Separation tool and method for nozzle section of gas turbine

Abstract

The present application provides a nozzle section separation tool (100) for use with a pair of airfoils (190) of adjacent nozzle sections (66) in a turbine (40). The nozzle section separation tool (100) includes a pair of separation brackets (110), a movable separation bracket (120) and a fixed separation bracket (130), and a hydraulic cylinder (140) positioned between the pair of separation brackets (110). A movable separation bracket (120) is positioned about a first airfoil (300) of the pair of airfoils (190) and a fixed separation bracket (130) is positioned about a second airfoil (310) of the pair of airfoils (190). The hydraulic cylinder (140) urges the movable separation bracket (120) against the first airfoil (300) until the fixed separation bracket (130) urges the second airfoil (310) away from the first airfoil (300).

Description

Technical Field

[0001] This application and the resulting patents generally relate to gas turbine engines, and more specifically to a separation tool for separating adjacent nozzle sections in preparation for removing the nozzles from the turbine housing for repair or replacement. Background Technology

[0002] Gas turbine engines typically consist of a compressor for compressing ambient air and a combustor for mixing the airflow with a fuel flow to produce hot combustion gases. The turbine receives the hot combustion gas flow and extracts energy from it to power the compressor and generate output power for external loads such as generators. Turbine components, such as turbine nozzles and blades positioned along the hot gas path, are subjected to high combustion temperatures and pressures, as well as various types of dynamic forces. Therefore, these hot gas path components may be periodically replaced and / or overhauled to ensure efficient and safe performance.

[0003] Removing hot gas components such as nozzles can be difficult and time-consuming. Each stage of a nozzle can typically be formed into multiple segments and placed end-to-end circumferentially to form a continuous ring around the housing of the turbine section. High temperature and high pressure environments can cause the nozzles to stick together and / or become stuck together in the support structure. However, the small clearances in the turbine section provide very little space to access the nozzles, and the other components within it provide much less space to apply any type of force to separate the nozzles before removal. Summary of the Invention

[0004] Therefore, this application and the resulting patent provide a nozzle section separation tool for use with a pair of airfoils of adjacent nozzle sections in a turbine. The nozzle section separation tool includes a pair of separation brackets, a movable separation bracket, and a fixed separation bracket, and a hydraulic cylinder positioned between the pair of separation brackets. The movable separation bracket is positioned around a first airfoil of the pair of airfoils, and the fixed separation bracket is positioned around a second airfoil of the pair of airfoils. The hydraulic cylinder pushes the movable separation bracket against the first airfoil until the fixed separation bracket pushes the second airfoil apart from the first airfoil.

[0005] This application and the resulting patent also provide a method for separating a pair of adjacent nozzles in the housing of a turbine. The method may include the following steps: sliding a nozzle segment separation tool about the pair of airfoils; positioning a movable separation bracket of the nozzle segment separation tool about a first airfoil of the pair; positioning a fixed separation bracket of the nozzle segment separation tool about a second airfoil of the pair; and pushing the movable separation bracket against the first airfoil by a hydraulic cylinder until the fixed separation bracket pushes the second airfoil apart from the first airfoil.

[0006] This application and the resulting patent also provide a nozzle section separation tool for use with a pair of airfoils of adjacent nozzle sections in a turbine. The nozzle section separation tool includes a pair of separation brackets, a movable separation bracket, and a fixed separation bracket, and a hydraulic cylinder positioned between the pair of separation brackets. The fixed separation bracket is attached to the hydraulic cylinder and has a profile shape. The movable separation bracket is positioned around a first airfoil of the pair of airfoils, and the fixed separation bracket is positioned around a second airfoil of the pair of airfoils. The hydraulic cylinder pushes the movable separation bracket against the first airfoil until the fixed separation bracket pushes the second airfoil apart from the first airfoil.

[0007] These and other features and improvements of this application and the resulting patent will become apparent to those skilled in the art upon reading the following detailed description in conjunction with the accompanying drawings and claims. Attached Figure Description

[0008] Figure 1 This is a schematic diagram of a gas turbine engine, which includes a compressor, burner, turbine, and external load.

[0009] Figure 2 This is a schematic diagram of multiple stages located within the turbine housing.

[0010] Figure 3 This is a front perspective view of the nozzle section separation tool as described in this article.

[0011] Figure 4 yes Figure 3 Rear perspective view of the nozzle section separation tool.

[0012] Figure 5 It is positioned between a pair of airfoils. Figure 3 A partial front view cross-section of the nozzle section separation tool.

[0013] Figure 6 It is positioned between a pair of airfoils. Figure 3 A partial rear cross-sectional view of the nozzle section separation tool.

[0014] Figure 7 It is located between the nozzle sections Figure 3 A perspective view of the nozzle section separation tool.

[0015] Figure 8 It is positioned between a pair of airfoils. Figure 3 Top view of the nozzle section separation tool.

[0016] Figure 9 It is positioned around the nozzle section. Figure 3 Side view of the nozzle section separation tool. Detailed Implementation

[0017] Referring now to the accompanying drawings, where similar numbers in several views refer to similar elements. Figure 1 A schematic diagram of a gas turbine engine 10, which may be used herein, is shown. The gas turbine engine 10 may include a compressor 15. The compressor 15 compresses an incoming air stream 20. The compressor 15 delivers the compressed air stream 20 to a plurality of burner canisters 25. The burner canisters 25 mix the compressed air stream 20 with a pressurized fuel stream 30 and ignite the mixture, thereby producing a hot combustion gas stream 35. Although only a single burner canister 25 is shown, the gas turbine engine 10 may include any number of burner canisters 25 positioned in a circumferential array or the like. Alternatively, the burner 25 may be an annular burner. The combustion gas stream 35 is then delivered to a turbine 40. The combustion gas stream 35 drives the turbine 40 to generate mechanical work. The mechanical work generated in the turbine 40 drives the compressor 15 via a rotor shaft 45 and drives an external load 50 (such as a generator).

[0018] The gas turbine engine 10 can use natural gas, various types of syngas, liquid fuels, and / or other types of fuels and blends thereof. The gas turbine engine 10 can be any of a variety of different gas turbine engines supplied by General Electric Company of Schenectady, New York, including but not limited to those such as the 7 Series or 9 Series heavy-duty gas turbine engines. The gas turbine engine 10 can be part of a single-cycle or combined-cycle power generation system or other types of power generation systems. The gas turbine engine 10 can have different configurations and can use other types of components. Other types of gas turbine engines may also be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment may also be used together herein.

[0019] Figure 2This is a partial cross-sectional view of turbine 40. Turbine 40 includes multiple stages 52. Generally, each stage 52 of turbine 40 includes a fixed row 54 of nozzles 56 and a rotating row 58 of turbine blades 60. In this example, three stages 52 are shown: a first stage, a second stage, and a third stage. Any number of stages 52 may be used herein. Turbine blades 60 in each row 58 are circumferentially spaced around rotor disks 62 and extend radially outward from the rotor disks. Each rotor disk 62 is coupled to a rotor shaft 45. Turbine housing 64 extends circumferentially around the nozzles 56. Each nozzle 56 is coupled to turbine housing 64, and each nozzle 56 extends radially inward from turbine housing 64 toward rotor shaft 45. Specifically, as will be described in more detail below, the nozzles 56 may be arranged in multiple segments 66 and may be attached to turbine housing 64 via multiple shroud recesses in multiple shrouds. A hot combustion gas path 72 may be defined between turbine housing 64 and each rotor disk 62.

[0020] Figures 3 to 5 An example of a nozzle segment separation tool 100 as described herein is shown. The nozzle segment separation tool 100 may include a pair of separation brackets 110. In this case, there is a movable separation bracket 120 and a fixed separation bracket 130. The separation brackets 110 may be made of any substantially rigid material, such as stainless steel. A hydraulic cylinder 140 may be positioned between and attached to the separation brackets 110. The hydraulic cylinder 140 may have a conventional design. Specifically, the hydraulic cylinder 140 may include a hydraulic fluid port 150 located within a hydraulic rotary lift 160 and an internal piston 170. The hydraulic cylinder 140 may have a single-stroke or two-stroke design. An exemplary hydraulic cylinder may be a 5-ton capacity hydraulic cylinder sold by ENERPAC of Milwaukie, Wisconsin. Other types of hydraulic cylinders, other types of capacities, and other types of push or pull mechanisms may be used herein. For example, different types of jacks, screws, etc., may be used herein. The hydraulic rotary lift 160 can rotate through any desired rotation angle. Other components and configurations are also available in this paper.

[0021] At least a fixed separation bracket 130 of the nozzle section separation tool 100 may have a profile shape 180. The profile shape 180 of the fixed separation bracket 130 may be complementary to the shape of the intended airfoil 190. A movable separation bracket 120 may have a similar profile. Separation brackets 110 having different types of profile shapes 180 may be used herein to accommodate airfoils 190 of different types and shapes. Each separation bracket in the separation brackets 110 may have a damping layer 200 thereon. The damping layer 200 may be any type of viscoelastic material, such as rubber, polymer, etc. Each separation bracket in the separation brackets 110 may also have a buffer 210 extending laterally therefrom. The buffer 210 may be any type of substantially rigid material and may also have a damping layer 200 thereon. The buffer 210 helps guide the separation bracket 110 into the proper position around the airfoil 190 and holds the separation bracket 110 in the proper position once operation has begun. Other components and other configurations may also be used herein.

[0022] The fixed separation bracket 130 of the nozzle section separating tool 100 can be bolted or otherwise attached to the hydraulic cylinder 140. The separation bracket 110 can also be attached to each other via a pair of safety slides 220. In this case, there is a top safety slide 230 and a front safety slide 240. Each safety slide 220 can be fixedly attached to the movable separation bracket 120 and slidably attached to the fixed separation bracket 130 via a roller 250 positioned within a slot 260. If the nozzle section separating tool 100 disengages from the airfoil 190, the safety slides 220 limit the travel length of the separation bracket 110. Brackets, cables, etc., can also be used. Other components and configurations are also possible herein.

[0023] The nozzle section separating tool 100 may have a tool lever 270 attached thereto. Specifically, the tool lever 270 may be attached to the fixed separating bracket 130 or other locations via a quick-release coupling 280 having a quick-release pin 290. Other types of attachment mechanisms may also be used herein. The tool lever 270 may have any suitable size, shape, and length. Other types of operating devices and connecting devices may also be used herein. Other components and other configurations may also be used herein.

[0024] In such Figures 5 to 9In the illustrated application, the nozzle segment separation tool 100 can be inserted between the airfoils 190 of adjacent nozzle segments 66. Specifically, the nozzle segment separation tool 100 can be operated into position between the first airfoil 300 and the second airfoil 310 via a tool lever 270 or otherwise. A movable separation bracket 120 contacts the first airfoil 300, and a fixed separation bracket 130 contacts the second airfoil 310. A buffer 210 helps to properly orient the separation bracket 110 into position. A hydraulic cylinder 140 can be activated and can push the movable separation bracket 120 against the first airfoil 300. The hydraulic cylinder 140 continues to push, causing the fixed separation bracket 130 to contact the second airfoil 310. The nozzle segment separation tool 100 thus pushes the second airfoil 310 along the direction of travel 320 until the airfoil 190 and the nozzle segment 66 are separated. The hydraulic cylinder 140 can then disengage. The nozzle segment separation tool 100 can then be removed and / or repositioned. Once separated, the nozzle segment 66 can be removed in the normal manner.

[0025] The nozzle section separation tool 100 thus allows for quick and easy separation of the nozzle section 66. Notably, the nozzle section separation tool 100 can separate the nozzle section 66 without requiring the time-consuming disassembly of the turbine 40 as a whole, i.e., without removing the rotor 45, etc. The nozzle section separation tool 100 thus reduces the required labor time and the overall downtime of the gas turbine engine 10.

[0026] It should be apparent that the foregoing only relates to certain embodiments of this application and the resulting patent. Many changes and modifications can be made herein by those skilled in the art without departing from the general spirit and scope of the invention as defined by the appended claims and their equivalents.

[0027] Other aspects of the invention are provided by the subject matter of the following provisions:

[0028] 1. A nozzle section separation tool for use with a pair of airfoils of adjacent nozzle sections in a turbine, the nozzle section separation tool comprising: a pair of separation brackets; wherein the pair of separation brackets includes a movable separation bracket and a fixed separation bracket; and a hydraulic cylinder positioned between the pair of separation brackets; wherein the movable separation bracket is positioned around a first airfoil of the pair of airfoils, and the fixed separation bracket is positioned around a second airfoil of the pair of airfoils; and wherein the hydraulic cylinder pushes the movable separation bracket against the first airfoil until the fixed separation bracket pushes the second airfoil apart from the first airfoil.

[0029] 2. The nozzle section separation tool according to any of the preceding clauses, wherein the hydraulic cylinder includes an internal piston.

[0030] 3. The nozzle section separating tool according to any of the preceding clauses, wherein the hydraulic cylinder includes a hydraulic fluid port located within a hydraulic rotary lift.

[0031] 4. The nozzle section separation tool according to any of the preceding clauses, wherein one or both of the pair of separation brackets have a profile shape.

[0032] 5. The nozzle section separation tool according to any of the preceding clauses, wherein each of the pair of separation brackets includes a damping layer.

[0033] 6. The nozzle section separation tool according to any of the preceding clauses, wherein each of the pair of separation brackets includes a buffer.

[0034] 7. The nozzle section separation tool according to any of the preceding clauses, wherein the buffer includes a damping layer.

[0035] 8. The nozzle section separation tool according to any of the preceding clauses further includes a safety slide positioned between the pair of separation brackets.

[0036] 9. The nozzle section separation tool according to any of the preceding clauses, wherein the safety slider is fixedly attached to the movable separation bracket.

[0037] 10. The nozzle section separation tool according to any of the preceding clauses, wherein the safety slider is slidably attached to the fixed separation bracket via rollers and slots.

[0038] 11. The nozzle section separation tool according to any of the preceding clauses further includes a plurality of safety sliders.

[0039] 12. The nozzle section separation tool according to any of the foregoing clauses further includes a tool control lever.

[0040] 13. The nozzle section separation tool according to any of the preceding clauses, wherein the tool lever is attached to the fixed separation bracket via a quick-release coupling.

[0041] 14. The nozzle section separation tool according to any of the preceding clauses, wherein the fixed separation bracket is bolted to the hydraulic cylinder.

[0042] 15. A method for separating a pair of airfoils in adjacent nozzle sections of a turbine, the method comprising: sliding a nozzle section separating tool about the pair of airfoils; positioning a movable separating bracket of the nozzle section separating tool about a first airfoil of the pair of airfoils; positioning a fixed separating bracket of the nozzle section separating tool about a second airfoil of the pair of airfoils; and pushing the movable separating bracket against the first airfoil by a hydraulic cylinder until the fixed separating bracket pushes the second airfoil away from the first airfoil.

[0043] 16. A nozzle section separation tool for use with a pair of airfoils of adjacent nozzle sections in a turbine, the nozzle section separation tool comprising: a pair of separation brackets; wherein the pair of separation brackets includes a movable separation bracket and a fixed separation bracket; and a hydraulic cylinder positioned between the pair of separation brackets; wherein the fixed separation bracket is attached to the hydraulic cylinder and has a profile shape; wherein the movable separation bracket is positioned around a first airfoil of the pair of airfoils, and the fixed separation bracket is positioned around a second airfoil of the pair of airfoils; and wherein the hydraulic cylinder pushes the movable separation bracket against the first airfoil until the fixed separation bracket pushes the second airfoil apart from the first airfoil.

[0044] 17. The nozzle section separating tool according to any of the preceding clauses, wherein the hydraulic cylinder includes a hydraulic rotary lift.

[0045] 18. The nozzle section separation tool according to any of the preceding clauses, wherein each of the pair of separation brackets includes a damping layer and a buffer.

[0046] 19. The nozzle section separation tool according to any of the preceding clauses further includes a safety slide positioned between the pair of separation brackets.

[0047] 20. The nozzle section separation tool according to any of the preceding clauses further includes a tool lever attached to the fixed separation bracket.

[0048] Reference List :

[0049] 10 Gas Turbine Engine

[0050] 15 Compressors

[0051] 20 Airflow

[0052] 25 Burners

[0053] 30 Fuel Flow

[0054] 35 Combustion Gas Flow

[0055] 40 Turbo

[0056] 45 axis

[0057] 50 generators

[0058] Level 52

[0059] 54 fixed rows

[0060] 56 nozzles

[0061] 58 Rotating Rows

[0062] 60 turbine blades

[0063] 62 Rotor disc

[0064] 64. Housing

[0065] Section 66

[0066] 68 grooves

[0067] 70 shield

[0068] 72 Combustion Path

[0069] 100 Nozzle Section Separation Tool

[0070] 110 Separation bracket

[0071] 120 Movable Separable Bracket

[0072] 130 Fixed Separation Bracket

[0073] 140 hydraulic cylinder

[0074] 150 hydraulic fluid port

[0075] 160 Hydraulic Rotary Lift

[0076] 170 Piston

[0077] 180 Outline Shape

[0078] 190 airfoil

[0079] 200 damping layer

[0080] 210 Buffer

[0081] 220 Safety Slider

[0082] 230 Top Safety Slide

[0083] 240 Front safety slider

[0084] 250 rolls

[0085] 260 slot

[0086] 270 Tool joystick

[0087] 280 Quick-Release Connector

[0088] 290 Quick Release Pin

[0089] 300 First airfoil component

[0090] 310 Second airfoil component

[0091] 320 Direction of travel

Claims

1. A nozzle section separation tool for use with a pair of airfoils of adjacent nozzle sections in a turbine, the nozzle section separation tool comprising: A pair of separate brackets; The pair of separation brackets includes a movable separation bracket and a fixed separation bracket; and A hydraulic cylinder, positioned between the pair of separating brackets; The movable separation bracket is positioned around the first airfoil of the pair of airfoils, and the fixed separation bracket is positioned around the second airfoil of the pair of airfoils; and The hydraulic cylinder pushes the movable separation bracket against the first airfoil until the fixed separation bracket pushes the second airfoil to separate from the first airfoil.

2. The nozzle section separation tool according to claim 1, wherein the hydraulic cylinder includes an internal piston.

3. The nozzle section separation tool according to claim 1, wherein the hydraulic cylinder includes a hydraulic fluid port located within a hydraulic rotary lift.

4. The nozzle section separation tool according to claim 1, wherein one or both of the pair of separation brackets have a profile shape.

5. The nozzle section separation tool according to claim 1, wherein each of the pair of separation brackets includes a damping layer.

6. The nozzle section separation tool according to claim 1, wherein each of the pair of separation brackets includes a buffer.

7. The nozzle section separation tool according to claim 6, wherein the buffer includes a shock-absorbing layer.

8. The nozzle section separation tool according to claim 1, wherein the nozzle section separation tool further comprises a safety slider positioned between the pair of separation brackets.

9. The nozzle section separation tool according to claim 8, wherein the safety slider is fixedly attached to the movable separation bracket.

10. The nozzle section separation tool according to claim 9, wherein the safety slider is slidably attached to the fixed separation bracket via rollers and slots.

11. The nozzle section separation tool according to claim 8, wherein the nozzle section separation tool further comprises a plurality of safety sliding members.

12. The nozzle section separation tool according to claim 1, wherein the nozzle section separation tool further comprises a tool control lever.

13. The nozzle section separation tool of claim 12, wherein the tool lever is attached to the fixed separation bracket via a quick-release coupling.

14. The nozzle section separation tool according to claim 1, wherein the fixed separation bracket is bolted to the hydraulic cylinder.

15. A method for separating a pair of airfoils in adjacent nozzle sections of a turbine, the method comprising: Slide the nozzle section separation tool around the pair of airfoils; A movable separation bracket for positioning the nozzle section separation tool around the first airfoil of the pair of airfoils; A fixed separation bracket for positioning the nozzle section separation tool around the second airfoil of the pair of airfoils; as well as The movable separation bracket is pushed against the first airfoil by a hydraulic cylinder until the fixed separation bracket pushes the second airfoil to separate from the first airfoil.

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