• 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 turbomachine includes a compressor section and a turbine section operatively connected to the compressor section. The turbine section (8) includes a compressor outlet section (19), a hot gas path, and a first-stage nozzle (12) disposed on the hot gas path. A combustor assembly is fluidly connected to the compressor section. A transition piece has an inlet portion fluidly connected to the combustor assembly and an outlet portion fluidly connected to the turbine portion. A seal member (60) is operatively connected relative to one of the transition piece and the first stage nozzle (12) of the turbine section. The sealing member (60) extends from a first end (72) to a second cantilevered end (73) through an intermediate portion (75) containing one or more openings (80) that directs a clearance fluid flow path from the compressor outlet portion to the hot gas path provide.
    公开号:CH710372A2
    申请号:CH01587/15
    申请日:2015-11-02
    公开日:2016-05-13
    发明作者:Paul Wassynger Stephen；Timothy Brown Joe；Vedhagiri Sivaraman
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    STATE OF THE ART
    The subject matter disclosed herein relates to the field of turbomachinery systems, and more particularly to a variable purge flow seal employed between a transition piece and a turbine section of a turbomachine system.
    Turbomachine systems usually include a turbomachine connected to an intake system and a load. The turbomachine usually includes a compressor section and a turbine section. An airflow enters the compressor section through the intake system. The compressor section generates a stream of compressed air that is introduced into the turbine section. In a gas turbine engine, a portion of the compressed air stream mixes with combustion products in a combustor assembly to produce a hot gas stream that is introduced into the turbine section through a transition piece.
    The hot gas stream flows from a transition piece which connects the combustion chamber arrangement and the turbine section in terms of flow. The hot gases passing from the transition piece flow toward a first stage of the turbine section. The hot gases flow through a first stage nozzle before impinging on first stage buckets. The first stage nozzle conditions and directs the hot gases toward the first stage buckets. The hot gases expand through additional stages of the turbine section, each having associated blades, before the hot gases travel to an exhaust system. The blades are generally connected to an impeller, which in turn may be connected to a shaft. Usually, the shaft is effectively connected to a load. The hot gas stream imparts a force to the blades which causes rotation of the shaft. The rotation of the shaft is transmitted to the rotor. Thus, the turbine section converts heat energy from the hot gas stream into mechanical energy / rotational energy used to drive the load. The load may take a variety of forms, including that of a generator, a pump, an aircraft, a locomotive, or the like.
    BRIEF DESCRIPTION OF THE INVENTION
    In one aspect of an exemplary embodiment, a turbomachine includes a compressor section and a turbine section that is operatively connected to the compressor section. The turbine section includes a compressor outlet section, a hot gas path, and a first stage nozzle disposed on the hot gas path. With the compressor section, a combustion chamber arrangement is fluidly connected. A transition piece has an inlet portion fluidly connected to the combustor assembly and an outlet portion fluidly connected to the turbine portion. A seal member is operatively connected relative to one of the transition piece and the first stage nozzle of the turbine section. The sealing member extends from a first end to a second cantilevered end through an intermediate portion that includes one or more apertures that permit variable flushing fluid flow from the compressor outlet portion to the hot gas path.
    In the aforementioned turbomachine, the one or more openings may include a plurality of openings extending across the intermediate portion.
    The plurality of openings may have a plurality of circular openings.
    Alternatively, the plurality of openings may have a plurality of elongated openings.
    In addition, the plurality of openings may extend from a first end portion disposed at the first end to a second end portion disposed at the second cantilevered end.
    In one embodiment, the plurality of openings may extend through the second end.
    In the turbomachine of any kind mentioned above, the sealing member may be operatively connected relative to the transition piece.
    In particular, the transition piece may include a rear frame, wherein the sealing element is operatively connected to the rear frame.
    In an embodiment, the sealing member may include a mounting member disposed at the first end.
    In a further embodiment, the second end of the sealing member may be biased toward the other by the transition piece and the first stage nozzle of the turbine section.
    According to another aspect of an exemplary embodiment, a turbomachine system includes a compressor section including an inlet, an intake system fluidly connected to the inlet of the compressor section, and a turbine section operatively connected to the compressor section. The turbine section includes a compressor outlet section, a hot gas path, and a first stage nozzle disposed on the hot gas path. A load is operatively connected to one of the compressor section and the turbine section. A combustor assembly is fluidly connected to the compressor section. A transition piece has an inlet portion fluidly connected to the combustor assembly and an outlet portion fluidly connected to the turbine portion. A seal member is operatively connected relative to one of the transition piece and the first stage nozzle of the turbine section. The sealing member extends from a first end to a second cantilevered end through an intermediate portion that includes one or more apertures that permit variable flushing fluid flow from the compressor outlet portion to the hot gas path.
    In the aforementioned turbomachine system, the one or more openings may include a plurality of openings extending across the intermediate portion.
    The plurality of openings may have a plurality of circular openings.
    Alternatively, the plurality of openings may have a plurality of elongated openings.
    In addition, the plurality of openings may extend from a first end portion disposed at the first end to a second end portion disposed at the second cantilevered end.
    In one embodiment of the turbomachine system, the plurality of openings may extend through the second end.
    In the turbomachine system of any kind mentioned above, the sealing member may be operatively connected relative to the transition piece.
    In particular, the transition piece may include a rear frame, wherein the sealing element is operatively connected to the rear frame.
    In one embodiment of the turbomachine system, the sealing member may include a mounting member disposed at the first end.
    In another embodiment, the second end of the sealing member may be biased toward the other by the transition piece and the first stage nozzle of the turbine section.
    These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The article which is regarded as the invention is particularly indicated in the claims at the end of the description and clearly claimed. The foregoing and other features and advantages of the invention will become more apparent from the following detailed description taken in conjunction with the accompanying drawings, in which:<Tb> FIG. 1 <SEP> is a schematic view of a turbomachine system including a turbomachine with a seal member, according to an example embodiment;<Tb> FIG. 2 <SEP> is a cutaway partial view of the turbomachine of FIG. 1;<Tb> FIG. 3 <SEP> is a partial sectional view of a first stage of a turbine section of the turbomachine system of FIG. 1;<Tb> FIG. Fig. 4 <SEP> is a perspective view of the sealing element of Fig. 1; and<Tb> FIG. 5 <SEP> is a perspective view of a sealing element according to another aspect of an exemplary embodiment.
    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
    With reference to Figures 1 and 2, a turbomachine system is indicated generally at 2. The turbomachine system 2 includes a turbomachine 4 having a compressor section 6 connected to a turbine section 8. The compressor section 6 includes an inlet 10. The turbine section 8 includes a first stage nozzle 12 disposed on the inlet (not separately designated). The turbine section 8 also holds an outlet 14. The first stage nozzle 12 conditions combustion gases flowing along a hot gas path 16. The hot gas path 16 is disposed radially outward of an impeller space portion 18 and a compressor outlet plenum or portion 19. The combustion gases are generated in a combustion chamber assembly 20 which fluidly connects the compressor section 6 and the turbine section 8. The combustor assembly 20 includes one or more combustors 22. The turbomachine system 2 is further illustrated as including an intake system 24 fluidly connected to the inlet 10 and a load 26 that may be operatively connected to the turbine section 8. It should be understood that the load 26 may also be connected to the compressor section 6. An exhaust system 28 is fluidly connected to the outlet 14 of the turbine section 8. The exhaust system 28 receives and conditions exhaust gases flowing from the turbomachine 4.
    As illustrated in FIG. 2, the combustor 22 includes a plurality of nozzles 32 that deliver a combustible mixture into a combustion chamber 34. The combustible mixture is combusted to produce combustion products that flow from the combustor 22 into the turbine section 8 via a transition piece 38. The transition piece 38 extends from an inlet portion 39, which is fluidly connected to the combustion chamber 22, to an outlet portion 40, which is connected to a rear frame 41. The combustion products flow along the hot gas path 16 in interaction with turbine blades as illustrated, for example, at 44, doing work that drives the load 26. In addition to the combustion products, compressed air from the compressor section 6 flows to the impeller space section 18 via a diffuser 45 which is fluidly connected to the compressor outlet section 19. The compressed air supplies cooling and flushing flows in the turbine section 8.
    According to an exemplary embodiment, the turbomachine 4 includes a sealing member 60 extending between the rear frame 41 and the first stage nozzle 12. As explained in more detail below, the sealing element 60 prevents hot gases from entering the compressor outlet section 19 via a channel-shaped cavity 66. As illustrated in FIGS. 3 and 4, the sealing member 60 includes a body 70 that extends from a first end 72 to a second cantilevered end 73 through an intermediate portion 75. A mounting member 78 is provided at the first end 72 and serves as a joint between the sealing member 60 and the rear frame 41. It should of course be understood that the sealing member 60 may alternatively be rigidly mounted to the first stage nozzle 12 and attached may extend toward the rear frame 41. The intermediate portion 75 is biased or biased toward the first stage nozzle 12. In this way, during operation of the turbine section 8, the seal member 60 remains in contact with the first stage nozzle 12.
    Further, according to an exemplary embodiment, the sealing member 60 includes one or more apertures generally indicated at 80 and extending through the intermediate portion 75. The apertures 80 are substantially circular and extend between the first end 72 and the second end 73. The apertures 80 allow pressurized air to flow from the compressor outlet portion 19 toward the hot gas path 16. The compressed air cooperates with the combustion products to create a flow vortex in the trough-shaped cavity 66. The flow vortex improves overall sealing efficiency of the sealing element 60.
    In another aspect of the exemplary embodiment illustrated in FIG. 5, a sealing member 90 includes a body 92 that extends from a first end 94 to a second cantilevered end 95 via an intermediate portion 97. A mounting member 98 is provided at the first end 94 and serves as a joint between the sealing member 90 and a rear frame 41. Of course, it should be understood that the sealing member 90 may alternatively be rigidly mounted to the first stage nozzle 12 and toward may extend the rear frame 41. The intermediate portion 97 is biased or biased toward the first stage nozzle 12. In this way, during operation of the turbine section 8, the sealing member 90 remains in contact with the first stage nozzle 12.
    Further in accordance with the further aspect of the exemplary embodiment, the sealing member 90 includes one or more apertures generally indicated at 100 and extending through the intermediate portion 97. The apertures 100 take the form of elongated apertures extending from a first end portion 101 located at the first end 94 to a second end portion 102 disposed at the second end 95. The orifices 100 allow a variable flushing fluid flow in the form of compressed air to pass from the compressor outlet section 19 toward the hot gas path 16. The pressurized air cooperates with the combustion products to create a flow vortex in the trough-shaped cavity 66. The vortex improves overall sealing efficiency of the sealing member 90. In the illustrated exemplary aspect, the second end portion 102 extends through the second end 95. In this way, the openings 100 create multiple gaps 104 in the second end 95.
    At this point, it should be understood that the exemplary embodiments describe a sealing element that spans a trough-shaped cavity in a turbine section of a turbomachine. The seal member maintains a seal while components of the turbine section expand / grow during operation. The seal includes ports that allow pressurized air to pass from the compressor outlet section to the hot gas path to reduce hot gas feed through the trough-shaped cavity. Further, by adjusting the number, size, shape, pattern and / or location of the openings, flow through the sealing member can be regulated for various turbomachinery installations and operating conditions. In addition, it should be understood that the seal may be disposed on an inner periphery of the nozzle or an outer circumference of the nozzle or may extend annularly around the nozzles.
    While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention may be modified to incorporate any number of variations, modifications, substitutions, or equivalent arrangements not heretofore described, which, however, are within the spirit and scope of the invention. In addition, it should be understood that while various embodiments of the invention have been described, aspects of the invention may optionally include only some of the described embodiments. Accordingly, the invention should not be construed as being limited by the foregoing description, but is limited only by the scope of the appended claims.
    A turbomachine 4 includes a compressor section 6 and a turbine section 8 operatively connected to the compressor section 6. The turbine section 8 includes a compressor outlet section 19, a hot gas path 16, and a first stage nozzle 12 disposed on the hot gas path 16. A combustor assembly 20 is fluidly connected to the compressor section 6. A transition piece 38 has an inlet portion 39 which is fluidly connected to the combustion chamber assembly 20 and an outlet portion 40 which is fluidly connected to the turbine portion 8. A seal member 60 is operatively connected relative to one of the transition piece 38 and the first stage nozzle 12 of the turbine section 8. The seal member 60 extends from a first end 72 to a second cantilevered end 73 through an intermediate portion 75 that includes one or more apertures 80 that provide a play fluid flow path from the compressor outlet portion 19 to the hot gas path 16.
    LIST OF REFERENCE NUMBERS
    [0036]<Tb> 2 <September> turbomachinery system<Tb> 4 <September> turbomachinery<Tb> 6 <September> compressor section<Tb> 8 <September> turbine section<Tb> 10 <September> inlet<tb> 12 <SEP> First stage nozzle<Tb> 14 <September> outlet<Tb> 16 <September> hot gas path<Tb> 18 <September> impeller chamber section<Tb> 19 <September> Verdichterauslassabschnitt<Tb> 20 <September> combustor assembly<Tb> 22 <September> combustion chamber<Tb> 24 <September> intake<Tb> 26 <September> Last<Tb> 28 <September> Exhaust System<tb> 32 <SEP> multiple nozzles<Tb> 35 <September> combustion chamber<Tb> 38 <September> transition piece<Tb> 39 <September> inlet section<Tb> 40 <September> outlet<tb> 41 <SEP> rear frame<Tb> 42 <September> housing section<Tb> 44 <September> turbine blades<Tb> 45 <September> diffuser<Tb> 48 <September> outlet plenum<Tb> 60 <September> sealing element<tb> 66 <SEP> channel-shaped cavity<Tb> 70 <September> Body<tb> 72 <SEP> first end<tb> 73 <SEP> second, cantilevered finish<Tb> 75 <September> intermediate section<Tb> 78 <September> mounting element<Tb> 80 <September> openings<Tb> 90 <September> sealing element<tb> 92 <SEP> Body (90)<tb> 94 <SEP> first end (90)<tb> 95 <SEP> second, cantilevered end (90)<tb> 97 <SEP> Intermediate Section (90)<tb> 98 <SEP> Mounting element (90)<tb> 100 <SEP> openings (90)<tb> 101 <SEP> first end section<tb> 102 <SEP> second end section<tb> 104 <SEP> multiple gaps
    权利要求:
    Claims (10)
    [1]
    1. Turbomachine (4), comprising:a compressor section (6);a turbine section (8) connected to the compressor section (6), the turbine section (8) including a compressor outlet section (19), a hot gas path (16) and a first stage nozzle (12) connected to the hot gas path (16 ) is arranged;a combustor assembly (20) fluidly connected to the compressor section (6);a transition piece (38) having an inlet portion (39) fluidly connected to the combustor assembly (20) and an outlet portion (40) fluidly connected to the turbine portion (8); anda seal member (60) operatively connected to one of the transition piece (38) and the first stage nozzle (12) of the turbine section (8), the seal member (60) extending from a first end (72) to a second one cantilevered end (73) extends through an intermediate portion (75) including one or more apertures (80) providing a purge fluid flow path from the compressor outlet portion (19) to the hot gas path (16).
    [2]
    The turbomachine (4) of claim 1 wherein said one or more openings (80) include a plurality of openings (100) extending across said intermediate section (75).
    [3]
    The turbomachine (4) of claim 1 or 2, wherein the plurality of apertures (100) includes a plurality of circular openings.
    [4]
    The turbomachine (4) of claim 1 or 2, wherein the plurality of apertures (100) has a plurality of elongate apertures.
    [5]
    The turbomachine (4) of any one of the preceding claims, wherein the plurality of apertures (100) extend from a first end portion (101) located at the first end (72) to a second end portion (102) is disposed at the second cantilevered end (73); and orwherein the plurality of openings (100) extend through the second end (73).
    [6]
    A turbomachine (4) according to any one of the preceding claims, wherein the sealing member (60) is operatively connected relative to the transition piece (38).
    [7]
    A turbomachine (4) according to claim 6, wherein the transition piece (38) includes a rear frame (41), the sealing member (60) being operatively connected to the rear frame (41).
    [8]
    A turbomachine (4) according to any one of the preceding claims, wherein the sealing member (60) includes a mounting member (78) disposed at the first end (72).
    [9]
    A turbomachine (4) according to any one of the preceding claims, wherein the second end (73) of the sealing member (60) faces the other of the transition piece (38) and the first stage nozzle (12) of the turbine section (8) is biased.
    [10]
    10. Turbomachine system (2), comprising:a compressor section (6) containing an inlet (10);an intake system (24) fluidly connected to the inlet (10) of the compressor section (6);a turbine section (8) operatively connected to the compressor section (6), wherein the turbine section (8) includes a compressor outlet section (19), a hot gas path (16) and a first stage nozzle (12) connected to the hot gas path (16 ) is arranged;a load (26) operatively connected to one of the compressor section (6) and the turbine section (8);a combustor assembly (20) fluidly connected to the compressor section (6);a transition piece (38) having an inlet portion (39) fluidly connected to the combustor assembly (20) and an outlet portion (40) fluidly connected to the turbine portion (8); anda seal member (60) operatively connected to one of the transition piece (38) and the first stage nozzle (12) of the turbine section (8), the seal member (60) extending from a first end (72) to a second one cantilevered end (73) extends through an intermediate portion (75) including one or more apertures (80) providing a purge fluid flow path from the compressor outlet portion (19) to the hot gas path (16).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20160131041A1|2016-05-12|
    CN105587347A|2016-05-18|
    CH710372A8|2016-08-15|
    JP2016089830A|2016-05-23|
    DE102015118276A1|2016-05-12|
    引用文献:
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    法律状态:
    2016-08-15| PK| Correction|Free format text: BERICHTIGUNG A8 |
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-07-15| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/534,934|US20160131041A1|2014-11-06|2014-11-06|Turbomachine including a tranistion piece to turbine portion variable purge flow seal member|
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