Separation tool and method for nozzle segment of gas turbine

Abstract

To provide a separation tool and method for a nozzle segment of a gas turbine.SOLUTION: A nozzle segment separation tool (100) includes a pair of separation brackets, a movable separation bracket (120), a stationary separation bracket (130), and a hydraulic cylinder (140) positioned between the pair of separation brackets. The movable separation bracket (120) is positioned around a first vane-shaped part (300) of a pair of vane-shaped parts (190), and the stationary separation bracket (130) is positioned around a second vane-shaped part (310) of the pair of vane-shaped parts (190). The hydraulic cylinder (140) presses the movable separation bracket (120) against the first vane-shaped part (300) until the stationary separation bracket (130) presses and separates the second vane-shaped part (310) from the first vane-shaped part (300).SELECTED DRAWING: Figure 5

Description

[Technical Field]

[0001] This application and the resultant patent relate generally to gas turbine engines, and more particularly to a separation tool used to separate adjacent nozzle segments in preparation for removing the nozzle from the casing of the turbine for repair or replacement. [Background technology]

[0002] A gas turbine engine traditionally includes a compressor for compressing ambient air and a combustor for mixing the flow of air with a flow of fuel to generate hot combustion gases. A turbine receives the flow of hot combustion gases and extracts energy therefrom to power the compressor, which generates output power for an external load, such as an electrical generator. 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 different types of dynamic forces. Therefore, these hot gas path components may be periodically replaced and / or refurbished to ensure efficient and safe performance.

[0003] Removal of hot gas components, such as nozzles, can be difficult and time-consuming. Each stage of nozzles is typically formed in segments and may be mounted end-to-end circumferentially to form a continuous ring around the casing of the turbine section. The high temperature and pressure environment can cause the nozzles to stick together and / or become seized together within the supporting structure. Furthermore, small gaps in the turbine section provide little space for accessing the nozzles and other components therein, much less sufficient space for applying any type of force to separate the nozzles before removal. Summary of the Invention

[0004] Accordingly, this application and the resulting patent provide a nozzle segment separation tool for use with a pair of airfoils of adjacent nozzle segments in a turbine. The nozzle segment separation tool includes a pair of separation brackets, a movable separation bracket and a stationary 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 stationary separation bracket is positioned around a second airfoil of the pair of airfoils. The hydraulic cylinder presses the movable separation bracket against the first airfoil until the stationary separation bracket presses against the second airfoil, separating it from the first airfoil.

[0005] The present application and resultant patent further provides a method for separating a pair of adjacent nozzles in a casing of a turbine, the method including sliding a nozzle segment separation tool around a pair of airfoils, positioning a movable separation bracket of the nozzle segment separation tool around a first airfoil of the pair of airfoils, positioning a stationary separation bracket of the nozzle segment separation tool around a second airfoil of the pair of airfoils, and pressing the movable separation bracket against the first airfoil with a hydraulic cylinder until the stationary separation bracket presses the second airfoil to separate it from the first airfoil.

[0006] The present application and the resulting patent may further provide a nozzle segment separation tool for use with a pair of airfoils of adjacent nozzle segments in a turbine. The nozzle segment separation tool includes a pair of separation brackets, a movable separation bracket and a stationary separation bracket, and a hydraulic cylinder positioned between the pair of separation brackets. The stationary separation bracket is attached to the hydraulic cylinder and includes an outer shape. The movable separation bracket is positioned around a first airfoil of the pair of airfoils, and the stationary separation bracket is positioned around a second airfoil of the pair of airfoils. The hydraulic cylinder presses the movable separation bracket against the first airfoil until the stationary separation bracket presses against the second airfoil to separate it from the first airfoil.

[0007] These and other features and improvements of the present application and the resulting patent will become apparent to those skilled in the art from a review of the following detailed description taken in conjunction with the several drawings and the appended claims. [Brief explanation of the drawings]

[0008] [Figure 1] 1 is a schematic diagram of a gas turbine engine including a compressor, a combustor, a turbine, and an external load. [Figure 2] 1 is a schematic diagram of several stages positioned within a casing of a turbine. [Figure 3] FIG. 10 is a front perspective view of a nozzle segment separation tool that may be described herein. [Figure 4] FIG. 4 is a rear perspective view of the nozzle segment separation tool of FIG. 3. [Figure 5] FIG. 4 is a partial cross-sectional front view of the nozzle segment separation tool of FIG. 3 positioned between a pair of airfoils. [Figure 6] FIG. 4 is a partial rear cross-sectional view of the nozzle segment separation tool of FIG. 3 positioned between a pair of airfoils. [Figure 7] FIG. 4 is a perspective view of the nozzle segment separation tool of FIG. 3 positioned between the nozzle segments. [Figure 8] FIG. 4 is a top view of the nozzle segment separation tool of FIG. 3 positioned between a pair of airfoils. [Figure 9] FIG. 4 is a side view of the nozzle segment separation tool of FIG. 3 positioned around a nozzle segment. DETAILED DESCRIPTION OF THE INVENTION

[0009] Referring now to the drawings, wherein like numerals refer to like elements throughout the several views, FIG. 1 illustrates a schematic diagram of a gas turbine engine 10 that may be used herein. The gas turbine engine 10 may include a compressor 15. The compressor 15 compresses an incoming flow of air 20. The compressor 15 delivers the compressed flow of air 20 to a number of combustor cans 25. The combustor cans 25 mix the compressed flow of air 20 with a pressurized flow of fuel 30 and ignite the mixture to generate a flow of hot combustion gases 35. While only a single combustor can 25 is shown, the gas turbine engine 10 may include any number of combustor cans 25 positioned, such as in a circumferential array. Alternatively, the combustor 25 may be an annular combustor. The flow of combustion gases 35 is then delivered to a turbine 40. The flow of combustion gases 35 drives the turbine 40 to generate mechanical work. The mechanical work generated in the turbine 40 drives the compressor 15 and an external load 50, such as an electrical generator, via a rotor shaft 45.

[0010] The gas turbine engine 10 may use natural gas, various types of synthetic gas, liquid fuels, and / or other types of fuels, as well as blends thereof. The gas turbine engine 10 may be any one of several different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, engines such as a 7 Series or 9 Series heavy-duty gas turbine engine. The gas turbine engine 10 may be part of a simple cycle or combined cycle power generation system or other type of power generation system. The gas turbine engine 10 may have a different configuration and may 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.

[0011] FIG. 2 is a partial cross-sectional view of the turbine 40. The turbine 40 includes several stages 52. Generally described, each stage 52 of the turbine 40 includes a stationary 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. The turbine blades 60 in each row 58 are circumferentially spaced about a rotor disk 62 and extend radially outward therefrom. Each rotor disk 62 is coupled to the rotor shaft 45. A turbine casing 64 extends circumferentially around the nozzles 56. Each nozzle 56 is coupled to the turbine casing 64, and each nozzle 56 extends radially inward from the turbine casing 64 toward the rotor shaft 45. Specifically, as described in more detail below, the nozzles 56 may be arranged in several segments 66 and may be attached to the turbine casing 64 via several shroud grooves in several shrouds. A hot combustion gas path 72 may be defined between the turbine casing 64 and each rotor disk 62 .

[0012] 3-5 illustrate an example of a nozzle segment separation tool 100 that may be described herein. The nozzle segment separation tool 100 may include a pair of separation brackets 110, in this case a movable separation bracket 120 and a stationary 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 be of conventional design. Specifically, the hydraulic cylinder 140 may include a hydraulic swivel hoist 160 and a hydraulic fluid port 150 positioned within an internal piston 170. The hydraulic cylinder 140 may have a single-stroke or double-stroke design. An exemplary hydraulic cylinder may be a 5-ton capacity hydraulic cylinder sold by ENERPAC of Milwaukee, Wisconsin. Other types of hydraulic cylinders, capacities, and push or pull mechanisms may be used herein. For example, different types of jacks, screws, etc. may be used herein. The hydraulic swivel hoist 160 can rotate through any desired angle of rotation. Other components and configurations may be used herein.

[0013] At least the stationary separation brackets 130 of the nozzle segment separation tool 100 can have a contoured shape 180. The contoured shape 180 of the stationary separation bracket 130 can be complementary to the shape of the intended airfoil 190. The movable separation bracket 120 can be similarly contoured. Herein, separation brackets 110 having different types of contoured shapes 180 can be used to accommodate different types and shapes of airfoils 190. Each separation bracket 110 can have a shock absorbing layer 200 thereon. The shock absorbing layer 200 can be any type of viscoelastic material, such as rubber, a polymer, or the like. Each separation bracket 110 can also have a bumper 210 extending laterally therefrom. The bumper 210 can be any type of substantially rigid material and can have the shock absorbing layer 200 thereon. The bumper 210 helps guide the separation bracket 110 into position around the airfoil 190 and maintains the separation bracket 110 in position once operation is initiated. Other components and other configurations may be used herein.

[0014] The stationary separation bracket 130 of the nozzle segment separation tool 100 may be bolted or otherwise attached to the hydraulic cylinder 140. The separation brackets 110 may also be attached to one another by a pair of safety slides 220, in this case an upper safety slide 230 and a front safety slide 240. Each safety slide 220 may be fixedly attached to the movable separation bracket 120 and slidably attached to the stationary separation bracket 130 via a roller 250 positioned in a slot 260. The safety slides 220 limit the length of travel of the separation bracket 110 when the nozzle segment separation tool 100 disengages from the airfoil 190. Brackets, cables, and the like may also be used. Other components and configurations may be used herein.

[0015] The nozzle segment separation tool 100 may have an attached tool steering rod 270. Specifically, the tool steering rod 270 may be attached to the stationary separation bracket 130 or elsewhere via a quick release coupling 280 having a quick release pin 290. Other types of attachment mechanisms may be used herein. The tool steering rod 270 may have any suitable size, shape, and length. Other types of steering and connection devices may be used herein. Other components and other configurations may be used herein.

[0016] During use, as shown in FIGS. 5-9 , 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 manipulated into position via the tool steering rod 270, or between the first airfoil 300 and the second airfoil 310. The movable separation bracket 120 contacts the first airfoil 300, and the stationary separation bracket 130 contacts the second airfoil 310. The bumper 210 assists in properly orienting the separation bracket 110 in position. The hydraulic cylinder 140 can be actuated to press the movable separation bracket 120 against the first airfoil 300. The hydraulic cylinder 140 continues to press the stationary separation bracket 130 into contact with the second airfoil 310. Thus, the nozzle segment separation tool 100 pushes the second airfoil 310 in the direction of travel 320 until the airfoil 190 and nozzle segment 66 are separated. The hydraulic cylinder 140 may then be disengaged. The nozzle segment separation tool 100 may then be removed and / or repositioned. Once separated, the nozzle segment 66 may be removed in the usual manner.

[0017] Thus, the nozzle segment separation tool 100 enables quick and easy separation of the nozzle segments 66. Importantly, the nozzle segment separation tool 100 can separate the nozzle segments 66 without requiring time-consuming disassembly of the entire turbine 40, i.e., without requiring removal of the rotor 45, etc. The nozzle segment separation tool 100 therefore reduces the labor hours required and reduces the overall downtime of the gas turbine engine 10.

[0018] It should be apparent that the foregoing relates only to certain embodiments of this application and the resulting patent. Numerous changes and modifications may be made herein by those skilled in the art without departing from the general spirit and scope of the invention as defined by the following claims and their equivalents.

[0019] Further aspects of the present invention are provided by the subject matter of the following clauses.

[0020] 1. A nozzle segment separation tool for use with a pair of airfoils of adjacent nozzle segments in a turbine, comprising: a pair of separation brackets, the pair of separation brackets including a movable separation bracket and a stationary separation bracket; and a hydraulic cylinder positioned between the pair of separation brackets, the movable separation bracket being positioned around a first airfoil of the pair of airfoils and the stationary separation bracket being positioned around a second airfoil of the pair of airfoils, the hydraulic cylinder pressing the movable separation bracket against the first airfoil until the stationary separation bracket presses against the second airfoil to separate it from the first airfoil.

[0021] 2. The nozzle segment separation tool of clause 1, wherein the hydraulic cylinder includes an internal piston.

[0022] 3. A nozzle segment separation tool as described in any one of clauses 1 to 2, wherein the hydraulic cylinder has a hydraulic fluid port positioned within a hydraulic swivel hoist.

[0023] 4. A nozzle segment separation tool as described in any one of clauses 1 to 3, wherein one or both of the pair of separation brackets has an outer shape.

[0024] 5. A nozzle segment separation tool as described in any one of clauses 1 to 4, wherein each of the pair of separation brackets comprises an impact absorbing layer.

[0025] 6. A nozzle segment separation tool as described in any one of clauses 1 to 5, wherein each of the pair of separation brackets includes a bumper.

[0026] 7. A nozzle segment separation tool as described in any one of clauses 1 to 6, wherein the bumper comprises an impact absorbing layer.

[0027] 8. A nozzle segment separation tool as described in any one of clauses 1 to 7, further comprising a safety slide positioned between the pair of separation brackets.

[0028] 9. A nozzle segment separation tool as described in any one of clauses 1 to 8, wherein the safety slide is fixedly attached to the movable separation bracket.

[0029] 10. A nozzle segment separation tool as described in any one of clauses 1 to 9, wherein the safety slide is slidably attached to the stationary separation bracket via rollers and slots.

[0030] 11. The nozzle segment separation tool of any one of clauses 1 to 10, further comprising a plurality of safety slides.

[0031] 12. A nozzle segment separation tool as described in any one of clauses 1 to 11, further comprising a tool steering rod.

[0032] 13. A nozzle segment separation tool as described in any one of clauses 1 to 12, wherein the tool steering rod is attached to the stationary separation bracket via a quick release coupling.

[0033] 14. A nozzle segment separation tool as described in any one of clauses 1 to 13, wherein the stationary separation bracket is bolted to the hydraulic cylinder.

[0034] 15. A method of separating a pair of airfoils of adjacent nozzle segments in a turbine, the method comprising: sliding a nozzle segment separation tool around the pair of airfoils; positioning a movable separation bracket of the nozzle segment separation tool around a first airfoil of the pair of airfoils; positioning a stationary separation bracket of the nozzle segment separation tool around a second airfoil of the pair of airfoils; and pressing the movable separation bracket against the first airfoil with a hydraulic cylinder until the stationary separation bracket presses the second airfoil against the first airfoil to separate it from the first airfoil.

[0035] 16. A nozzle segment separation tool for use with a pair of airfoils of adjacent nozzle segments in a turbine, comprising: a pair of separation brackets, the pair of separation brackets comprising a movable separation bracket and a stationary separation bracket; and a hydraulic cylinder positioned between the pair of separation brackets, the stationary separation bracket attached to the hydraulic cylinder and having an outer shape, the movable separation bracket positioned around a first airfoil of the pair of airfoils and the stationary separation bracket positioned around a second airfoil of the pair of airfoils, and the hydraulic cylinder pressing the movable separation bracket against the first airfoil until the stationary separation bracket presses against the second airfoil to separate it from the first airfoil.

[0036] 17. The nozzle segment separation tool of clause 16, wherein the hydraulic cylinder comprises a hydraulic swivel hoist.

[0037] 18. A nozzle segment separation tool as described in any one of clauses 16-17, wherein each of the pair of separation brackets comprises an impact absorbing layer and a bumper.

[0038] 19. A nozzle segment separation tool as described in any one of clauses 16 to 18, further comprising a safety slide positioned between the pair of separation brackets.

[0039] 20. A nozzle segment separation tool as described in any one of clauses 16 to 19, further comprising a tool steering rod attached to the stationary separation bracket. [Explanation of symbols]

[0040] 10. Gas turbine engine 15 Compressor 20 Air Flow 25 Combustor 30 Fuel flow 35 Combustion gas flow 40 Turbine 45 shaft 50 Generator 52 steps 54 Stationary column 56 nozzles 58 Rotating Row 60 turbine blades 62 rotor disc 64 Casing 66 segments 68 Groove 70 Shroud 72 Combustion Path 100 Nozzle Segment Separation Tool 110 Separation bracket 120 Movable separation bracket 130 Stationary Separation Bracket 140 Hydraulic Cylinder 150 hydraulic fluid ports 160 Hydraulic Swivel Hoist 170 piston 180 External shape 190 Airfoil 200 shock absorbing layer 210 Bumper 220 Safety Slide 230 Upper Safety Slide 240 Front Safety Slide 250 Lola 260 slots 270 Tool Control Rod 280 Quick Release Coupling 290 Quick Release Pin 300 First airfoil 310 Second Airfoil 320 Direction of travel

Claims

1. A nozzle segment separation tool (100) for use with a pair of airfoils (190) of adjacent nozzle segments (66) in a turbine (40), comprising: A pair of separation brackets (110), The pair of separation brackets (110) comprises a movable separation bracket (120) and a stationary separation bracket (130). A pair of separating brackets (110); a hydraulic cylinder (140) positioned between the pair of separating brackets (110); Equipped with the movable isolation bracket (120) is positioned about a first airfoil (300) of the pair of airfoils (190) and the stationary isolation bracket (130) is positioned about a second airfoil (310) of the pair of airfoils (190); the hydraulic cylinder (140) presses the movable separation bracket (120) against the first airfoil (300) until the stationary separation bracket (130) presses the second airfoil (310) away from the first airfoil (300); A nozzle segment separation tool (100).

2. The nozzle segment separation tool (100) of claim 1, wherein the hydraulic cylinder (140) comprises an internal piston (170).

3. The nozzle segment separation tool (100) of claim 1, wherein the hydraulic cylinder (140) comprises a hydraulic fluid port (150) positioned within a hydraulic swivel hoist (160).

4. The nozzle segment separation tool (100) of claim 1, wherein one or both of the pair of separation brackets (110) comprises a contoured shape (180).

5. The nozzle segment separation tool (100) of claim 1, wherein each of the pair of separation brackets (110) comprises an impact absorbing layer (200).

6. The nozzle segment separation tool (100) of claim 1, wherein each of the pair of separation brackets (110) comprises a bumper (210).

7. The nozzle segment separation tool (100) of claim 6, wherein the bumper (210) comprises an impact absorbing layer (200).

8. The nozzle segment separation tool (100) of claim 1, further comprising a safety slide (220) positioned between the pair of separation brackets (110).

9. The nozzle segment separation tool (100) of claim 8, wherein the safety slide (220) is fixedly attached to the movable separation bracket (120).

10. The nozzle segment separation tool (100) of claim 9, wherein the safety slide (220) is slidably mounted to the stationary separation bracket (130) via a roller (250) and a slot (260).

11. The nozzle segment separation tool (100) of claim 8, further comprising a plurality of safety slides (220).

12. The nozzle segment separation tool (100) of claim 1, further comprising a tool steering rod (270).

13. The nozzle segment separation tool (100) of claim 12, wherein the tool steering rod (270) is attached to the stationary separation bracket (130) via a quick release coupling (280).

14. The nozzle segment separation tool (100) of claim 1, wherein the stationary separation bracket (130) is bolted to the hydraulic cylinder (140).

15. A method of separating a pair of airfoils (190) of adjacent nozzle segments (66) in a turbine (40), comprising: sliding a nozzle segment separation tool (100) around the pair of airfoils (190); positioning a movable separation bracket (120) of the nozzle segment separation tool (100) about a first airfoil (300) of the pair of airfoils (190); positioning a stationary separation bracket (130) of the nozzle segment separation tool (100) about a second airfoil (310) of the pair of airfoils (190); pressing the movable separation bracket (120) against the first airfoil (300) by a hydraulic cylinder (140) until the stationary separation bracket (130) presses the second airfoil (310) away from the first airfoil (300); A method comprising:

Images