• 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 combustor (10) has a combustion chamber (20) and an inner wall (16, 18) surrounding at least a portion of the combustion chamber (20) in the circumferential direction and defining an outer surface (22) and a longitudinal centerline (24). On the outer surface (22) is a plurality of turbulators (28). A shell (36) circumferentially surrounds at least a portion of the inner wall (16, 18) with respect to the flow direction in the combustion chamber (20), and the shell (36) defines an air space between the inner wall (16, 18) and the shell (36). , The shell (36) further includes an end portion (38) having an edge surrounding the inner wall (16, 18), the end portion (38) of the shell having a funnel shape (42) over at least a portion of the edge.
    公开号:CH703767B1
    申请号:CH01481/11
    申请日:2011-09-08
    公开日:2017-01-13
    发明作者:Dugar Saurav；P Berkebile Matthew；Ghosh Dullal；Vincent Pawlowski Joseph；Kumar Pallikara Gopalan Krishna；Byron Huffman Marcus
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Field of the invention
    The present invention relates to a combustion chamber with turbulators, which are arranged at predetermined locations on an outer surface of the combustion chamber to improve the heat transfer from the combustion chamber.
    General state of the invention
    Gas turbines are often used in industrial processes and power generation processes. A typical gas turbine has an axial compressor at the front, one or more combustion chambers at the center, and a turbine at the rear. Ambient air flows into the compressor, and blades and vanes in the compressor transfer stepwise kinetic energy to the working fluid (air) to produce a compressed working fluid in a high energy state. The compressed working fluid exits the compressor and flows through nozzles into the combustion chambers, where it is mixed with fuel and ignited to produce combustion gases at a high temperature, pressure, and velocity. The combustion gases flow to the turbine where they relax to do work. For example, by relaxing the combustion gases in the turbine, a shaft can be rotated that is connected to a generator to generate electricity.
    It is well known that the thermodynamic efficiency of a gas turbine increases when the operating temperature, that is, the combustion gas temperature rises. Combustion gas temperatures in excess of 3000 ° F, i. above 1650 ° C, are therefore desirable and relatively common in the industry. Conventional combustion chambers and transition pieces which direct the combustion gases out of the combustion chamber are usually made of materials generally having a maximum temperature on the order of about 1500 ° F for about 10,000 hours. of about 815 ° C, can withstand. It is therefore desirable to provide a type of cooling for the combustion chamber and / or transition piece to protect it from thermal damage.
    Various techniques for providing cooling to the combustion chamber are known in the art. For example, US Pat. Nos. 5,724,816, 7,010,921 and 7,373,778, assigned to the same assignee as the present invention, each describe various structures and methods for cooling a combustion chamber and / or a transition piece of a combustion chamber.
    However, continuous improvements in structures and methods for cooling combustor components would be useful.
    Brief description of the invention
    The present invention relates to a combustion chamber having a combustion chamber and an inner wall which surrounds at least a portion of the combustion chamber in the circumferential direction with respect to the flow direction in the combustion chamber. The inner wall has an outer surface on which a plurality of turbulators are located and defines a longitudinal centerline. A shell circumferentially surrounds at least a portion of the interior wall with respect to the flow direction in the combustion chamber, and the shell defines an air space between the interior wall and the shell. The shell further includes an end portion having an edge surrounding the inner wall, the end portion of the shell having a funnel shape over at least a portion of the edge for preferentially directing fluid flow through the air space and across the plurality of turbulators.
    From the description, one of ordinary skill in the art will better appreciate the features and aspects of these and other embodiments.
    Brief description of the drawings
    The disclosure of the present invention relates to the associated figures, in which:<Tb> FIG. 1 <SEP> is a simplified cross section of a combustion chamber according to an embodiment of the present invention;<Tb> FIG. Fig. 2 is a perspective view of a transition piece according to an embodiment of the present invention;<Tb> FIG. FIG. 3 is a perspective cutaway view of a transition piece according to a second embodiment of the present invention; and FIG<Tb> FIG. Fig. 4 is a perspective cutaway view of a transition piece according to a third embodiment of the present invention.
    Detailed description of the invention
    [0009] Reference will now be made in detail to present embodiments of the invention, for which one or more examples are illustrated in the accompanying drawings. In the detailed description, numerals and letters are used to refer to features in the drawings. In the drawings and the description, similar or similar terms have been used to refer to the same or similar parts of the invention.
    Fig. 1 shows a simplified cross section of a combustion chamber 10 with a combustion chamber 20 according to an embodiment of the present invention. As shown, the combustion chamber 10 generally has one or more nozzles 12, which are arranged parallel to the flow direction in the combustion chamber 20 side by side in a closure piece 14. For ease of understanding, the nozzles 12 are shown in the figures as cylinders, without details of the type, arrangement or internal components of the nozzles 12.
    An insert 16 and a transition piece 18 surround the combustion chamber 20 in its circumferential direction with respect to the flow direction in the combustion chamber 20 behind the end piece 14. The insert 16 and the transition piece 18 define an outer surface 22 and along the flow direction in the combustion chamber 20 extending center line 24th so that compressed working fluid or air can flow through the combustion chamber 20. The insert 16 and the transition piece 18 may comprise a single, continuous piece, which surrounds the combustion chamber 20 in its circumferential direction with respect to the flow direction in the combustion chamber 20. Alternatively, as shown in FIG. 1, for example, insert 16 and transition piece 18 may each have a separate inner wall connected to a seal 26 such that each surrounds at least a portion of combustion chamber 20 in the circumferential direction. As shown in each of the figures, one of the inner walls 16, 18 or both inner walls 16, 18 may have a gradually decreasing in the flow direction through the combustion chamber, which concentrates or concentrates the combustion gases leaving the combustion chamber 10.
    The combustion chamber 10 further includes a plurality of turbulators 28 on the outer surface 22 of the inner walls 16, 18. The turbulators 28 may be angled protrusions or depressions on the outer surface 22 of one or both of the inner walls 16, 18 to interfere with the laminar flow of the compressed working fluid as it flows over the outer surface 22 of the inner walls 16, 18. The turbulators 28 thus increase the effective area of the outer surface 22 of the inner walls 16, 18 and cause turbulence in the compressed working fluid. The perturbation of the laminar flow on the outer surface 22 and the increase in the proportion of the outer surface 22 usable for cooling together contribute to increasing the turbulence of the compressed working fluid over the outer surface 22 to promote the cooling of the inner walls 16, 18. The increased turbulence in the compressed working fluid caused by the turbulators 28 may additionally enhance the subsequent mixing of the compressed working fluid with the fuel to improve combustion in the combustor 20.
    The turbulators 28 may be projections or depressions on the outer surface 22, which may have virtually any geometric shape, including circular, rectangular, trapezoidal or any combination thereof. The turbulators 28 may be molded, welded, bolted or otherwise secured to the outer surface 22 of the inner walls 16, 18 using any suitable method known in the art and capable of withstanding the high ambient temperatures of the combustor 10. In certain embodiments, such as illustrated in FIG. 2, the turbulators 28 may include a stepped protrusion 30 extending from the inner walls 16, 18. The step-shaped projection 30 may have a generally rectangular base 32 with a pointed end 33, similar to a wing with a winglet distal to the inner walls 16, 18. The step-shaped projection 30 may transfer heat by creating vortices over the outer surface 22 of the inner walls 16 , 18 reinforce. As shown in FIG. 2, the turbulators 28 or step-like projections 30 may be arranged in rows and columns to redirect the compressed working fluid flowing over the outer surface 22 of the inner walls 16, 18 to prevent the cooling caused by the compressed working fluid is provided to further improve. In addition, a higher concentration of the turbulators 28 or step-shaped projections 30 may be found at a predetermined location 34 on the outer surface 22 of the inner walls 16, 18. The predetermined location 34 may be an area on the outer surface 22 of the inner walls 16, 18 which, according to empirical measurements and / or mathematical models, usually has a higher operating temperature. In this way, the positive cooling effect achieved by the turbulators 28 or the stepped projections 30 can be enhanced at the predetermined location 34, which would presumably have higher operating temperatures without them.
    The combustor 10 further includes means for preferentially directing a fluid flow, namely, the flow of compressed working fluid, over the predetermined location 34 of the plurality of turbulators 28. As further illustrated in FIG. 1, the means for preferentially directing a flow of fluid may include a skirt 36 having an end portion 38 which is oriented approximately 90 degrees to the longitudinal centerline 24 of the inner walls 16, 18 and flow direction in the combustion chamber 20, respectively. The shell 36 circumferentially surrounds at least a portion of one or both of the interior walls 16, 18 and is generally concentric with one or both interior walls 16, 18. The shell 36 thus defines an air space 40 between the interior walls 16, 18 and the sheath 36. The end portion 38 of the sheath 36 forms an edge around the inner walls 16, 18 and further comprises a funnel shape 42 around at least a portion of the edge. For example, as shown in FIG. 1, the edge of the end portion 38 of the shell 36 has a continuous funnel shape 42 around the entire edge. In this manner, the shell 36, the end portion 38, the air space 40 and the funnel shape 42 jointly direct a flow of fluid preferably through the air space 40 and across the plurality of turbulators 28. As shown in FIG. 1, the shell 36 may in certain embodiments and a plurality of the orifices 44 for further flowing fluid over the turbulators 28, although the presence of the orifices 44 in the shell 36 is not a required structure for the means for directing fluid flow and is not a limitation of the present invention.
    Fig. 3 shows a perspective cutaway view of the portion of the transition piece 18 of the combustion chamber 10 according to an alternative embodiment of the present invention. In this embodiment, the means for preferentially directing a fluid flow comprises the shell 36, the end region 38, the air space 40, and the funnel shape 42 as previously described with reference to FIG. In this particular embodiment, however, the end portion 38 is oriented approximately 45 ° to the longitudinal centerline 24 of the inner wall 18 with respect to the flow direction in the combustion chamber 20. As shown in Fig. 3, the lower portion of the end portion 38 has a funnel shape 42, while the upper portion of the end portion 38 is generally straight. The means for preferentially directing a fluid flow also has at least one enlarged opening 46 in the shell 36 in this particular embodiment. The size and location of the enlarged opening 46 in the shell 36 may be selected to control the amount and location of the fluid flow, and thus the cooling, which is preferably directed to or over certain turbulators 28 on the outer surface 22 of the inner wall 18. For example, the enlarged opening 46 may be sized such that the means for preferentially directing fluid flow covers less than about 90%, 80%, 70%, or 60% of the inner wall 18 and / or the turbulators 28. Additionally or alternatively, the enlarged opening 46 may be located near the predetermined location 34 previously described with reference to FIG. 2 and having a higher concentration of the turbulators 28 and / or known or likely to have higher operating temperatures.
    Fig. 4 shows a perspective cutaway view of the portion of the transition piece 18 of the combustion chamber 10 according to another alternative embodiment of the present invention. In this embodiment, the means for preferentially directing a fluid flow comprises the shell 36, the end region 38, the air space 40, and the funnel shape 42 as previously described with reference to FIG. In this particular embodiment, however, the end portion 38 is oriented approximately 135 ° to the longitudinal centerline 24 of the inner wall 18 with respect to the direction of counterflow in the combustion chamber 20. As shown in Fig. 4, the upper portion of the end portion 38 has a funnel shape 42, while the lower portion of the end portion 38 is substantially straight. As in the embodiment illustrated in FIG. 3, the means for preferentially directing fluid flow in this embodiment again includes at least one enlarged opening 46 in the shell 36. The size and location of the enlarged opening 46 in the shell 36 may be selected to control the amount and location of the fluid flow, and thus the cooling, which is preferably directed to or over certain turbulators 28 on the outer surface 22 of the inner wall 18. For example, the enlarged opening 46 may be sized so that the means for preferentially directing a fluid flow is less than between about 90%, 80%, 70%, or 60% of the inner wall 18 and / or the turbulators 28. Additionally or alternatively, the enlarged opening 46 may be located near the predetermined location 34 previously described with reference to FIG. 2 and having a higher concentration of the turbulators 28 and / or known or likely to have higher operating temperatures.
    A combustion chamber 10 has a combustion chamber 20 and an inner wall 16, 18 which surrounds at least a portion of the combustion chamber 20 in the circumferential direction and defines an outer surface 22. On the outer surface 22 is a plurality of turbulators 28. A shell 36 surrounds circumferentially with respect to the flow direction in the combustion chamber at least a portion of the inner wall 16, 18, and the shell 36 defines an air space between the inner wall 16, 18 and the shell 36th The sheath 36 further includes an end portion 38 having an edge surrounding the inner wall 16, 18, the end portion 38 of the sheath having a funnel shape 42 over at least a portion of the edge.
    LIST OF REFERENCE NUMBERS
    [0018]<Tb> 10 <September> combustion chamber<Tb> 12 <September> Nozzles<Tb> 14 <September> Final Piece<Tb> 16 <September> Application<Tb> 18 <September> transition piece<Tb> 20 <September> combustion chamber<Tb> 22 <September> outer surface<tb> 24 <SEP> Longitudinal centerline<Tb> 26 <September> seal<Tb> 28 <September> turbulators<tb> 30 <SEP> Stepped ledge<tb> 32 <SEP> Rectangular area<tb> 33 <SEP> Pointed distal end<tb> 34 <SEP> Default location<Tb> 36 <September> coat<Tb> 38 <September> end<Tb> 40 <September> airspace<Tb> 42 <September> funnel shape<Tb> 44 <September> openings<tb> 46 <SEP> Enlarged opening
    权利要求:
    Claims (9)
    [1]
    A combustor (10) comprising:a) a combustion chamber (20);b) an inner wall (16, 18) which surrounds at least a portion of the combustion chamber (20) in the circumferential direction with respect to the flow direction in the combustion chamber (20), wherein the inner wall (16, 18) has an outer surface (22) and a longitudinal center line (24) defined;c) a plurality of turbulators (28) on the outer surface (22) of the inner wall (16, 18);d) a jacket (36) which surrounds at least a portion of the inner wall (16, 18) in the circumferential direction with respect to the flow direction in the combustion chamber (20), the jacket (36) having an air space (40) between the inner wall (16, 18) and the sheath (36) and having an end portion (38) with an edge surrounding the inner wall (16, 18), the end portion (38) of the sheath (36) having a funnel shape (42) over at least a portion of the edge Having a fluid flow through the air space (40) and the plurality of turbulators (28).
    [2]
    2. combustion chamber (10) according to claim 1, wherein the inner wall (16, 18) along the flow direction in the combustion chamber (20) has a gradually decreasing circumference.
    [3]
    The combustor (10) of any of claims 1 to 2, further comprising a higher concentration of the plurality of turbulators (28) at a predetermined location (34) on the outer surface (22) of the inner wall (16, 18) compared to others Positions on the outer surface (22) of the inner wall (16, 18).
    [4]
    A combustor (10) according to any one of claims 1 to 3, wherein the plurality of turbulators (28) comprises a step-shaped projection (30) extending from the inner wall (16, 18) and a pointed end (33) distally the inner wall (16, 18).
    [5]
    The combustor (10) of any one of claims 1 to 4, further comprising a plurality of apertures (44) in the jacket (36).
    [6]
    6. combustion chamber (10) according to one of claims 1 to 5, wherein the end portion (38) of the jacket (36) has a continuous funnel shape (42) around the entire edge.
    [7]
    7. combustion chamber (10) according to one of claims 1 to 6, wherein the end region (38) of the jacket (36) over at least a portion of the peripheral edge with respect to the flow direction in the combustion chamber (20) 45 ° to the longitudinal center line (24) Inner wall (16, 18) is aligned.
    [8]
    8. combustion chamber (10) according to one of claims 1 to 7, wherein the end portion (38) of the jacket (36) over at least a portion of the peripheral edge with respect to the flow direction in the combustion chamber (20) 90 ° to the longitudinal center line (24) Inner wall (16, 18) is aligned.
    [9]
    9. combustion chamber (10) according to one of claims 1 to 8, wherein the jacket (36) less than 90% of the plurality of turbulators (28) on the outer surface (22) of the inner wall (16, 18) covered.
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2018-04-30| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/880,446|US8201412B2|2010-09-13|2010-09-13|Apparatus and method for cooling a combustor|
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