• 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:
    A gas turbomachine (2) nozzle (62) includes a base portion (70) having a first fluid inlet (90) and a second fluid inlet (92), and an outlet portion (74) having one or more outlets (99). A connection section (78) fluidically connects the base portion (70) and the outlet portion (74). An orifice plug (110) is arranged in the base portion (70) at the second fluid inlet (92). The orifice plug (110) includes one or more openings (117) fluidically connecting the second fluid inlet (90) and the connection section (78).(Fig. 3)
    公开号:SE1551058A1
    申请号:SE1551058
    申请日:2015-08-04
    公开日:2016-02-13
    发明作者:David William Cihlar；Zhaoli Hu；Patrick Benedict Melton；Kevin Woodlock
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    [1] [0001] The subject matter disclosed herein relates to the art of turbomachines and, moreparticularly, to a nozzle having an orifice plug for a gas turbomachine.[0002] Turbomachines typically include a compressor portion and a turbine portion. The compressor portion forms a compressed air stream that is introduced into the turbine portion.In a gas turbomachine, a portion of the compressed air stream miXes With products ofcombustion forming a hot gas stream that is introduced into the turbine portion through atransition piece. The products of combustion are developed in a combustion chamber of acombustor. In the combustor, fuel and air may be passed through a nozzle to form acombustible miXture. The combustible miXture is combusted to form the products ofcombustion.
    [3] [0003] along the hot gas path. The airfoils are generally connected to a Wheel Which, in turn, may be The hot gas stream impacts turbomachine airfoils arranged in sequential stages connected to a rotor. Typically, the rotor is operatively connected to a load. The hot gasstream imparts a force to the airfoils causing rotation. The rotation is transferred to the rotor.Thus, the turbine portion converts thermal energy from the hot gas stream intomechanical/rotational energy that is used to drive the load. The load may take on a variety offorms including a generator, a pump, an aircraft, a locomotive or the like.
    [5] [0005] a compressor portion, a turbine portion operatively linked to the compressor portion, and a According to another aspect an eXemplary embodiment, a turbomachine includes combustor assembly fluidically connected to the compressor portion and the turbine portion.The combustor assembly includes at least one combustor having at least one nozzle. The atleast one nozzle includes a base portion having a first fluid inlet and a second fluid inlet, anoutlet portion having one or more outlets, a connection section fluidically connecting the baseportion and the outlet portion, and an orifice plug arranged in the base portion at the secondfluid inlet. The orifice plug includes one or more openings fluidically connecting the secondfluid inlet and the connection section.
    [6] [0006] system includes a compressor portion, a turbine portion operatively linked to the compressor According to yet another aspect of an eXemplary embodiment, a turbomachine portion, an inlet system fluidically connected to the compressor portion, a load operativelyconnected to one of the compressor portion and the turbine portion, and a combustor assembly fluidically connected to the compressor portion and the turbine portion. Thecombustor assembly includes at least one combustor having at least one nozzle. The at leastone nozzle includes a base portion having a first fluid inlet, a second fluid inlet, an outletportion having one or more outlets, a connection section fluidically connecting the baseportion and the outlet portion, and an orifice plug arranged in the base portion at the secondfluid inlet. The orifice plug includes one or more openings fluidically connecting the secondfluid inlet and the connection section.
    [7] [0007] following description taken in conjunction with the drawings.
    [9] [0009] having a nozzle provided with an orifice plug, in accordance with an exemplary embodiment;
    [10] [0010] FIG. 1 is a schematic view of a turbomachine system including a combustor FIG. 2 is a partial cross-sectional view of the combustor and nozzle of FIG. 1;
    [11] [0011] FIG. 3 is a partial cross-sectional view of the nozzle of FIG. 2; and
    [12] [0012] FIG. 4 is a partial perspective axially end cross-sectional view of the nozzle ofFIG. 3.
    [13] [0013] The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.DETAILED DESCRIPTION OF THE INVENTION[0014] generally at 1. Turbomachine system 1 includes a turbomachine 2 having a compressor With initial reference to FIGs. 1 and 2, a turbomachine system is indicated portion 4 connected to a turbine portion 6 through a combustor assembly 8 including at leastone combustor 9. Compressor portion 4 is also connected to turbine portion 6 via a commoncompressor/turbine shaft 10. An air inlet system 12 is fluidically connected to an inlet (notseparately labeled) of compressor portion 4. A load, indicated generally at 14, is operativelyconnected to turbine portion 6. Load 14 may take on a variety of forms including generators,pumps, locomotive systems, and other driven loads. Turbine portion 6 may also be connectedto an exhaust system (not shown).
    [15] [0015] 24 that are coupled in fluidic communication with each other and combustor assembly 8.
    [16] [0016] combustor liner 36. As shown, combustor liner 36 is positioned radially inward from Combustor 9 includes a combustor body 30 having a combustor cap 33 and a combustor body 30 so as to define a combustion Chamber 38. Combustion chamber 38eXtends from a head end 39 to a compressor discharge 40. Combustor liner 36 may be spacedfrom combustor body 30 forming a compressor discharge casing (CDC) airflow passage 43.A transition piece 45 connects combustor assembly 8 to turbine portion 6. Transition piece 45channels combustion gases generated in combustion chamber 38 downstream towards a firststage 46 of turbine portion 6. Transition piece 45 may include an inner wall 48 and an outerwall 49 that define an annular passage 54 that fluidically connects with CDC airflow passage43. Inner wall 48 may also define a guide cavity 56 that eXtends between combustionchamber 38 and turbine portion 6. A nozzle assembly 60 is arranged at head end 39 ofcombustor liner 36. Nozzle assembly 60 includes one or more nozzles, such as indicated at62.
    [17] [0017] joined by a connection section 78. In accordance with an aspect of an eXemplary As shown in FIG. 3, nozzle 62 includes a base portion 70 and an outlet portion 74 embodiment, base portion 70 includes a base surface 82 defined by an outer, annular edge 84.Base surface 82 includes a first fluid inlet 90 and a second fluid inlet 92. First fluid inlet 90fluidically connects to a first passage 94 that eXtends centrally from base portion 70 to outletportion 74 through connection section 78. Second fluid inlet 92 fluidically connects with asecond passage 96 that eXtends from base portion 70 to outlet portion 74 through connectionsection 78. Second passage 96 is arranged radially outwardly of first passage 94. First andsecond passages 94 and 96 lead to one or more outlets 99 (FIG. 2) formed in outlet portion 74.While shown as a flange, it should be understood that base portion 70 may be definedanywhere along nozzle 62 that may support second fluid inlet 92 and provide access to secondpassage 96.
    [18] [0018] 110 provided in an orifice plug receiving zone 114 formed in base portion 70. Orifice plug In accordance with an eXemplary embodiment, nozzle 62 includes an orifice plug 110 may be secured in orifice plug receiving zone 114 through a variety of methods includingbrazing, welding, staking, press-fitting and the like. Orifice plug 110 is inserted into anopening 117 formed in outer, annular edge 84. Orifice plug 110 includes a base section 124and a plug section 128 joined by an intermediate section 130. Base section 124 and plugsection 128 may include a first dimension while intermediate section 130 includes a seconddimension. The second dimension is less than the first dimension such as orifice plug 110includes an hourglass shaped geometry. Base section 124 includes a plurality of meteredopenings 134 that deliver a fluid from second fluid inlet 92 into second passage 96. The fluidmay mix with fluid passing through first passage 94 at outlet portion 74 and discharge intocombustion chamber 38 to be combusted.
    [19] [0019] an orifice plug that forms a secondary orifice for a turbomachine nozzle. Instead of being At this point, it should be understood that the eXemplary embodiments describe incorporated into an endcover, the orifice plug of the eXemplary embodiments is integrateddirectly into the nozzle. More specifically, the orifice plug is integrated into a base portion ofthe nozzle. In this manner, the orifice plug does not limit fuel flow or provide additional obstructions as compared to endcover mounted orifice plugs. Further, integrating the orificeplug into the nozzle eliminates the need for separate floW testing of the endcover assemblyand the nozzle assemblies. In addition, While shown as being mounted through an openingformed in an annular side Wall of the base portion, the orifice plug may be mounted into thebase portion through a variety of mechanisms. Further, it should be understood that Whileshown as having an hour-glass shape, orifice plug may include a variety of geometriesdepending upon installation and operational requirements. Still further, it should beunderstood that the orifice plug may be formed having a cylindrical, oval, teardrop or othershapes.
    [20] [0020] number of embodiments, it should be readily understood that the invention is not limited to While the invention has been described in detail in connection With only a limited such disclosed embodiments. Rather, the invention can be modified to incorporate anynumber of variations, alterations, substitutions or equivalent arrangements not heretoforedescribed, but Which are commensurate With the spirit and scope of the invention.Additionally, While various embodiments of the invention have been described, it is to beunderstood that aspects of the invention may include only some of the describedembodiments. Accordingly, the invention is not to be seen as limited by the foregoingdescription, but is only limited by the scope of the appended claims.
    权利要求:
    Claims (14)
    [1] 1. A gas turbomachine (2) nozzle (62) comprising:a base portion (70) including a first fluid inlet (90) and a second fluid inlet (92);an outlet portion (74) having one or more outlets (99); a connection section (78) fluidically connecting the base portion (70) and the outletportion (74); and an orifice plug (110) arranged in the base portion (70) at the second fluid inlet (92),the orifice plug (110) including one or more openings (117) fluidically connecting the secondfluid inlet (92) and the connection section (78).
    [2] 2. The gas turbomachine (2) nozzle (62) according to claim 1, Wherein theorifice plug (110) includes a base section (124), the one or more openings (117) being formedin the base section (124).
    [3] 3. The gas turbomachine (2) nozzle (62) according to claim 1, Wherein the baseportion (70) includes a base surface (82) defined by an annular, outer edge (84), the first andsecond fluid inlets (90 and 92) being formed in the base surface (82).
    [4] 4. The gas turbomachine (2) nozzle (62) according to claim 3, furthercomprising: an orifice plug receiving zone (114) having an opening (117) formed in the annular, outer edge (84).
    [5] 5. The gas turbomachine (2) nozzle (62) according to claim 4, Wherein theorifice plug (110) includes a base section (124) and a plug section (128) joined by anintermediate section (130), the plug section (128) eXtending into, and closing, the opening(117).
    [6] 6. The gas turbomachine (2) nozzle (62) according to claim 5, Wherein the basesection (124) and the plug section (128) include a first diameter and the intermediate section(130) includes a second diameter that is smaller than the first diameter.
    [7] 7. The gas turbomachine (2) nozzle (62) according to claim 1, furthercomprising: a first passage (94) eXtending from the base portion (70) to the outlet portion(74) through the connection section (78), the first passage (94) being fluidically connected tothe first inlet (90), and a second passage (96) eXtending from the base portion (70) to theoutlet portion (74) through the connection section (78), the second passage (96) beingfluidically connected to the second fluid inlet (92).
    [8] 8. The gas turbomachine (2) nozzle (62) according to claim 7, Wherein thesecond passage (96) is arranged radially outWardly of the first passage (94). 5
    [9] 9. A turbomachine (2) comprising:a Compressor portion (4);a turbine portion (6) operatively linked to the compressor portion (4); and a combustor assembly (8) fluidically connected to the compressor portion (4) and theturbine portion (6), the combustor assembly (8) including at least one combustor (9) having atleast one nozzle (62), the at least one nozzle (62) comprising: a base portion (70) including a first fluid inlet (90) and a second fluid inlet(92); an outlet portion (74) having one or more outlets (99); a connection section (78) fluidically connecting the base portion (70) and theoutlet portion (74); and an orifice plug (110) arranged in the base portion (70) at the second fluid inlet(92), the orifice plug (110) including one or more openings (117) fluidicallyconnecting the second fluid inlet (92) and the connection section (78).
    [10] 10. The turbomachine (2) according to claim 9, Wherein the orifice plug (110)includes a base section (124), the one or more openings (117) being formed in the basesection (124).
    [11] 11. The turbomachine (2) according to claim 9, Wherein the base portion (70)includes a base surface (82) defined by an annular, outer edge (84), the first and second fluidinlets (90 and 92) being formed in the base surface (84) and an orifice plug receiving zone(114) having an opening (117) formed in the annular, outer edge (84).
    [12] 12. The turbomachine (2) according to claim 11, Wherein the orifice plug (110)includes a base section (124) and a plug section (128) joined by an intermediate section (130),the plug section (128) eXtending into, and closing, the opening (117).
    [13] 13. The turbomachine (2) according to claim 9, further comprising: a firstpassage (94) eXtending from the base portion (70) to the outlet portion (74) through theconnection section (78), the first passage (94) being fluidically connected to the first inlet(90), and a second passage (96) eXtending from the base portion (70) to the outlet portion (74)through the connection section (78), the second passage (96) being fluidically connected to the second fluid inlet (92).
    [14] 14. The turbomachine (2) according to claim 13, Wherein the second passage (96)is arranged radially outWardly of the first passage (94).
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    法律状态:
    2018-06-05| NAV| Patent application has lapsed|
    优先权:
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    US14/457,505|US9546600B2|2014-08-12|2014-08-12|Nozzle having an orifice plug for a gas turbomachine|
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