface of the inner barrel 48. The rear plate 62 may be offset from the root 160 of the first circumferential groove 142 at 6 o'clock position 122 (eg, opposite side of 12 o'clock position 118) of the seal interface 140.

The rear plate 62 can be composed of a plurality of circumferential segments 152 (for example, a rear plate segment, a conical plate 72). In some embodiments, one or more of the plurality of circumferential segments 152 is arranged along a junction 156 between the circumferential segments 152 of the rear plate 62, as described in connection with FIG. The stress relaxation feature portion 154 may be included. The stress relaxation feature portion 154 can be concentrated on the end portion of the circumferential segment 152 (eg, rear plate segment) close to the seal interface 140.

In one embodiment, the rear plate 62 can include a rear plate assembly 65 that may consist of a plurality of rear plate segments 67 (see FIG. 8). The rear plate assembly 65 can include two, three, four, five, six, or more rear plate segments 67. It will be appreciated that reducing the number of rear plate segments 67 contributes to a reduction in region assembly time by reducing the components associated with the rear plate assembly 65. The rear plate assembly 65 may be an annular rear plate assembly extending circumferentially 66 around the axis 76 of the inner barrel. The circumferential groove 40 also extends circumferentially 66 around the axis 76 of the inner barrel. The rear plate segments 67 can be joined together in a suitable manner, such as by welding, brazing, fusing, fastening, or any combination thereof. In the illustrated embodiment, the rear plate assembly 65 reduces the space between the first circumferential groove 142 and the root 160 so that no gap is formed at the 12 o'clock position 118. As further described with reference to FIGS. 8 and 9, the rear plate segment 67 can include a plurality of notches 71 and a plurality of ridges 73. The plurality of ridges 73 can be arranged on the radial inner surface 75 of the rear plate 62. The notch 71 and the ridge 73 can reduce the thermal mass of the rear plate assembly 65. Reducing the thermal mass of the rear plate assembly 65 can contribute to the reduction of thermal stress in the region when the turbine is operating and / or more uniform heat transfer between the components of the rear plate assembly 65. ..

FIG. 8 shows an axial view of an embodiment of the rear plate assembly 65 along line 8-8 of the diffuser 38 of FIG. In the illustrated embodiment, the rear plate assembly 65 includes three rear plate segments 67. As mentioned above, the rear plate assembly 65 has two, three, four, five, six, or more rear plate segments to form a 360 degree structure (eg, annular rear plate assembly). Any number of rear plate segments 67 can be included, including 67. The segments 67 can be joined together along the joint 156 by any suitable joining step such as welding or fusion. In some embodiments, each rear plate segment 67 may include one or more notches 71 (eg, receiving) and one or more ridges 73 (eg, inserts). can. The notch 71 and the ridge 73 are arranged on the radial inner surface 75 of the rear plate 62. The rear plate assembly 65 includes a downstream lip 61 of the inner barrel 48. The downstream lip 61 of the rear plate assembly 65 has a plurality of notches 79 and a plurality of ridges 83. In the illustrated embodiment, the radial inner surface 75 of the rear plate 62 has a raised portion 73 of the rear plate 62 axially passing through a notch 79 of the downstream lip 61 and a raised portion of the downstream lip 61. The 83 can be inserted into the circumferential groove 40 in the axial direction 76 so that the 83 passes through the notch 71 of the inner surface 75 of the rear plate 62 in the axial direction. Inserting the rear plate 62 into the circumferential groove 40 may include inserting the first ridge 81 of the rear plate 62 into the first notch 85 of the inner barrel 48. When the first ridge 81 is inserted into the first notch 85, the rear plate 62 is placed in a first circumferential orientation 87 (eg, first position) with respect to the inner barrel 48. .. That is, the rear plate assembly 65 is in the first circumferential orientation 87. The rear plate 62 is swiveled (eg, in a second position) in a second circumferential orientation 89 (eg, a second position) such that the first raised portion 81 is axially overlapped with the second raised portion 111 of the downstream lip 61 (eg, second position). It can rotate in the circumferential direction 66).

The rear plate 62 of the rear plate assembly 65 can swivel or rotate at about 15-60 degrees, 30-45 degrees, 35-40 degrees, or any partial range between them. When the rear plate 62 turns in the second circumferential orientation 89 with respect to the inner barrel 48, as indicated by the arrow 69, the rear plate assembly 65 holds the rear plate 62 axially 76 in the circumferential groove 40. It is configured as follows. The first circumferential orientation 87 is offset from the second circumferential orientation 89 in the circumferential direction by less than about 60 degrees around the axis 76 of the inner barrel 48. In some embodiments, the first circumferential orientation 87 is offset about less than about 30 degrees circumferentially around the axis 76 of the inner barrel from the second circumferential orientation 89. A method of forming the rear plate assembly 65 by inserting the plurality of ridges 73 of the rear plate 62 through the plurality of notches 71 of the downstream lip 61 can be further understood with reference to FIG. It will be appreciated that the rear plate assembly 65 allows the leakage of exhaust gas through the connection between the rear plate 62 and the inner barrel 48. Leakage of exhaust gas through the rear plate assembly 65 can reduce stress on the rear plate 62, the inner barrel 48, or some combination thereof. Leakage may be reduced as the ridge 73 turns in the second circumferential orientation 89 such that the ridge 73 of the rear plate 62 axially overlaps the ridge 83 of the inner barrel 48. In one embodiment, the exhaust gas leak may be 0.01-3%, 0.05-2%, 1-1.5% exhaust gas flow, or any subrange between them. ..

FIG. 9 shows a partial cross section of the rear plate assembly. As illustrated and described above, the rear plate assembly 65 includes a plurality of openings 176 for receiving the plurality of poles 46. One or more openings 176 can be placed in the rear plate segment 67. The rear plate segments 67 can be joined together via fusion, brazing, welding, or any other suitable process. The rear plate segment 67 can form a joint portion 156 (for example, a weld joint portion, a brazed joint portion, a fusion joint portion, a fastening joint portion) to which the rear plate segment 67 is joined together. As shown, the rear plate segment 67 includes a radial ridge height 91 between the root portion 97 of each notch 71 and the top 99 of the adjacent ridge 73. In addition, the downstream lip 61 of the inner barrel 48 has substantially the same or greater radial ridge height between the root 97 of each notch 79 and the top 99 of the adjacent ridge 83. 91 may have. In one embodiment, the radial height 91 is smaller than the radial height 105 of the upstream lip 77 of the circumferential groove 40.

FIG. 10 shows an axial view of an embodiment of the rear plate 62 of the inner barrel 48 along line 8-8 of the diffuser 38 of FIG. In the illustrated embodiment, the downstream end 104 of the rear plate 62 is coupled to the downstream end 104 of the front plate 64 via a plurality of poles 46. As mentioned above, the inner barrel 48 and the outer barrel 50 are arranged around the turbine axis 76. Therefore, the plurality of poles 46 are arranged around the turbine axis 76 at intervals in the circumferential direction 66.

As described above, the rear plate 62 can be composed of a plurality of circumferential segments 152 (eg, rear plate segment, conical plate 72). The plurality of circumferential segments 152 may include a plurality of stress relaxation feature portions 154 arranged along the plurality of joints 156 between the circumferential segments 152 of the rear plate 62. The plurality of stress relaxation feature portions 154 can be in any suitable shape for achieving stress relaxation, including circular, heart-shaped, bean-shaped, or any combination thereof.

In some embodiments, the pole 46 has a different pole diameter 70. The pole diameter 70 is partially based on the circumferential 66 position of the pole 46 position along the diffuser 38. For example, the diameter 70 of the pole 46 closest to the top 172 of the rear plate 62 and the front plate 64 has a diameter 70 larger than the pole 46 closest to the bottom 174 of the rear plate 62 and the front plate 64. Therefore, the plurality of openings 176 correspond to the plurality of poles 46 arranged in the diffuser 38. The opening 176 differs based in part on the circumferential 66 position of the opening 176 and can be coupled to the outer posterior plate 62 and the medial posterior plate 63 via a plurality of poles.

In the illustrated embodiment, the first set 178 (see FIG. 2) of poles 46 located at 66 positions in the circumferential direction within the bottom 174 of the diffuser 38 section can have a non-uniform axial cross section. For example, the first set 178 of poles 46 may have oval, oval, spherical, or other non-uniform axial cross-section portions. Due to the non-uniform portion of the pole 46 within the bottom 174 of the diffuser 38 section, the pole 46 can exhibit higher elasticity (eg, in the radial direction 84) than the circular pole 46, which can reduce the stress on the bottom 174. .. In some embodiments, the pole diameter 70 is reduced to reduce the aerodynamic effect on the flow of exhaust gas 36. Therefore, the small pole diameter 70 can be beneficial by reducing blockage of the exhaust flow path 36.

FIG. 11 shows an axial view of an embodiment of the rear plate assembly 65 of the inner barrel 48 along line 8-8 of the diffuser 38 of FIG. As mentioned above, the rear plate assembly 65 includes a plurality of rear plate segments 67. As described above, the rear plate assembly 65 shown in FIG. 11 is oriented in the second circumferential direction so that the raised portion 73 of the rear plate 62 is axially held by the raised portion 83 of the downstream lip 61 of the inner barrel 48. It is at 89. The rear plate segment 67 includes an opening 176 for receiving the pole 46 and connecting the downstream end 104 of the rear plate 62 to the downstream end 104 of the front plate 64. The pole 46 can be coupled to the rear plate segment 67 as described above with reference to FIG. That is, the first set 178 (see FIG. 2) of poles 46 located at the circumferential position within the bottom 174 of the diffuser 38 section can have a non-uniform axial cross section. In the illustrated embodiment, the rear plate segment 67 does not include the stress relaxation feature 154 shown in the rear plate 62 described above with reference to FIG.

FIG. 12 is a diagram illustrating a method of forming a rear plate assembly 65 according to an embodiment of the present disclosure. The rear plate assembly 65 can be formed by method 190. Method 190 can include joining a plurality of rear plate segments 67 to each other in the radial direction 84 by welding, fusing, brazing, bolting, or fastening, or any combination thereof (block 192). The joined rear plate segments 67 form the rear plate 62. Method 190 can include connecting the rear plate 62 and the root portion 160 of the first sealing interface 162 at 12 o'clock position 118 (block 194). As described above, the rear plate 62 provides the downstream lip 61 of the inner barrel 48 via complementary notches and ridges so that the rear plate 62 is located in the circumferential groove of the inner barrel 48. It can be inserted axially through it. That is, at the first circumferential position 87, the raised portion 73 of the rear plate 62 may be inserted axially through the notch 79 of the downstream lip 61, and the notch 71 of the rear plate 62 may be inserted. , The raised portion 83 of the downstream lip 61 may be accepted in the axial direction. In some embodiments, the 6 o'clock position 122 of the rear plate 62 is offset from the root 160 (eg, radially separated). Method 190 can include rotating the rear plate 62 about the axis of the inner barrel 48 (block 196). As mentioned above, the rear plate assembly 65 can rotate from the first circumferential position 87 to the second circumferential position 89. In some embodiments, the rear plate 62 rotates about 15-45 degrees with respect to the inner barrel 48. Method 190 can further include mounting the poles 46 between the downstream ends 104 of the rear plate 62 coupled to the downstream ends 104 of the front plate 64 via a plurality of poles 46 (block 198). ..

Next, returning to FIG. 10, the pole 46 arranged in the top 172 of the diffuser 38 can be configured to support the load (eg, weight) of the diffuser 38. For example, a pole 46 located within the top 172 of the diffuser 38 may be used to lift the diffuser 38. In some embodiments, a pole 46 located within the top 172 of the diffuser 38 section moves the diffuser 38 assembled with the rear plate 62 into the proper position (eg, for installation, removal, inspection, repair). Can be combined with hoists, lifts, cranes, or other suitable lifters to (move).

Each of the plurality of poles 46 includes a pole axis. In some embodiments, the plurality of poles 46 may be substantially parallel to a common pole axis (eg, turbine axis 76). It should be understood that the plurality of poles 46 do not support the plurality of swiveling vanes. Moreover, in some embodiments, the swivel vane is not placed on the diffuser 38. The poles are located at or near the downstream end of the diffuser 38 to reduce vibration and facilitate installation.

13 and 14 show side views of the inner barrel 48 and the outer barrel 50 of the diffuser 38. As shown by the solid line, the inner barrel 48 and the outer barrel 50 are curved to reduce the stress of the diffuser 38. The bends 88 of the inner barrel 48 and the outer barrel 50 start downstream of the turbine section 18. A portion of the inner barrel 48 and the outer barrel 50 is arranged within the exhaust plenum 60. FIG. 13 shows a side view of an embodiment of the outer barrel 50. The outer barrel 50 includes a first plurality of axial segments 180 located downstream of the outer barrel 50. In the illustrated embodiment, the outer barrel 50 includes two segments (eg, axial segments). Although two axial segments are shown, it will be appreciated that the outer barrel may include three, four or more axial segments. The first plurality of outer barrel segments 180 are joined together in the axial direction to form an outer barrel connecting portion 188 between each of the outer barrel segments 180. As mentioned above, joining can include welding, brazing, fusing, fastening, or any combination thereof. The first plurality of outer barrel segments 180 include a first continuous curve 182 that curves away from the turbine axis 76 (eg, from the upstream end of the outer barrel 50 to the outer rear plate 62).

FIG. 14 shows a side view of the inner barrel 48. In the illustrated embodiment, the inner barrel 48 includes four segments (eg, axial segments). The inner barrel 48 includes a second plurality of axial segments 184 disposed between the upstream end of the inner barrel 48 and the sealing interface 140. Although four axial segments are shown, it will be appreciated that the inner barrel 48 may include three, four, five, six, or more axial segments 184. The second plurality of axial segments 184 are joined together in the axial direction to form an inner barrel connecting portion 208 between each of the inner barrel segments 184. As mentioned above, joining can include welding, brazing, fusing, fastening, or any combination thereof. The second plurality of axial segments 184 (eg, the inner barrel segment) is a second continuous curve 186 that curves away from the turbine axis 76 (eg, from the upstream end of the inner barrel 48 to the seal interface 140). including. As will be appreciated, the second plurality of axial segments 184 (eg, of the inner barrel 48) are larger than the first plurality of axial segments of the outer barrel 50 due to the arrangement of the inner barrel 48 and the outer barrel 50. .. The bends in both the inner barrel 48 and the outer barrel 50 can be further understood in connection with the description of the spinning process, as illustrated in FIG.

FIG. 15 shows an exemplary device used to machine the inner barrel 48 and the outer barrel 50 into the desired continuous bend, as described in FIGS. 13 and 14. The first and second continuous curves 182,186 (eg, of the outer barrel, of the inner barrel) can be created via a suitable low temperature cutting step, such as a spinning step. The spinning step involves forming a suitable material 204 (eg, stainless steel) to shape the inner barrel 48 and the outer barrel 50 into the desired shape by placing the material on the mold 206. Next, the material 204 is formed into a desired shape by pushing the material into the mold 206 using a roller 202 and gradually forming a desired mold shape.

By the spinning steps described above, the desired curvature of the diffuser 38 can provide the required turbine engine performance (eg, through stress reduction). In order to reduce the residual stress encountered by the spinning process, the inner and outer barrels 48, 50 may have a plurality of axial segments (eg, a first plurality of axial segments 180, a second plurality of axial segments 184). May be formed from. Utilizing more axial segments to form the inner barrel 48 and the outer barrel 50 reduces the deformation of each segment to form the desired shape of the inner barrel 48 and the outer barrel 50, thereby reducing the deformation of each segment. The amount of residual stress remaining in the completed diffuser 38 can be reduced.

Once the axial segments (eg, the first plurality of axial segments 180, the second plurality of axial segments 184) are formed, the axial segments can be joined together. The axial segment is such that the axial segment (eg, the first plurality of axial segments 180, the second plurality of axial segments 184) has extra material so that the segments can be properly joined together. In addition, it can be cut from suitable materials. Axial segments can be joined together axially by welding, brazing, fusion, bolting, fastening, or any combination thereof.

FIG. 16 shows a method 300 of forming the inner barrel 48 and the outer barrel 50 by a spinning step. The spinning process described herein may be spin-processed around the axis of the mold using rollers, or the mold may be spin-processed around the axis under the rollers. As mentioned above, method 300 includes forming a first plurality of axially forward plate segments of the outer barrel 50 by spinning the appropriate material in a mold (block 302). As mentioned above, the spinning step of each segment involves molding the appropriate material (eg, stainless steel, metal) into the desired shape by placing the material in a mold. Next, the material is formed into a desired shape by pushing the material into the mold using a roller and gradually deforming the material into a desired mold shape. Method 300 also includes forming a second plurality of axial rear plate segments of the inner barrel 48 by spinning the appropriate material in a mold (block 304). After forming the axial segments, the method 300 joins the first plurality of axial anterior plate segments to each other to form the outer barrel 50 (block 306) and to form the inner barrel 48. Includes joining two plurality of axial rear plate segments to each other (block 308). Both the inner barrel 48 and the outer barrel 50 are coupled to the gas turbine engine 18. As mentioned above in connection with FIG. 7, the circumferential groove can be machined into the inner barrel 48.

The technical effect of the present invention includes improving the conventional diffuser by utilizing the mechanical improvement of the diffuser section. Mechanical improvements to the diffuser include a rear plate assembly with notches and ridges to facilitate axial installation of the rear plate on the inner barrel. The rear plate can be inserted axially through the notch in the circumferential groove of the inner barrel of the diffuser section and then in the circumferential groove so that the ridge holds the rear plate assembly axially. Rotate in the circumferential direction. Mechanical improvements to the diffuser contribute to the improved mechanical integrity of the diffuser by reducing the stress associated with traditional diffuser designs. Embodiments of mechanical modification were to manufacture the desired curvature of the diffuser, to place multiple poles between the front and rear plates of the diffuser, and to receive the rear plate on the inner barrel. Includes circumferential grooves, circumferential lap joints, multiple individual brackets located along the inner and outer barrels of the diffuser configured to connect the diffuser to the turbine outlet, or any combination thereof.

This specification uses examples to disclose the present invention and includes the best embodiments. It also uses examples to allow any person skilled in the art to practice the invention, including making and using any device or system and performing any embedded method. The patentable scope of the invention is defined by the claims and may include other embodiments reminiscent of those skilled in the art. Such other embodiments are patented if they have structural elements that are not significantly different from the wording of the claims, or if they contain equivalent structural elements that are not substantially different from the wording of the claims. It is within the claims.
[Phase 1]
By inserting the radial inner surface (75) of the rear plate assembly (65) into the circumferential groove (40) of the inner barrel (48) of the diffuser section (38) of the gas turbine (18) axially (76). The rear plate assembly (65) is inserted into the first circumferential orientation (87) with respect to the circumferential groove (40), and the circumferential groove (40) is the inner barrel (48). Insertion placed on the radial outer surface of the
Rotating the rear plate assembly (65) in the circumferential direction (66) within the circumferential groove (40) from the first circumferential orientation (87) to the second circumferential orientation (89). The inner barrel (48) holds the rear plate assembly (65) axially (76) when the rear plate assembly (65) is placed in the second circumferential orientation (89). Consists of rotating and including methods.
[Embodiment 2]
The rear plate assembly (65) includes an annular rear plate assembly extending circumferentially (66) around the axis (76) of the inner barrel (48), and the circumferential groove (40) is the axis (76). The method according to the first embodiment, which extends in the circumferential direction (66) around the).
[Embodiment 3]
The method of embodiment 1, wherein the rear plate assembly (65) comprises a plurality of rear plate segments (67).
[Embodiment 4]
The method of embodiment 3, comprising joining the plurality of rear plate segments (67) together, the joining comprising welding, brazing, fusing, fastening, or any combination thereof.
[Embodiment 5]
The rear plate assembly (65) includes a first plurality of notches (71) and a first plurality of ridges (73) on the radial inner surface (75) and the circumferential groove (75). 40) comprises a downstream lip (61), wherein the downstream lip (61) comprises a second plurality of notches (79) and a second plurality of ridges (83). The method according to 1.
[Embodiment 6]
Inserting the radial inner surface (75) of the rear plate assembly (65) into the circumferential groove (40) of the inner barrel (48) in the axial direction (76) is the second plurality of cuts. The first plurality of ridges (73) may be inserted through the notch (79), the second plurality of notches (79) may have the rear plate assembly (65) of the second. The method according to embodiment 5, wherein the first plurality of notches (71) are configured to be held in the axial direction (76) when arranged in the circumferential orientation (89).
[Embodiment 7]
Of the root portion (97) of each notch portion (71) of the first plurality of notch portions (71) and the adjacent ridge portion (73) of the first plurality of ridge portions (73). The height of the radial ridge (91) to and from the top (99) is smaller than the radial height (105) of the upstream lip (77) of the circumferential groove (40), and the first plurality. The ridges (73) of the upstream lip (77) and the second plurality of ridges (83) when the rear plate assembly (65) is arranged in the second circumferential orientation (89). ). The method according to the fifth embodiment.
[Embodiment 8]
The method of embodiment 1, wherein a plurality of poles (46) are coupled between the rear plate assembly (65) and the anterior plate (64) of the diffuser section (38).
[Embodiment 9]
The first circumferential orientation (87) is offset from the second circumferential orientation (89) about less than about 30 degrees in the circumferential direction (66) around the axis (76) of the inner barrel (48). The method according to embodiment 1.
[Embodiment 10]
The diffuser section (38) includes a diffuser section (38) configured to receive the exhaust gas (36) from the turbine section (18).
A rear plate assembly (65) that includes a radial inner surface (75) that includes a first notch (71) and a first ridge (73), and
The circumferential groove (40) includes an inner barrel (48) including a circumferential groove (40) arranged on the outer surface in the radial direction.
With the upstream lip (77),
Includes a second notch (79) and a downstream lip (61) containing a second ridge (83).
In the first raised portion (73), the rear plate assembly (65) is arranged in a first circumferential orientation (87) and a second circumferential orientation (89) with respect to the inner barrel (48). The first raised portion (73) is configured to be arranged in the circumferential groove (40) in the case of ) And the axial direction (76), the first raised portion (73) is oriented in the second circumferential direction (89) from the second notch portion (79) to the circumferential direction (66). System (10) offset to.
[Embodiment 11]
10. The system (10) according to embodiment 10, wherein the rear plate assembly (65) comprises a plurality of rear plate segments (67).
[Embodiment 12]
The plurality of rear plate segments (67) are joined together to form an annular rear plate assembly, and the plurality of rear plate segments (67) are welded joints, brazed joints, fusion joints, and fastened. 10. The system (10) according to embodiment 11, wherein the joints are joined together by at least one of the joints, or any combination thereof.
[Embodiment 13]
The radial inner surface (75) includes a first plurality of notches (71) and a first plurality of ridges (73), and the radial outer surface includes a second plurality of notches. The first plurality of ridges (73) include the notch (79) and the second plurality of ridges (83), and the first plurality of ridges (73) are aligned with the first circumferential orientation (87). The first plurality of raised portions (73) are aligned with the notch portion (79) of the above, and the first plurality of raised portions (73) are aligned with the second circumferential orientation (89). The system (10) according to embodiment 10, which is aligned with (83) in the axial direction (76).
[Phase 14]
The radial ridge height (91) between the root portion (97) of the first notch portion (71) and the top portion (99) of the first ridge portion (73) is the circumferential direction. 10. The system (10) according to embodiment 10, wherein the upstream lip (77) of the groove (40) is smaller than the radial height (105).
[Embodiment 15]
The diffuser section (38)
Front plate (64) and
A plurality of poles (46) coupled to the front plate (64) and the rear plate assembly (65) when the rear plate assembly (65) is arranged in the second circumferential orientation (89). 10. The system (10) according to embodiment 10, which includes. [Embodiment 16]
10. The system (10) according to embodiment 10, wherein the first circumferential orientation (87) is offset from the second circumferential orientation (89) in the circumferential direction (66) by less than about 30 degrees.
[Embodiment 17]
The diffuser section (38) includes a diffuser section (38) configured to receive the exhaust gas (36) from the turbine section (18).
Front plate (64) and
A rear plate assembly (65) that includes a radial inner surface (75) that includes a first plurality of notches (71) and a first plurality of ridges (73).
An inner barrel (48) including a circumferential groove (40) arranged on a radial outer surface, wherein the circumferential groove (40) is
With the upstream lip (77),
An inner barrel (48) containing a second plurality of notches (79) and a downstream lip (61) including a second plurality of ridges (83).
Between the front plate (64) and the rear plate assembly (65) when the rear plate assembly (65) is arranged in a second circumferential orientation (89) with respect to the inner barrel (48). Includes multiple poles (46) to be combined
In the first plurality of ridges (73), the rear plate assembly (65) has a first circumferential orientation (87) and a second circumferential orientation (89) with respect to the inner barrel (48). The first plurality of raised portions (73) are configured to be arranged in the circumferential groove (40) when arranged in the first circumferential orientation (87). Aligned with the plurality of notches (79) in the axial direction (76), the first plurality of ridges (73) are the second plurality of cuts in the second circumferential orientation (89). System (10) offset from the notch (79) in the circumferential direction (66).
[Embodiment 18]
The rear plate assembly (65) includes a plurality of rear plate segments (67) that are joined together to form an annular rear plate assembly, and the plurality of rear plate segments (67) are welded joints, brazed joints. The system (10) according to embodiment 17, wherein the fusion joint and at least one of the fastening joints, or any combination thereof, are joined together.
[Embodiment 19]
The top (99) of the first ridge (73) of the first plurality of ridges (73) is the second circumference of the rear plate assembly (65) with respect to the inner barrel (48). The system (10) according to embodiment 17, which is configured to connect to the root portion (160) of the circumferential groove (40) at the 12 o'clock position (118) when arranged in the directional orientation (89).
[Embodiment 20]
Each pole (46) of the plurality of poles (46) includes a diameter (70), and the diameter (70) of each pole (46) is said to be around the axis (76) of the diffuser section (38). The system (10) according to embodiment 17, which is at least partially based on the circumferential position of each pole (46).

10 Gas turbine system 12 Fuel nozzle 14 Fuel 16 Combustor 18 Turbine section, gas turbine, gas turbine engine 20 Turbine outlet, exhaust outlet 22 Compressor 24 Air intake 26 Load 28 Shaft 30 Air 32 Pressurized air 34 Air-fuel mixing Air 36 Exhaust flow path, exhaust flow, high temperature pressurized exhaust gas 38 Integrated diffuser, diffuser section, modified diffuser 40 Circumferential groove 42 Joint 44 Individual outer bracket, circumferential support bracket 45 Outer individual bracket, support bracket, individual Outer Bracket 46 Circular Pole 47 Support Bracket, Inner Individual Bracket 48 Inner Barrel 49 One End 50 Outer Barrel 52 Upper Part 54 Lower Part, Lower Section 56 Ventilation Bearing Tunnel 58 Exhaust Frame, Frame Assembly 60 Exhaust Plenum 61 Downstream Lip 62 Outer Rear Plate 63 Inner Rear Plate 64 Front Plate 65 Rear Plate Assembly 66 Circumferential 67 Rear Plate Segment 68 Gasset 69 Arrow 70 Pole Diameter, Different Diameter 71 Notch 72 Conical Plate 73 Raised 74 Vertical Joint 75 Radial Inner Surface 76 Turbine Axis, Axial, Axis 77 Upstream Lip 78 Vertical 79 Notch 80 Lateral 81 First Raised 82 Blade 83 Raised 84 Radial 85 First Notch 86 Pin 87 First Circumferential position, first circumferential orientation 88 Continuous curved portion 89 Second circumferential position, second circumferential orientation 90 Relay block 91 Radial ridge height 92 Flexible seal 93 First end 94 Flexible Seal Groove 95 Gap Space 96 Upstream Lip, Outer Lip 97 Root 98 Slot 99 Top 100 Damping Length 101 Secondary Flexible Seal 102 Upstream End, Secondary Flexible Seal Groove 103 First End Part 104 Downstream, Downstream end 105 Radial height 106 Outer side wall 111 Second raised part 112 Inner side wall 114 Inner peripheral joint 116 Flange, diffuser frame 118 12 o'clock position 120 3 o'clock position 122 6 o'clock position 124 9 Time Position 126 Insulation 128 Outer Lip, Downstream Lip 130 Primary Flow 134 Inner Region
136 Secondary flow path 140 Seal interface 142 First circumferential groove 144 Second circumferential groove 146 First direction 150 Second direction 152 Circumferential segment 154 Stress relaxation feature 156 Joint 160 Root 162 First Seal interface 172 Top 174 Bottom 176 Opening 178 First set 180 Outer barrel segment, axial segment 182 First continuous curve 184 Inner barrel segment, axial segment 186 Second continuous curve 188 Outer barrel connection 190 Method 192 Block 194 Block 196 Block 198 Block 202 Roller 204 Appropriate Material 206 Mold 208 Inner Barrel Connection 302 Block 304 Block 306 Block 308 Block

Claims (14)

In the step of axially (76) inserting the radial inner surface (75) of the rear plate assembly (65) into the circumferential groove (40) of the inner barrel (48) of the diffuser section (38) of the gas turbine (18). The rear plate assembly (65) is inserted into the first circumferential orientation (87) with respect to the circumferential groove (40), and the circumferential groove (40) is the inner barrel (48). a step that will be positioned in the radially outer surface of
It is a step of rotating the rear plate assembly (65) in the circumferential direction (66) in the circumferential groove (40) from the first circumferential orientation (87) to the second circumferential orientation (89). The inner barrel (48) holds the rear plate assembly (65) axially (76) when the rear plate assembly (65) is placed in the second circumferential orientation (89). A method that includes steps and <br /> that are configured in. The rear plate assembly (65) includes an annular rear plate assembly extending circumferentially (66) around the axis (76) of the inner barrel (48), and the circumferential groove (40) is the axis (76). ) extend in the circumferential direction (66) around the method of claim 1. The rear plate assembly (65) comprises a plurality of rear plate segments (67), The method of claim 1. The includes a plurality of both joining the rear plate segment (67), joining comprises welding, brazing, fusing, the alignment look fastening or their combination, the method according to claim 3. The rear plate assembly (65) includes a first plurality of notches (71) and a first plurality of ridges (73) on the radial inner surface (75) and the circumferential groove (75). 40) comprises a downstream lip (61), including the downstream lip (61), a second plurality of notches and (79), a second plurality of raised portion (83), wherein Item 1. The method according to item 1. Inserting a semi-radial inner surface (75) in the axial direction (76) of the rear plate assembly in circumferential grooves (40) of the inner barrel (48) (65) lacks said second plurality off The first plurality of ridges (73) are inserted through the portion (79), and the second plurality of notches (79) include the rear plate assembly (65) in the second circumference of the second plurality of notches (79). configured to maintain the first plurality of notches when placed in the alignment direction (89) and (71) in the axial direction (76), the method of claim 5. Of the root portion (97) of each notch portion (71) of the first plurality of notch portions (71) and the adjacent ridge portion (73) of the first plurality of ridge portions (73). The height of the radial ridge (91) to and from the top (99) is smaller than the radial height (105) of the upstream lip (77) of the circumferential groove (40), and the first plurality. The ridges (73) of the upstream lip (77) and the second plurality of ridges (83) when the rear plate assembly (65) is placed in the second circumferential orientation (89). ) is disposed between the method of claim 5. Comprising coupling a plurality of poles (46) between the after how plate assembly of the diffuser section (38) and (65) and front plate (64), The method of claim 1. The first circumferential orientation (87) is offset from the second circumferential orientation (89) by less than 30 degrees in the circumferential direction (66) around the axis (76) of the inner barrel (48). , The method according to claim 1. A turbine section (18) configured diffuser section to receive the exhaust gas (36) from (38) the including system (10), said diffuser section (38),
A rear plate assembly (65) that includes a radial inner surface (75) that includes a first notch (71) and a first ridge (73), and
Includes an inner barrel (48) including a radially disposed outer surface circumferential grooves (40), said circumferential groove (40) is,
With the upstream lip (77),
Includes a second notch (79) and a downstream lip (61) containing a second ridge (83).
In the first raised portion (73), the rear plate assembly (65) is arranged in a first circumferential orientation (87) and a second circumferential orientation (89) with respect to the inner barrel (48). The first raised portion (73) is configured to be arranged in the circumferential groove (40) at the time, and the first raised portion (73) is arranged in the first circumferential orientation (87) with the second notched portion (79). ) And the axial direction (76), the first raised portion (73) is oriented in the second circumferential direction (89) from the second notch portion (79) to the circumferential direction (66). System (10) offset to. The rear plate assembly (65) comprises a plurality of rear plate segment (67) The system of claim 10, (10). The plurality of rear plate segments (67) are joined together to form an annular rear plate assembly, and the plurality of rear plate segments (67) are welded joints, brazed joints, fusion joints and fastening joints. part of being joined together by at least one or combination thereof set saw system of claim 11 (10). The radial inner surface (75) includes a first plurality of notches (71) and a first plurality of ridges (73), and the radial outer surface includes a second plurality of notches. The first plurality of ridges (73) include the notch (79) and the second plurality of ridges (83), and the first plurality of ridges (73) are aligned with the first circumferential orientation (87). The first plurality of raised portions (73) are aligned with the notch portion (79) of the above, and the first plurality of raised portions (73) are aligned with the second circumferential orientation (89). The system (10) according to claim 10, which is aligned axially with (83). The radial ridge height (91) between the root portion (97) of the first notch portion (71) and the top portion (99) of the first ridge portion (73) is the circumferential direction. radial height (105) is smaller than the groove (40) on the upstream side lip (77) of the system of claim 10 (10).

Images