• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    What is provided is an apparatus and method for removing and installing combustor walls (310) in a combustor shell (380) of a turbine. The apparatus includes an elongated handle (410) having two ends, a first U-shaped bracket (430) having a hole for receiving a pin (435) and a second bracket (412) attached to the elongate shaft (410), and wherein the first U-shaped bracket (430) is located at one of the two ends. A clamp turner assembly (440, 445, 447, 449) having a tower clamp (445) adapted to be attached to a flange (381) of a combustor housing (380) and a tower clamp section (440) having a number of recesses is formed to receive the pin (435) of the elongated stem (410).
    公开号:CH701187B1
    申请号:CH00850/10
    申请日:2010-05-28
    公开日:2016-01-15
    发明作者:Randall S Corn；James B Holmes；John W Herbold
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background to the invention
    The invention described herein relates to gas turbines, and more particularly to an apparatus and method for removing and / or installing combustor walls in a combustor casing of a turbine.
    Gas turbines usually include a combustion chamber having a combustion chamber wall defining a combustion chamber. In the combustion chamber, a mixture of compressed air and fuel is burned to produce hot combustion gases. The combustion gases may flow through the combustor to one or more turbine stages to produce power for driving a load and / or a compressor. Due to the hot combustion gases, the combustion process usually heats the combustion chamber wall.
    Combustor walls are routinely removed and installed during maintenance of gas turbines. Some known removal tools are usually unwieldy, but make it easier to remove combustion chamber walls without significant damage. The combustor wall stops usually require circumferential alignment in each combustion chamber between the projecting combustor wall stops and the receiving combustor wall stops. Sealing tires usually require several hundreds of pounds of axial installation force, which is often applied with a manually guided hammer. The force exerted by the hammer is uneven, can damage parts and cause injury. Without a perfectly aligned orientation of the combustor wall stops, the combustor wall is rotated while the seal tire is loaded. The torsional loading of the grommet may damage the gasket sheets or the gasket coating.
    Brief description of the invention
    In the following special embodiments according to the subject matter of the present invention are described in summary. These embodiments are not intended to limit the scope of the present invention, but rather, these embodiments are intended merely to provide a brief description of possible embodiments of the invention. In fact, the invention may cover a variety of forms which may be similar or different from those set forth below.
    According to the present invention, a device for removing and installing combustion chamber walls in a combustion chamber housing of a turbine is provided. The device comprises an elongate stem having two ends, a first U-shaped holder having a recess for receiving a pin and a second holder being secured to the elongate stem, and wherein the first U-shaped holder (430) is attached to one of the two Ends is arranged. An attachment device having a body in the form of a clamp adapted to be attached to a flange of a combustor casing has a tower portion with a number of recesses which serve to receive the pin of the elongated stem.
    According to the present invention, a method for installing a combustion chamber wall in a combustion chamber housing a turbine with the device according to claims 1, 3 and 7 is provided. The method includes the steps of providing an alignment guide that serves to align a stop of the combustion chamber wall with a stop on the combustion chamber housing in alignment. In a step of attaching, the alignment guide is attached to the combustion chamber housing. An insertion step at least partially inserts the combustion chamber wall into the combustion chamber housing. An elongate stem assembly, a combustor wall push rod and a clamp turner assembly are provided, and the clamp turner assembly is attached to the combustor housing. The combustor wall push rod is attached to the elongated handle assembly and the elongated handle assembly is attached to the clamp turner assembly. A groove formed in the combustion chamber wall push rod is positioned over a portion of the combustion chamber wall and the combustion chamber wall is installed in the combustion chamber housing by applying force to the elongate stem assembly.
    According to the present invention, a method for removing a arranged in a combustion chamber housing a turbine combustion chamber wall by means of a device according to claims 1 and 5 is provided. The method includes the steps of providing an elongate stem assembly, a combustor wall hook and a clamp turner assembly, attaching the clamp turner assembly to the combustor casing, attaching the combustor wall hook to the elongate stem assembly, and attaching the elongate stem assembly to the clamp turner assembly. The combustion chamber wall hook is positioned behind a stop of the combustion chamber wall, and the combustion chamber wall is at least partially removed from the combustion chamber housing by applying force to the elongated stem assembly.
    Brief description of the drawings
    These and other features, aspects, and advantages of the present invention will become more apparent upon reading the following detailed description taken in conjunction with the accompanying drawings, in which like parts are numbered consistently with like reference numerals:<Tb> FIG. 1 <SEP> illustrates in a block diagram a turbine system with a combustion chamber wall;<Tb> FIG. 2 <SEP> illustrates the turbine system shown in FIG. 1 in a cutaway side view;<Tb> FIG. 3 <SEP> shows in a cutaway side view the combustion chamber with a combustion chamber wall, according to an embodiment of the present invention;<Tb> FIG. Figure 4 <SEP> is a perspective view of a stem and clamp that may be used to remove and install combustor walls, according to one embodiment of the present invention;<Tb> FIG. FIG. 5 is a perspective view showing a combustor wall push rod that may be used to install combustor walls according to one embodiment of the present invention; FIG.<Tb> FIG. 6 <SEP> is a perspective view of a combustor wall hook that may be used to remove combustor walls according to one embodiment of the present invention;<Tb> FIG. Fig. 7 shows in perspective view an alignment guide that may be used during the removal and installation of combustor walls, according to an embodiment of the present invention;<Tb> FIG. Fig. 8 <SEP> is a perspective view showing a combustion chamber housing and a combustion chamber wall including the stem and clamp of Fig. 4, the combustion chamber wall push rod of Fig. 5, and the alignment guide of Fig. 7 secured and positioned for installation an embodiment of the present invention.
    Detailed description of the invention
    Hereinafter, one or more specific embodiments of the present invention will be described. In an effort to provide a concise description of these embodiments, not all features of an actual implementation may be included in the description. It should be understood, however, that in developing any such implementation, as in any engineering or design project, numerous application-specific decisions must be made in order to achieve specific objectives of the designers, e.g. Conformance with systemic and economic constraints that may vary from one implementation to another. Moreover, it should be understood that such a development effort could be complex and time consuming, but nonetheless would be a routine means of development, manufacture, and manufacture for those skilled in the art having the benefit of this description.
    When elements of various embodiments of the present invention are introduced, the indefinite and definite articles "a," "the," "the," etc., are intended to include the presence of more than one element. The terms "comprise", "contain" and "exhibit" are to be understood as inclusive and mean that additional elements may exist that are different from the listed elements. Examples of operating parameters and / or environmental conditions do not exclude other parameters / conditions of the described embodiments. Moreover, it should be understood that references to "one embodiment" of the present invention are not to be interpreted as excluding the existence of additional embodiments also incorporating the listed features.
    Before reading further, several terms commonly used in the present specification are first defined to enable a better understanding of the subject matter being treated. As used herein, the terms "upstream" and "downstream" as used in connection with a combustor wall are to be understood as the near end of the combustor wall and the far end of the combustor wall, respectively, with respect to the fuel nozzles. That is, the terms "upstream" and "downstream" are, unless otherwise indicated, generally used with respect to the flow of combustion gases flowing inside the combustion chamber wall. For example, a direction labeled "downstream" indicates the direction in which a fuel-air mixture burns and flows from the fuel nozzles to a turbine, and a direction labeled "upstream" indicates the direction opposite to the downstream direction as defined above. Moreover, as used herein, the term "downstream end portion", "connecting portion" or the like is intended to refer to a rearmost (most downstream) portion of the combustion chamber wall. As discussed below, in specific embodiments, the axial length of the downstream end portion of the combustion chamber wall may be up to 20 percent of the total axial length of the combustion chamber wall. The downstream end portion (or connecting portion), in some embodiments, may also refer to the portion of the combustion chamber wall that is configured to be connected to a downstream transition piece of the combustion chamber in substantially a telescoping, concentric, or coaxial overlapping annular relationship. In addition, it should be clear that the term "chamber wall / lining" on its own is generally to be understood as synonymous with "combustion chamber wall". Considering the terms defined above, the present description relates to a method and apparatus for removing and / or installing a combustor wall of a gas turbine.
    [0012] Referring now to the drawings and initially to FIG. 1, a block diagram of one embodiment of a turbine system 10 is illustrated. As discussed in more detail below, the described turbine system 10 may utilize a combustor wall having a number of surface features formed about a downstream end portion to provide improved and more uniform cooling of the combustor wall. The turbine system 10 may use liquid or gaseous fuel to operate the turbine system 10, e.g. Natural gas and / or a hydrogen-rich synthesis gas. As shown, a plurality of fuel nozzles 12 receive a fuel supply 14, mix the fuel with air, and discharge the fuel-air mixture into a combustor system 16. The fuel-air mixture burns in a chamber in the interior of the combustion chamber system 16 and thereby generates hot, pressurized exhaust gases. The combustion chamber 16 directs the exhaust gases through a turbine 18 in the direction of an outlet 20 into the open. As the exhaust gases flow through the turbine 18, the gases cause one or more turbine blades to rotate a shaft 22 along an axis of the system 10. As can be seen, the shaft 22 is connected to various components of the turbine system 10, e.g. with a compressor 24. The compressor 24 also has blades that may be connected to the shaft 22. Thus, the blades disposed in the compressor 24 rotate as the shaft 22 rotates, thereby compressing air received from an air intake port 26 through the compressor 24 and into the fuel nozzles 12 and / or the combustion chamber 16. The shaft 21 may be connected to a load 28, which may be a vehicle or a stationary load, e.g. an electric generator in a power plant or a propeller of an aircraft. Of course, the load 28 may include any suitable device that may be driven by the torque output of the turbine system 10. The load 28 can also be removed at the turbine end of the gas turbine.
    Fig. 2 illustrates a cut-away side view of an embodiment of the turbine system 10 shown schematically in Fig. 1. The turbine system 10 has one or more fuel nozzles 12, which are arranged in the interior of one or more combustion chambers 16. The combustors 16 may include one or more combustor walls, which are usually arranged in one or more corresponding flow sleeves. In operation, air enters the turbine system 10 through the air intake port 26 and may be pressurized within the compressor 24. The compressed air can then be mixed with gas to be burned in the combustion chamber 16. For example, the fuel nozzles 12 may inject a fuel-air mixture into the combustor system 16 in a ratio that is capable of optimizing combustion, emissions, fuel consumption, and power output. The combustion produces hot, pressurized exhaust gases which subsequently drive one or more blades 17 in the turbine 18 to rotate the shaft 22 (shown in FIG. 1) and subsequently the compressor 24 and the compressor (shown in FIG. 1). To drive load 28 rotating. The rotation of the turbine blades 17 causes the shaft 22 to rotate so that the blades 19 disposed in the compressor 22 are caused to suck and compress the air taken in through the suction port 26. While the portion of the air supplied by the compressor (which is generally much cooler in comparison to the combustion gases flowing in the combustion chamber 16) flows through the cooling passage and contacts the surface features, heat transfer occurs in the heat from the combustion chamber wall is dissipated. For example, this heat transfer can be carried out by means of forced convection.
    Referring now to Figure 3, a more detailed cutaway side view of one embodiment of the combustor 16 is illustrated. It will be appreciated that the combustor 16 is usually fluidly connected to the compressor 24 and the turbine 18. The combustion chamber 16 has a combustion chamber wall 310, which is arranged in a flow sleeve 320. Flow sleeves may be used in conjunction with combustor walls, however, some applications may dispense with the flow sleeve. The interior of the combustor wall 310 may define a substantially cylindrical or annular combustor 315. The illustrated combustor wall 310 is but one example of a plurality of different combustor walls that may be used in conjunction with the method and apparatus of the invention.
    Downstream of the combustion chamber wall 310 and the flow sleeve 320 (for example in the direction C), a transition piece 330 may be connected to the combustion chamber wall 310. Thus, the direction C may represent a downstream direction relative to the flow of combustion gases away from the fuel nozzles 12 disposed inside the combustion chamber wall 310. As used herein, the terms "upstream" and "downstream" used in connection with a combustor wall are to be understood as those proximate the fuel nozzles at the end of the combustion chamber wall and the distal end of the combustion chamber wall, respectively. That is, the terms "upstream" and "downstream" are, unless otherwise indicated, generally used with respect to the flow of combustion gases present within the combustion chamber wall. For example, a direction labeled "downstream" indicates the direction in which a fuel-air mixture burns and flows from the fuel nozzles to a turbine, and a direction labeled "upstream" indicates the direction opposite to the downstream direction as defined above.
    The transition piece 330 (which may also be referred to as a "transitional channel") may be disposed in a baffle sleeve 340. An internal cavity 335 of the transition piece 330 essentially forms a flow path (as shown by the arrow C) through which combustion gases from the combustion chamber 315 can be directed to the turbine 18. In the illustrated embodiment, the transition piece 330 may be connected to the downstream end of the combustor wall 310 (in the direction C) using a seal 350 (e.g., a grommet). In some combustor wall embodiments, a grommet may seal the junction between the combustor wall and the transition piece. Gasket tires are circumferentially arranged metal gaskets that may be slotted in the axial direction and that may be contoured to be spring biased between inner and outer diameters of mating components that experience relative movement. Sealing tires may be disposed between the rear (i.e., downstream) end of the combustion chamber wall and the forward (i.e., upstream) end of the transition piece.
    The combustor wall 310 has one or more projecting combustor wall stops 360 that contact one or more receiving combustor wall stops 370 that are secured to the flow sleeve 320. In some embodiments that do not include a flow sleeve, the stops may be attached to the inside of the combustor housing 380. The combustor housing 380 usually further includes a flange 381. The receiving combustor wall stop 370 is generally U-shaped and the projecting combustor wall stop 360 has a substantially rectangular cross-section and fits into the receiving combustor wall stop 370. The combustor wall stops require circumferentially aligned alignment in each combustor, usually between the projecting combustor wall stops 360 and the receiving combustor wall stops 370. The combustor wall stops facilitate installation and removal of the combustor wall 310 and prevent the combustor wall 310 from rotating during operation of the turbine 10 ,
    The sealing strip 350 seals the downstream end of the combustion chamber wall 310 against the upstream end of the transition piece 330. Sealing tires usually require several hundreds of pounds of axial installation force, heretofore usually exerted with a hammer. The force exerted by the hammer is uneven, can damage components and cause injury. Without proper alignment of the combustor wall stops, the combustor wall may be rotated while the seal tire disposed in the inlet diameter of the transition piece is loaded. Torsional loading of the grommet may damage the gasket sheets or the gasket coating.
    In the following, with reference to Fig. 4, a tool for installing and removing a combustion chamber wall according to one aspect of the present invention will be described. A stem 410 may have a rubberized handle 420 at a first end and a U-shaped holder 430 at an opposite end. The stem 410 may be used to push a combustion chamber wall 310 into the combustion chamber, or may be used to withdraw a combustion chamber wall 310 from the combustion chamber, as described in more detail below. The bracket 430 has a hole located near the end that allows a pin 435 to pass therethrough. The pin 435 may further include one or more through holes at each end to receive a suitable fastener (e.g., a split pin, a spring pin, or any other fastener). The pin fits into one of the many slots in a clamp tower 440. The multiple slots allow a user to position the handle at different heights for optimal leverage. The clamping tower 440 is connected to a U-shaped base body 445 which, in cooperation with an adjustable clamping screw 447 and the knob 449, serves to securely attach the clamping tower to a flange of a combustion chamber. The stem also has a support 412 formed with a through hole 414 which serves to secure various components to facilitate installation and removal of combustion chamber walls. The stem assembly (410, 412, 420, 430, 435) and clamp turner assembly (440, 445, 447, 449) may be made of any material that can withstand the stresses encountered during use of the tool; usually, but not limited to, steel, steel alloys, aluminum, aluminum alloys, combinations thereof, or any other material.
    FIG. 5 illustrates a perspective view of a combustor wall push rod 500 that may be used in conjunction with the handle 410 to push a combustor wall 310 in place during installation. The combustion chamber wall push rod 500 has substantially the shape of a cylinder and is formed with a lower slot 510. Lower slot 510 is sized to fit over a portion of combustor wall 310. An upper slot 520 is vertically disposed opposite to the lower slot 510 and has a through hole 525. The through hole 525 is disposed in alignment with the through hole 414 of the holder 412. A suitable fastener (e.g., a pin and split pin) may be used to secure the push rod 510 to the bracket 412. After the combustor wall push rod 500 is connected to the bracket 412, it is pivotally rotatable about an axis that is collinear with the pin that traverses the holes 414 and 525. The combustor wall push rod 500 may be made of any material that withstands the stresses encountered during use of the tool; usually, but not limited to, steel, steel alloys, aluminum, aluminum alloys, combinations thereof, or any other material.
    FIG. 6 illustrates a perspective view of a combustor wall hook 600 that may be used in conjunction with the handle 410 to facilitate extraction of the combustor wall 310 during removal. The hook 600 is attached to a mounting block 610 by means of a pin 615. The block is fixed to the holder 412 by means of a pin 625. The hook is pivotally mounted about two axes defined by pin 615 and pin 625. The hooks may be applied under a projecting combustor wall stop 360 to facilitate removal of the combustor wall 310. All of the pins used in conjunction with the various aspects of the present invention can be secured in place by a split pin and / or a stop integrally formed on one side of the pin, preventing the pin from sliding entirely through the hole. Of course, the pin and the split pins may be replaced by any other fastening means, such as, but not limited to, spring splitters, nuts and / or washers and circular split pins. The combustor wall hook 600 and the mounting block 610 may be made of any material that withstands the stresses encountered during use of the tool; usually, but not limited to, steel, steel alloys, aluminum, aluminum alloys, combinations thereof, or any other material.
    Fig. 7 illustrates a perspective view of an alignment guide 700 according to one aspect of the present invention. The alignment guide 700 is clamped to the flange 381 of the combustor housing 380 and serves to introduce the projecting combustor wall stop 360 into the receiving combustor wall stop 370. The alignment guide includes a clamp 710 and an adjustment screw 720 that secure the alignment guide to the flange 381. A cover plate 730 may be formed with a window 735 that may be used to position the clamp over alignment marks provided on the flange 381. A guide plate 740 has a guide 742 sized to receive at least a portion of the projecting combustor wall stop 360. The projecting combustor wall stop 360 slides along this guide 742. The guide 742 is flared at the top or entry point to facilitate insertion of the projecting combustor wall stop 360. The lower end of the guide 742 transitions into the cavity 744, which is sized to receive the receiving combustion chamber wall stop 370. In some applications, the protruding and receiving stops may be reversed. That is, the protruding stopper may be disposed on the combustion chamber housing, and the receiving stopper may be disposed on the combustion chamber wall. In these applications, the alignment guide is constructed in correspondence. For example, the guide 742 could be configured to receive and guide a female stop, and the cavity 744 could be configured to receive a projecting stop.
    Fig. 8 shows a perspective view of the combustion chamber housing 380 and the combustion chamber wall 310 with the handle 410 and the clamp 445 of FIG. 4, the combustion chamber wall push rod 500 of FIG. 5, and the alignment guide 700 of FIG. 7, for an installation process is fixed and positioned according to an embodiment of the present invention. The clamp 445 may be secured to the flange 381, and the pin 435 of the handle 410 is inserted into one of the recesses on the clamping tower 440. For the installation of a combustion chamber wall 310, a combustion chamber wall push rod 500 can be attached to the support 412. The alignment guide 700 is positioned over a receiving combustor wall stop 370 and secured to the flange 381. The lower groove or slot formed in the combustion chamber wall push rod may be applied over the edge of the combustion chamber wall 310. A user is then able to apply pressure to the handle 410 by gripping the handle 420 and can push the combustion chamber wall 310 in place. The lever action provided by the pivot point of the pin 435 allows a large force to be exerted with a moderate effort of the user, resulting in a smooth and consistent operation. Another advantage is the avoidance of shock loads of the combustion chamber wall 310 by hammering. For clarity, only two projecting combustion chamber wall stops 360 are shown. However, it will be understood that combustor walls may have any suitable number of combustor wall stops.
    In the following, a method for installing a combustion chamber wall in a combustion chamber housing a turbine according to an embodiment of the present invention will be described. The method includes the steps of providing an alignment guide 700 for aligning a stop of the combustion chamber wall with a stop on the combustion chamber housing. An attaching step attaches the alignment guide 700 to the combustion chamber housing. A step of insertion at least partially introduces the combustion chamber wall into the combustion chamber housing. An elongate stem assembly (410, 412, 420, 430, 435), a combustor wall push rod 500, and a tower clamp assembly (440, 445, 447, 449) are provided, and the tower clamp assembly is attached to the combustor housing. The combustor wall push rod 500 is attached to the elongated handle assembly and the elongate handle assembly is attached to the tower clamp assembly. A groove 510 formed in the combustion chamber wall push rod is positioned over a portion of the combustion chamber wall and the combustion chamber wall is installed in the combustion chamber housing by applying force to the elongated stem assembly.
    In the following, a method for removing a arranged in a combustion chamber housing combustion chamber wall of a turbine according to an embodiment of the present invention will be described. The method includes the steps of providing an elongate stem assembly (410, 412, 420, 430, 435), a combustor wall hook 600, and a clamp turner assembly (440, 445, 447, 449), attaching the clamp turner assembly to the combustor casing, attaching the combustor wall hook 600 on the elongate stem assembly, and attaching the elongated stem assembly to the clamp turner assembly. The combustor wall hook 600 is positioned behind a stop of the combustor wall, and the combustor wall is at least partially removed from the combustor shell by applying force to the elongated shaft assembly.
    Provided is a method and apparatus for removing and installing combustor walls 310 in a combustor housing 380 of a turbine. The device comprises an elongated handle 410 having two ends, wherein a first U-shaped holder 430 with a hole for receiving a pin 435 and a second holder 412 are secured to the elongate stem 410, and wherein the first U-shaped holder 430 at one of the two ends is arranged. A clamp turner assembly 440, 445, 447, 449 having a tower clamp 445 adapted to be attached to a flange 381 of a combustor casing 380 and a tower clamp portion 440 formed with a number of recesses about the pin 435 of the elongated stem 410 record.
    LIST OF REFERENCE NUMBERS
    [0027]<Tb> 10 <September> Turbine System<Tb> 12 <September> fuel nozzles<Tb> 14 <September> fuel supply<Tb> 16 <September> combustion chamber<Tb> 17 <September> blades<Tb> 18 <September> Turbine<Tb> 19 <September> blades<tb> 20 <SEP> Outlet to the outside<Tb> 21 <September> wave<Tb> 22 <September> wave<Tb> 24 <September> compressor<Tb> 26 <September> air intake<Tb> 28 <September> Last<Tb> 310 <September> combustion chamber wall<Tb> 315 <September> combustion chamber<Tb> 320 <September> flow sleeve<Tb> 330 <September> transition piece<tb> 335 <SEP> inner cavity<Tb> 340 <September> impingement sleeve<Tb> 350 <September> sealing tires<tb> 360 <SEP> projecting combustion chamber wall stop<tb> 370 <SEP> receiving combustion chamber wall stop<Tb> 380 <September> combustion chamber housing<Tb> 381 <September> flange<Tb> 410 <September> stalk<Tb> 412 <September> bracket<Tb> 414 <September> Loch<Tb> 420 <September> handle<tb> 430 <SEP> U-shaped bracket<Tb> 435 <September> pen<tb> 440 <SEP> terminal tower arrangement, terminal tower section, tower arrangement<Tb> 445 <September> clamp base<Tb> 447 <September> Bolt<Tb> 449 <September> button<Tb> 500 <September> combustion chamber wall push rod<Tb> 510 <September> slot<Tb> 520 <September> slot<Tb> 525 <September> Loch<Tb> 600 <September> Hook<Tb> 610 <September> mounting block<Tb> 615 <September> pen<Tb> 625 <September> pen<Tb> 700 <September> alignment guide<Tb> 710 <September> Terminal<Tb> 720 <September> Bolt<Tb> 730 <September> cover plate<Tb> 735 <September> Window<Tb> 740 <September> guide plate<Tb> 742 <September> Leadership<Tb> 744 <September> cavity
    权利要求:
    Claims (10)
    [1]
    An apparatus for removing and installing combustor walls (310) in a combustor shell (380) of a turbine, the apparatus comprising:a stem assembly (410, 412, 420, 430) having an elongated handle (410) with two ends, a first U-shaped holder (430) having a hole for receiving a pin (435) and a second holder (412) the elongated stem (410) are fixed, and wherein the first U-shaped holder (430) is arranged at one of the two ends,a clamp turner assembly (440, 445, 447, 449) having a clamp body (445) for attachment to a flange (381) of the combustor housing (380), the clamp turner assembly (440, 445, 447, 449) having a clamp tower portion (440), having a plurality of recesses for receiving the pin (435).
    [2]
    The apparatus of claim 1, wherein the elongate stem (410) and the clamping turner assembly (440, 445, 447, 449) are made of a material comprising at least one of the following materials:Steel, steel alloys, aluminum, aluminum alloys or a combination thereof.
    [3]
    3. Apparatus according to claim 1, further comprising:a combustor wall push rod (500) having an elongate groove (510) at one end, the elongated groove (510) having a size suitable to fit over a portion of an edge of the combustor wall (310);wherein a second end of the push rod (500) is adapted to be attached to the second support (412) of the elongate shaft (410).
    [4]
    The apparatus of claim 3 wherein the combustor wall push rod (500) is made of a material comprising at least one of the following materials:Steel, steel alloys, aluminum, aluminum alloys or a combination thereof.
    [5]
    5. The apparatus of claim 1, further comprising:a combustion chamber wall hook (600) having a mounting block (610),wherein the combustion chamber wall hook (600) is adapted to be attached to the second support (412) of the elongated stem (410) and adapted to at least fit behind a portion of a stop of the combustion chamber wall (310).
    [6]
    6. The apparatus of claim 5, wherein the combustor wall hook (600) is made of a material comprising at least one material from the group comprising:Steel, steel alloys, aluminum, aluminum alloys or a combination thereof.
    [7]
    The device of claim 1, further comprising:an alignment guide (700) having a clamping device (710) adapted to be clamped to the flange (381) of the combustion chamber housing (380) and having a guide plate (740) with a groove (742) the groove (742) is adapted to receive at least a portion of a combustion chamber wall stop (370);whereby the groove (742) is arranged to facilitate alignment of the combustion chamber wall stop (370) and a combustion chamber housing stop (360) during installation of the combustion chamber wall (310).
    [8]
    8. The device of claim 7, wherein the alignment guide (700) is made of a material comprising at least one material of the following group:Steel, steel alloys, aluminum, aluminum alloys or a combination thereof.
    [9]
    9. A method of installing a combustion chamber wall (310) in a combustor shell (380) of a turbine by means of a device according to claims 1, 3 and 7, the method comprising:Providing the alignment guide (700) for aligning a stop (360) of the combustion chamber wall (310) with a stop (370) on the combustion chamber housing (380);Attaching the alignment guide (700) to the combustor housing (380);Inserting the combustion chamber wall (310) at least in part into the combustion chamber housing (380);Providing the elongate stem assembly (410, 420, 412, 430), the combustor wall push rod (500), and the clamp turner assembly (440, 445, 447, 449);Attaching the clamp turner assembly (440, 445, 447, 449) to the combustor housing (380);Attaching the combustor wall push rod (500) to the elongate handle assembly (410, 412, 420, 430);Attaching the elongate stem assembly (410, 412, 420, 430) to the clamp turner assembly (440, 445, 447, 449);Positioning the groove (510) formed in the combustion chamber wall push rod (500) over a portion of the combustion chamber wall (310);wherein the combustion chamber wall (310) is installed in the combustion chamber housing (380) by applying a force to the elongate stem assembly (410, 412, 420, 430).
    [10]
    A method of expanding a combustor wall (310) in a combustor shell (380) of a turbine by means of a device according to claims 1 and 5, said method comprising the steps of:Providing the elongate stem assembly (410, 412, 420, 430), the combustor wall hook (600), and the clamp turner assembly (440, 445, 447, 449);Attaching the clamp turner assembly (440, 445, 447, 449) to the combustor housing (380);Attaching the combustor wall hook (600) to the elongated handle assembly (410, 412, 420, 430);Attaching the elongate stem assembly (410, 412, 420, 430) to the clamp turner assembly (440, 445, 447, 449);Positioning the combustor wall clevis (600) behind a stop (360) of the combustor wall (310);wherein the combustion chamber wall (310) is at least partially removed from the combustion chamber housing (380) by applying a force to the elongate stem assembly (410, 412, 420, 430).
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    同族专利:
    公开号 | 公开日
    CN101905454B|2015-09-09|
    JP2010281317A|2010-12-16|
    CN101905454A|2010-12-08|
    JP5575546B2|2014-08-20|
    US20100307000A1|2010-12-09|
    CH701187A2|2010-12-15|
    CH701187A8|2011-02-15|
    US8276253B2|2012-10-02|
    DE102010017041A1|2010-12-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4074411A|1977-04-29|1978-02-21|Willard David A|Ring removing wrench|
    US4528735A|1984-03-27|1985-07-16|Eastridge Victor R|Tire tool|
    US5274991A|1992-03-30|1994-01-04|General Electric Company|Dry low NOx multi-nozzle combustion liner cap assembly|
    US5323600A|1993-08-03|1994-06-28|General Electric Company|Liner stop assembly for a combustor|
    US5499795A|1995-01-20|1996-03-19|Mathews; Mitchell L.|Post remover|
    JP3382746B2|1995-02-06|2003-03-04|三菱重工業株式会社|Inner tube removal insertion tool|
    JP3614976B2|1995-04-06|2005-01-26|株式会社東芝|Gas turbine disassembly and assembly equipment|
    JPH10196959A|1997-01-08|1998-07-31|Toshiba Corp|Gas turbine burner|
    JPH10231737A|1997-02-18|1998-09-02|Tokyo Electric Power Co Inc:The|Gas turbine combustor disassembling/assembling supporting device|
    US6279313B1|1999-12-14|2001-08-28|General Electric Company|Combustion liner for gas turbine having liner stops|
    US6345441B1|2000-07-18|2002-02-12|General Electric Company|Method of repairing combustion chamber liners|
    US7086232B2|2002-04-29|2006-08-08|General Electric Company|Multihole patch for combustor liner of a gas turbine engine|
    CN2550135Y|2002-06-19|2003-05-14|青岛港务局|Special tool for dismantling internal combustion engine gas valve|
    US7093440B2|2003-06-11|2006-08-22|General Electric Company|Floating liner combustor|
    US6923002B2|2003-08-28|2005-08-02|General Electric Company|Combustion liner cap assembly for combustion dynamics reduction|
    US7040096B2|2003-09-08|2006-05-09|General Electric Company|Methods and apparatus for supplying feed air to turbine combustors|
    US6951109B2|2004-01-06|2005-10-04|General Electric Company|Apparatus and methods for minimizing and/or eliminating dilution air leakage in a combustion liner assembly|
    US7010921B2|2004-06-01|2006-03-14|General Electric Company|Method and apparatus for cooling combustor liner and transition piece of a gas turbine|
    US7360364B2|2004-12-17|2008-04-22|General Electric Company|Method and apparatus for assembling gas turbine engine combustors|
    US7836569B2|2007-01-09|2010-11-23|Gm Global Technology Operations, Inc.|Tire pressure monitor installation tool|
    CN201079900Y|2007-07-09|2008-07-02|沈阳飞机工业（集团）有限公司|Bushing dismounting device|
    CN201208734Y|2008-03-17|2009-03-18|上海宝钢设备检修有限公司|Mounting tools for rubber seal strip of butterfly valve seat|
    CN101362286B|2008-09-26|2010-06-09|广东四会实力连杆有限公司|Connecting rod bushing press-loading device and method|US8713776B2|2010-04-07|2014-05-06|General Electric Company|System and tool for installing combustion liners|
    JP5342532B2|2010-10-05|2013-11-13|三菱重工業株式会社|Manufacturing method of body frame|
    KR101192123B1|2011-01-04|2012-10-16|한전케이피에스 주식회사|Assemble or Disassemble Jig for a Gas Turbine Combustion Liner Cap|
    TR201102511A2|2011-03-16|2012-10-22|General Electric Company|Combustion chamber liner and flow sleeve tool.|
    US8407892B2|2011-08-05|2013-04-02|General Electric Company|Methods relating to integrating late lean injection into combustion turbine engines|
    US9243507B2|2012-01-09|2016-01-26|General Electric Company|Late lean injection system transition piece|
    US9631812B2|2013-03-18|2017-04-25|General Electric Company|Support frame and method for assembly of a combustion module of a gas turbine|
    US9527173B2|2013-05-14|2016-12-27|Siemens Energy, Inc.|Alignment tool for use in aligning openings in structural members|
    US9321137B1|2013-07-08|2016-04-26|Norfolk Southern Corporation|Tool and method for seating engine pistons|
    WO2015156691A1|2014-04-09|2015-10-15|General Electric Company|Method and apparatus for servicing combustion liners|
    FR3022613B1|2014-06-24|2019-04-19|Safran Helicopter Engines|BOSSAGE FOR COMBUSTION CHAMBER.|
    JP6466720B2|2015-01-22|2019-02-06|中電プラント株式会社|Stator block mounting jig|
    US10088167B2|2015-06-15|2018-10-02|General Electric Company|Combustion flow sleeve lifting tool|
    US10208627B2|2015-12-10|2019-02-19|General Electric Company|Combustor assembly lift systems|
    US10704421B2|2016-12-02|2020-07-07|General Electric Company|Combustion liner tool|
    EP3354985B1|2017-01-27|2020-11-25|General Electric Company|Combustion can maintenance apparatus and method|
    CN108637961A|2018-05-15|2018-10-12|潘新凤|A kind of car sound equipment control panel disconnecting apparatus|
    CN110076727B|2019-04-15|2021-07-30|台州澳文机电有限公司|Force-resisting fastening piston type compressor air valve dismounting tool|
    法律状态:
    2011-02-15| PK| Correction|Free format text: ERFINDER BERICHTIGT. |
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    优先权:
    申请号 | 申请日 | 专利标题
    US12/477,451|US8276253B2|2009-06-03|2009-06-03|Method and apparatus to remove or install combustion liners|
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