• 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:
    The present invention provides a method for mounting lip seals (170) in a sleeve assembly (265) of a fuel nozzle (100). The method includes the steps of inserting a first lip seal (320) along a second diameter tube (290) until the first lip seal (320) contacts a first tube flange (310) of a first diameter tube (280) insertion a seal spacer (270) along the second diameter tube (290) until the seal spacer (270) contacts the first lip seal (320) and inserting a second lip seal (350) along the second diameter tube (290); until the second lip seal (350) contacts the seal spacer (270), the seal spacer (270) being disposed between the first lip seal (320) and the second lip seal (350), and wherein an outer diameter of the second lip seal (350) is equal to the outer diameter the first lip seal (320).
    公开号:CH702102B1
    申请号:CH01658/10
    申请日:2010-10-11
    公开日:2016-02-29
    发明作者:Lucas John Stoia；Karthik Subramanian
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Technical area
    The present invention relates generally to gas turbine plants, and more particularly to a method of mounting lip seals disposed about fuel nozzle tubes in a sleeve arrangement.
    Background of the invention
    Gas turbine combustors generally use a number of fuel nozzles disposed about an end cover. Given the possibility of large temperature variations between the various inner channels of the fuel nozzles, a different axial thermal expansion of the channels can be a constructive challenge, especially in transient operation. For example, different channels may contain fluids of different temperature, or different channels may be constructed of materials having different thermal expansion coefficients. In addition, the channels may generally take the form of concentric tubes. These concentric tubes should have a support and vibration damping.
    Known fuel nozzles have generally used bellows or piston rings as seals between the concentric tubes. The use of bellows, however, is relatively costly and can raise questions about durability. Likewise, the use of piston rings can allow significant leakage flow therethrough. Accordingly, in particular between two channels with a high differential pressure between them can result in high leakage fluctuations and lead to undesirable combustion properties.
    It has been found that lip seals offer improved sealing performance compared to the known piston rings. The lip seals may be disposed at one end about and captured by a tube end flange welded to the end of a tube of a sleeve assembly and enclosed at a second end by a counterbore in the fuel nozzle body. Although this method may be effective, subsequent seals must be of an alternately reduced size to allow for mounting and confining the seal in both directions. For fuel nozzles that require multiple seals, there may be too little room in the radial direction to apply this procedure to all required seals.
    Therefore, there is a desire for an improved method of mounting lip seals on fuel nozzle tubes and properly fitting them in place. The use of lip seals instead of piston rings is intended to improve the seal between different nozzle circuits and, accordingly, to improve overall emissions and performance.
    Summary of the invention
    The present application accordingly provides a method for mounting lip seals in a sleeve arrangement of a fuel nozzle, according to claim 1. A corresponding method for disassembly according to claim 11 is also provided.
    The invention further provides a sleeve assembly according to claim 12.
    These and other features of the present application will become apparent to those skilled in the art upon review of the following detailed description taken in conjunction with the several drawings and the appended claims.
    Brief description of the invention
    [0009]<Tb> FIG. 1 <SEP> is a partially sectioned view of a gas turbine plant as could be used herein.<Tb> FIG. Figure 2 is a side view of a portion of a secondary nozzle as might be used herein.<Tb> FIG. 3 <SEP> is a rotated cross-sectional view across the end cap of the secondary nozzle of FIG. 2.<Tb> FIG. Figure 4 is a side sectional view of a number of concentric tubes with lip seals as described herein.<Tb> FIG. Figure 5 is a side cross-sectional view of a lip seal that may be used with a tube assembly.<Tb> FIG. FIG. 6 is a perspective view of a seal spacer and a number of lip seals mounted on tubes of a sleeve assembly as described herein. FIG.<Tb> FIG. Figure 7 is a side sectional view of an alternative embodiment of a tube assembly as described herein disposed in an end cap.
    Detailed description of the invention
    Referring now to the drawings wherein the same numerals indicate the same elements throughout the several views: FIG. 1 shows parts of a gas turbine plant 10 having a compressor 12 (also partially shown), a combustor 14, and a turbine section 16; which is illustrated here by a single blade. Although not shown in detail, the turbine 16 is connected to the compressor 12 along a common axis. The compressor 12 compresses an incoming air flow and supplies the air to the combustion chamber 14. The combustor 14 mixes the compressed air stream with a compressed fuel stream and ignites the mixture. Although only a single combustor 14 is shown, the gas turbine engine 10 may include any number of combustors 14. The combustors 14 may be disposed in an annular array about the axis of the gas turbine plant 10.
    The hot combustion gases are in turn supplied to the turbine 16. The hot combustion gases drive the turbine 16 to perform mechanical work. The mechanical work generated by the turbine 16 drives the compressor 12 and generally an external load such as an electric generator and the like. The gas turbine plant 10 may use natural gas, various types of syngas, or other types of fuel. The gas turbine engine 10 is exemplary only and could have other configurations herein and use other types of components.
    A transition duct 18 may connect the outlet end of each of the combustors 14 to the inlet end of the turbine 16 to supply the hot combustion gases thereto. Each combustion chamber 14 may include a primary or upstream combustion chamber 20 and a secondary or downstream combustion chamber 22, which are generally separated by a throat region 24. The combustor 14 may be surrounded by a combustor flow sleeve 26 to direct the compressor exhaust airflow to the combustor 14. The combustion chamber 14 may further be surrounded by an outer housing 28 which may be bolted to or otherwise secured to a turbine housing 30. The combustor 14 may further include a number of primary nozzles 32 for supplying fuel to the primary combustion chamber 20. The primary nozzles 32 may be arranged in an annular array around a central secondary nozzle 34. The ignition may be effected in the combustion chamber 14 by means of a spark plug 36 in conjunction with a number of transverse fire tubes 38, only one of which is shown. The secondary nozzle 34 may supply fuel to the secondary combustion chamber 22. However, other configurations and configurations could be used herein.
    Figures 2 and 3 show a secondary nozzle 100 as described herein. The secondary nozzle 100 may include a number of concentric tubes 110. The concentric tubes 110 may form any number of channels therethrough. The concentric tubes 110 may include a central channel 120. The central channel 120 could be a liquid fuel channel in communication with a number of nozzle pegs 130. A number of secondary channels 140 may surround the central channel 120. The secondary channels 140 may include pilot gas, secondary gas and tertiary gas channels, water purging channels, airflow channels and channels for other types of fluid flows.
    The concentric tubes 110 may be attached to an end cover 150 at one end. The end cap 150 may include a number of spacer flow openings 155 and fuel or air ducts 165 therethrough. The concentric tubes 110 may extend to a nozzle tip 160 at the other end. Any number of secondary channels 140 and / or concentric tubes 110 may be used herein. However, other configurations and configurations could be used herein.
    FIG. 4 shows an example of the concentric tubes 110 of the secondary nozzle 100. As shown, a number of secondary channels 140 surround the central channel 120. Between pairs of concentric tubes 110, a number of lip seals 170 may be disposed. The lip seal 170 is a form of radial seal that reduces fuel leakage therethrough. The lip seal 170 may also be disposed between the concentric tubes 110 and the end cap 150.
    The lip seals 170 are typically used on rotating shafts. Generally described, the lip seal 170 seals by seating on a shaft that compresses the inner diameter and in a bore that compresses the outer diameter. In a typical application to a rotating shaft, the inner diameter would be considered the dynamic side of the seal because the shaft rotates relative to the stationary lip seal. The design of the seal relies on compression to produce a normal force on the inner and outer seal surfaces.
    FIG. 5 shows a side view of an example of the lip seal 170. The lip seal 170 may include an arcuate portion 180, an outer seal line 190, and an inner seal line 200. The lip seal 170 may have an inwardly facing camber or crimp 210 at one end of the arcuate portion 180 to form a rebate 220 at a first edge 230. The lip seal 170 may also include an inwardly tapered frusto-conical portion or a longitudinally extending portion 240 that terminates in an outwardly curved portion 250 at the second opposing edge 260. The function of the recess 220 is to provide a stiffener and a guide that facilitates the smooth insertion of the seal 170 into an internal cavity. Other configurations and configurations could be used herein. The lip seal 170 may be made of nickel superalloys, nickel cobalt alloys, and similar materials.
    In the present application, the lip seals 170 provide thermal expansion such that the lip seals 170 permit axial sliding along the inner diameter or inner arch 210 while maintaining the seal. The lip seal 170 is generally a metallic radial spring. Because the lip seal 170 is a full circumferential spring seal, the lip seal 170 also increases the natural frequencies of the nozzle components away from the excitation sources. The improved seal also reduces variations in pilot or pilot gas flow due to channel-to-channel leakage in ultra-low-emission combustors. This is important to accurately control the low pilot fuel flow rate. In addition, lip seals 170 may allow higher concentrations of H2 and other types of highly reactive fuels with acceptable leakage for greater fuel flexibility. The leakage on the known piston ring generally sets much narrower limits on the acceptable levels of highly reactive fuels.
    Fig. 6 shows an example of a sleeve assembly 265 for use with the fuel nozzle 100. The sleeve assembly 265 includes a seal spacer 270 as described herein. In this example, three secondary smaller diameter channels 140 are shown, a first tube 280, a second tube 290, and a third tube 300. The tubes 280, 290, 300 may have any desired decreasing diameters. Any number of tubes 280, 290, 300 may be used herein.
    The first tube 280 may have a flanged end 310. One of the lip seals 170, a first lip seal 320 may be pushed onto the second tube 290 with compression / decompression of the inside diameter 210 and recompressed on the first tube 280 and secured around the flange end 310 on the second tube 290. The seal spacer 270 may then be slid over the second tube 290 and brought into contact with the first seal 320. The second tube 290 lacks a flanged end. The seal spacer 270 may include an adjustment screw 330 or other type of connecting means to hold the spacer 270 in place. The second tube 290 may have recesses machined therein to allow the adjustment screw 330 to protrude from the surface of the recess without leaving burrs that engage the seals 170 during assembly or disassembly. Any number of adjustment screws 330 may be used. The seal spacer 270 also has a number of flow openings 340 to allow fluid flow therethrough with negligible pressure drop. Any number, size or shape of the flow openings 340 may be used. The seal spacer may be made of stainless steel or similar types of materials.
    A second lip seal 350 may thereafter be inserted until the inner diameter 210 compresses and the seal is disposed in place on the second tube 290 adjacent to the spacer 270. The compression holds the second lip seal 350 in place. The third tube 300 may also have a flanged end 360. A third lip seal 370 may be inserted over the third tube 300 until the inner diameter 210 is compressed and the seal 370 is disposed on the flanged end 360. The compression also holds the third lip seal 370 in place. The tubes 280, 290, 300 and sleeve assembly 265 may then be disposed as a whole in the fuel nozzle 100.
    The use of the seal spacer 270 and method of incorporation thus allows the use of multiple lip seals of the same size for a better seal between the tubes 280, 290, 300. The advantages of this improved seal may be lower pilot fluc- tuations belong. By reducing these fluctuations, the pilot fuel flow of the nozzle can be further reduced than is currently possible to achieve lower emissions and fuel flexibility before reaching an operational limit. Another advantage could be the avoidance of secondary fuel leakage into the tertiary channel, which could result in burning within the nozzle 100 and subsequent damage to the component.
    In summary, the first seal 320 is inserted along the second tube 290 with compression / decompression until it contacts the flange end 310. The seal spacer 270 is then slid along the second tube 290 until it is close to the first seal 320, and thereafter may be bolted or otherwise secured in place on the second tube 290. Thereafter, the second seal 350 may be inserted along the second tube 290 until the inner diameter 210 is compressed and the second seal is in contact with the seal spacer 270. The inner diameter 210 of the third lip seal 370 may then be compressed, and the seal 370 may be disposed along the third tube 300 and in contact with the flange end 360. The tubes 280, 290, 300 may then be disposed in the fuel nozzle 100. The seals 320, 350, 370 and the spacer 270 can be removed in the reverse order.
    FIG. 7 shows an alternate embodiment of a ferrule assembly 400 that may be used with the end cap 150 of the fuel nozzle 100. In this example, three secondary channels of progressively smaller diameter are shown, a first tube 410, a second tube 420 and a third tube 430. The tubes 410, 420, 430 may have any desired decreasing diameters. Any number of tubes 410, 420, 430 could be used herein. The first tube 410 may terminate in a first tube flange 440. Likewise, the second tube 420 may terminate in a second tube flange 450. A first lip seal 460 may be disposed about the first tube flange 440 while a second lip seal 470 may be disposed about the second tube flange 450. The first and second lip seals 460, 470 may be disposed on a first side 480 of the end cover 150.
    A third lip seal 490 may be disposed around the third tube 430. The third tube 430 may be formed without a flange on it. Rather, the third lip seal 490 can be held by a sealing collar 500 in position. The sealing collar 500 may extend along a third tube 430 from a second side 510 of the end cap 150.
    In use, the first lip seal 406 may be disposed about the first tube flange 440 of the first tube 410, while the second lip seal 470 may be disposed about the second tube flange 450 of the second tube 420. The sleeve assembly 400 may thereafter be disposed on the first side 480 of the end cap 150. The lip seals 460, 470 may be held in place against the tube flanges 440, 450 and end cap 150 themselves.
    Once the sleeve assembly 400 is disposed on the first side 480 of the end cover 150, the third lip seal 490 may be disposed about the second side 510 of the end cover 150 about the third tube 430. The sealing collar 500 may thereafter be disposed on the second side 510 of the end cover 150 against the third seal 490. However, other configurations could be used herein.
    It should be understood that the foregoing relates to particular embodiments of the present application only and various changes and modifications could be made thereto by those skilled in the art without departing from the invention as defined by the following claims and their equivalents ,
    The present invention provides a method of mounting lip seals 170 in a sleeve assembly 265 of a fuel nozzle 100. The method includes the steps of inserting a first lip seal 320 along a second diameter tube 290 until the first lip seal 320 has a first tube flange 310 contacts a tube 280 having a first diameter, inserting a seal spacer 270 along the second diameter tube 290 until the seal spacer 270 contacts the first lip seal 320, and inserting a second lip seal 350 along the second diameter tube 290; until the second lip seal 350 contacts the seal spacer 270, with the seal spacer 270 disposed between the first lip seal 320 and the second lip seal 350, and an outer diameter of the second lip seal 350 equal to the outer diameter of the first lip Termination 320 is.
    It is also possible to carry out the method by the steps of: disposing a first lip seal around a first tube flange of a first tube, disposing a second lip seal around a second tube flange of a second tube, disposing the sleeve assembly on a first side of the end cover to place a third lip seal around a third tube through a second side of the end cap and secure the third lip seal in place by a sealing collar.
    LIST OF REFERENCE NUMBERS
    [0031]<Tb> 10 'September> gas turbine plant<Tb> 12 <September> compressor<Tb> 14 <September> combustion chamber<Tb> 16 <September> Turbine<Tb> 18 <September> transition duct<tb> 20 <SEP> Primary combustion chamber<tb> 22 <SEP> Secondary combustion chamber<Tb> 24 <September> throat area<Tb> 26 <September> flow sleeve<tb> 28 <SEP> Outer case<Tb> 30 <September> turbine housing<Tb> 32 <September> primary nozzle<Tb> 34 <September> secondary nozzle<Tb> 36 <September> spark plug<Tb> 38 <September> cross fire tube<Tb> 100 <September> secondary nozzle<tb> 110 <SEP> Concentric Tubes<tb> 120 <SEP> Central Channel<Tb> 130 <September> pintle<Tb> 140 <September> secondary channel<Tb> 150 <September> end cover<Tb> 155 <September> Spacers flow opening<Tb> 160 <September> nozzle tip<tb> 165 <SEP> fuel or air duct<Tb> 170 <September> lip seal<tb> 180 <SEP> Arcuate section<tb> 190 <SEP> Outer sealing line<tb> 200 <SEP> Inner sealing line<Tb> 210 <September> vault<Tb> 220 <September> Return<tb> 230 <SEP> First edge<tb> 240 <SEP> Longitudinally extending section<tb> 250 <SEP> Outer curved section<tb> 260 <SEP> Second edge<Tb> 265 <September> sleeve assembly<Tb> 270 <September> seal spacer<tb> 280 <SEP> First tube<tb> 290 <SEP> Second tube<tb> 300 <SEP> Third tube<Tb> 310 <September> flange<tb> 320 <SEP> First seal<Tb> 330 <September> adjustment<Tb> 340 <September> flow opening<tb> 350 <SEP> Second Seal<Tb> 360 <September> flange<tb> 370 <SEP> Third Seal<Tb> 400 <September> sleeve assembly<tb> 410 <SEP> First tube<tb> 420 <SEP> Second tube<tb> 430 <SEP> Third Tube<tb> 440 <SEP> First tube flange<tb> 450 <SEP> Second tube flange<tb> 460 <SEP> First lip seal<tb> 470 <SEP> Second lip seal<tb> 480 <SEP> First Page<tb> 490 <SEP> Third lip seal<Tb> 500 <September> sealing collar<tb> 510 <SEP> Second page
    权利要求:
    Claims (11)
    [1]
    A method of mounting lip seals (170) in a sleeve assembly (265) of a fuel nozzle (100), comprising:Inserting a first lip seal (320) along a second diameter tube (290) until the first lip seal (320) contacts a first tube flange (310) of a first diameter tube (280);Inserting a seal spacer (270) along the second diameter tube (290) until the seal spacer (270) contacts the first lip seal (320); andInserting a second lip seal (350) along the second diameter tube (290) until the second lip seal (350) contacts the seal spacer (270), the seal spacer (270) between the first lip seal (320) and the second lip seal (350); 350), and wherein an outer diameter of the second lip seal (350) is equal to the outer diameter of the first lip seal (320).
    [2]
    The method of claim 1, wherein the step of inserting a first lip seal (320) along the second diameter tube (290) until the first lip seal (320) engages the first tube flange (310) of the tube (280) with the first tube seal (320) contacting first diameter, compressing an inner diameter (210) of the first lip seal (320).
    [3]
    The method of claim 1, wherein the step of inserting a second lip seal (350) along the second diameter tube (290) until the second lip seal (350) contacts the seal spacer (270) compresses an inner diameter ( 210) of the second lip seal (350).
    [4]
    The method of claim 1, further comprising inserting a third lip seal (370) along a third diameter tube (300).
    [5]
    The method of claim 4 wherein the third diameter tube (300) has a third tube flange (360) and the step of inserting a third lip seal (370) along the third diameter tube (300) comprises inserting the third one Lip seal (370) in contact with the third tube flange (360) contains.
    [6]
    The method of claim 4, wherein the step of inserting the third lip seal (370) along the third diameter tube (300) includes compressing an inner diameter (210) of the third lip seal (370).
    [7]
    7. The method of claim 4, wherein the tube (280) having the first diameter has an outer diameter which is larger than the outer diameter of the tube (290) with the second diameter, and the outer diameter of the tube (290) with the second diameter greater than the outer diameter of the third diameter tube (300).
    [8]
    The method of claim 1, further including the step of securing the seal spacer (270) in place along the second diameter tube (290).
    [9]
    The method of claim 1, wherein the seal spacer (270) has a number of flow openings (340) for directing fluid therethrough.
    [10]
    A method of disassembling the lip seals (170) mounted in accordance with the method of claim 1 in the sleeve assembly (265) of the fuel nozzle (100), which method comprises:Pushing the second lip seal (350) in contact with the seal spacer (270) along the second diameter tube (290);Pushing the seal spacer (270) in contact with the first lip seal (320) along the second diameter tube (290); andPushing the first lip seal (320) in contact with the first tube flange (310) of the first diameter tube (280) along the second diameter tube (290).
    [11]
    11. A ferrule assembly (265) for a fuel nozzle (100), the ferrule assembly comprising:a first tube (280) having a first outer diameter;a second tube (290) having a second outside diameter, the first outside diameter being larger than the second outside diameter;a first lip seal (320) disposed on the second tube (290) in contact with a first tube flange (310) of the first tube (280);a seal spacer (270) disposed on the second tube (280) in contact with the first lip seal (320); anda second lip seal (350) disposed on the second tube (290) in contact with the seal spacer (270), the seal spacer (270) disposed between the first lip seal (320) and the second lip seal (350), and wherein an outer diameter of the second lip seal (350) is equal to the outer diameter of the first lip seal (320).
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    同族专利:
    公开号 | 公开日
    CN102116477B|2015-09-23|
    US8662502B2|2014-03-04|
    CN102116477A|2011-07-06|
    JP2011085142A|2011-04-28|
    CH702102A2|2011-04-29|
    DE102010037844A1|2011-04-21|
    JP5685412B2|2015-03-18|
    US20110089267A1|2011-04-21|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-05-31| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/580,313|US8662502B2|2009-10-16|2009-10-16|Fuel nozzle seal spacer and method of installing the same|
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