Patent Abstract:
A combustor liner cooling assembly for a gas turbine system includes a combustor liner defining a combustor chamber. Also included is a flow sleeve surrounding at least a portion of the combustor liner, wherein the flow sleeve includes at least one aperture row comprising a plurality of apertures, each of the plurality of apertures impinging a cooling flow jet onto the combustor liner. Further included is a plurality of flow redirecting components disposed proximate an aft end of the flow sleeve, wherein the plurality of flow redirecting components divert an impingement cross-flow flowing relatively perpendicular to the cooling flow jet, thereby providing the cooling flow jet an undisturbed flow path to the combustor liner.

Full Description:
BACKGROUND OF THE INVENTION 
       [0001]    The subject matter disclosed herein relates to gas turbine systems, and more particularly to a combustor liner cooling assembly. 
         [0002]    A combustor section of a gas turbine system typically includes a combustor chamber disposed relatively adjacent a transition piece, where a hot gas passes from the combustor chamber through the transition piece to a turbine section. At least a portion of the combustor chamber is often surrounded by a flow sleeve, while at least a portion of the transition piece is surrounded by an impingement sleeve. The flow sleeve typically includes a plurality of apertures for providing impingement cooing for portions of a liner of the combustor. An additional airflow passes from a region defined by the impingement sleeve and the transition piece to a region defined by the flow sleeve and the combustor liner. The impingement cooling of the liner of the combustor is achieved by cooling jets that are pushed onto the liner in a direction relatively perpendicular to the additional airflow flowing from the region proximate the impingement sleeve to the region proximate the flow sleeve. The additional airflow often disrupts the cooling jets, thereby resulting in reduced cooling efficiency. 
       BRIEF DESCRIPTION OF THE INVENTION 
       [0003]    According to one aspect of the invention, a combustor liner cooling assembly for a gas turbine system includes a combustor liner defining a combustor chamber. Also included is a flow sleeve surrounding at least a portion of the combustor liner, wherein the flow sleeve includes at least one aperture row comprising a plurality of apertures, each of the plurality of apertures impinging a cooling flow jet onto the combustor liner. Further included is a plurality of flow redirecting components disposed proximate an aft end of the flow sleeve, wherein the plurality of flow redirecting components divert an impingement cross-flow flowing relatively perpendicular to the cooling flow jet, thereby providing the cooling flow jet an undisturbed flow path to the combustor liner. 
         [0004]    According to another aspect of the invention, a combustor liner cooling assembly for a gas turbine system includes a combustor liner defining a combustor chamber. Also included is a flow sleeve surrounding at least a portion of the combustor liner and having an aft end, wherein the flow sleeve includes a plurality of apertures for impinging a plurality of cooling flow jets onto the combustor liner. Further included is an impingement sleeve disposed proximate the aft end of the flow sleeve, wherein an impingement flow path is defined by the impingement sleeve and a transition duct, wherein an impingement cross-flow flows through the impingement flow path into a region between the flow sleeve and the combustor liner. Yet further included is a plurality of flow redirecting components disposed proximate the aft end of the flow sleeve, wherein the plurality of flow redirecting components divert the impingement cross-flow. 
         [0005]    According to yet another aspect of the invention, a combustor liner cooling assembly for a gas turbine system includes a combustor liner defining a combustor chamber. Also included is a flow sleeve surrounding at least a portion of the combustor liner and having an aft end, wherein the flow sleeve includes a plurality of aperture rows, wherein each of the plurality of aperture rows comprises a plurality of apertures extending circumferentially around the flow sleeve, wherein each of the plurality of apertures impinges a cooling flow jet onto the combustor liner. Further included is a plurality of flow redirecting components disposed on a forward sleeve located proximate the aft end of the flow sleeve and a forward end of an impingement sleeve, wherein each of the plurality of flow redirecting components is circumferentially aligned with a corresponding first row aperture for diverting an impingement cross-flow entering a region between the flow sleeve and the combustor liner proximate the aft end of the flow sleeve. 
         [0006]    These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWING 
         [0007]    The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which: 
           [0008]      FIG. 1  is a partial schematic illustration of a combustor section of a gas turbine system; 
           [0009]      FIG. 2  is an enlarged view of section II of  FIG. 1 , illustrating a combustor liner cooling assembly; 
           [0010]      FIG. 3  is a perspective view of a plurality of flow redirecting components of the combustor liner cooling assembly; 
           [0011]      FIG. 4  is an enlarged, perspective view of a flow redirecting component of the plurality of flow redirecting components of a first embodiment; 
           [0012]      FIG. 5  is a cross-sectional view of a flow profile proximate the flow redirecting component of the first embodiment of  FIG. 4 ; 
           [0013]      FIG. 6  is a perspective view of the flow redirecting component of a second embodiment; 
           [0014]      FIG. 7  is a perspective view of the flow redirecting component of a third embodiment; 
           [0015]      FIG. 8  is a perspective view of the flow redirecting component of a fourth embodiment; 
           [0016]      FIG. 9  is a perspective view of the flow redirecting component of a fifth embodiment; and 
           [0017]      FIG. 10  is a perspective view of the flow redirecting component of a sixth embodiment. 
       
    
    
       [0018]    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 
       [0019]    Referring to  FIG. 1 , partial schematic illustrates a combustor section of a gas turbine system and is referred to generally with numeral  10 . The combustor section  10  includes a transition piece  12  having a transition duct  14  at least partially surrounded by an impingement sleeve  16  disposed radially outwardly of the transition duct  14 . Upstream thereof, proximate a forward end  18  of the impingement sleeve  16  is a combustor liner  20  defining a combustor chamber  22 . The combustor liner  20  is at least partially surrounded by a flow sleeve  24  disposed radially outwardly of the combustor liner  20 . A forward sleeve  26  is located at the junction between the forward end  18  of the impingement sleeve  16  and an aft end  28  of the flow sleeve  24 . 
         [0020]    The combustor section  10  uses a combustible liquid and/or gas fuel, such as a natural gas or a hydrogen rich synthetic gas, to run the gas turbine system. The combustor chamber  22  is configured to receive and/or provide an air-fuel mixture, thereby causing a combustion that creates a hot pressurized exhaust gas. The combustor chamber  22  directs the hot pressurized gas through the transition piece  12  into the turbine section (not illustrated), causing rotation of the turbine section. The presence of the hot pressurized exhaust gas increases the temperature of the combustor liner  20  surrounding the combustor chamber  22 , particularly proximate a downstream end  30  of the combustor liner  20 . To overcome issues associated with excessive thermal exposure to the combustor liner  20 , a plurality of apertures  32  within the flow sleeve  24  are arranged to provide impinged air in the form of a plurality of cooling jets  34  onto the combustor liner  20 . The plurality of apertures  32  may optionally include “thimbles” (not illustrated) which protrude toward the combustor liner  20 , providing an enclosed region to deliver the plurality of cooling jets  34  toward the combustor liner  20 . An impingement cross-flow  36  flows relatively perpendicularly to the plurality of cooling jets  34  and provides a convective cooling effect on the combustor liner  20  while flowing from downstream to upstream along the combustor liner  20 . Specifically, the impingement cross-flow  36  flows from a region defined by the impingement sleeve  16  and the transition duct  14  to a region defined by the flow sleeve  24  and the combustor liner  20 . 
         [0021]    Referring to  FIG. 2 , an enlarged view of the aft end  28  of the flow sleeve  24 , the forward sleeve  26  and the forward end  18  of the impingement sleeve  16  is shown in greater detail. The plurality of apertures  32  within the flow sleeve  24  may be arranged in one or more circumferential rows proximate the aft end  28  of the flow sleeve  24 . The forward sleeve  26  includes at least one, but typically a plurality of flow redirecting components  38  operably coupled thereto that are disposed along an inner surface of the forward sleeve  26  in a circumferentially spaced arrangement. The plurality of flow redirecting components  38  may be integrally formed with the forward sleeve  24  or may be fastened thereto. Each of the plurality of flow redirecting components  38  includes a flow redirecting surface  40  that is arranged to interact with the impingement cross-flow  36  that is flowing upstream toward the combustor liner  20  and the flow sleeve  24 . Each of the plurality of flow redirecting components  38  is relatively circumferentially aligned with at least one of the plurality of apertures  32 . 
         [0022]    Although the plurality of flow redirecting components  38  are described above and illustrated as being operably coupled to the forward sleeve  26 , it is contemplated that alternative embodiments may include operable coupling of the plurality of flow redirecting components  38  to the impingement sleeve  16  proximate the forward end  18  thereof Additionally, it is contemplated that the plurality of flow redirecting components  38  may be operably coupled to the aft end  28  of the flow sleeve  24 , provided that the plurality of flow redirecting components  38  are disposed downstream of the plurality of apertures  32 . 
         [0023]    Referring to  FIGS. 3-5 , a first embodiment of the plurality of flow redirecting components  38  comprises a semi-circular geometry, with the flow redirecting surface  40  arranged to interact with the impingement cross-flow  36 , as described above. As the impingement cross-flow  36  interacts with the flow redirecting surface  40 , the impingement cross-flow  36  is diverted around the flow redirecting surface  40 . As noted above, the plurality of flow redirecting components  38  are relatively aligned with the plurality of apertures  32 , and therefore also the plurality of cooling jets  34  flowing relatively perpendicularly to the impingement cross-flow  36 . By diverting the impingement cross-flow  36 , a disturbance of each of the plurality of cooling jets  34  is reduced based on the lack of a direct interaction between the impingement cross-flow  36  and the plurality of cooling jets  34 , thereby allowing the plurality of cooling jets  34  to more efficiently cool the combustor liner  20 . Additionally, the diversion of the impingement cross-flow  36  increases the average velocity of the impingement cross-flow  36 , which increases the convective heat transfer associated with the flowing of the impingement cross-flow  36  over the combustor liner  20 . 
         [0024]    Referring now to  FIG. 6 , a second embodiment of the plurality of flow redirecting components  38  is shown and is similar in construction to that of the first embodiment illustrated in  FIGS. 3-5 . Specifically, the second embodiment of the plurality of flow redirecting components  38  includes a plurality of holes  42  for reducing the formation of vortices upon recirculation of the impingement cross-flow  36  subsequent to passing the flow redirecting surface  40 . 
         [0025]    Referring to  FIG. 7 , a third embodiment of the plurality of flow redirecting components  38  is illustrated and is similar in construction to the embodiments described above. The third embodiment of the plurality of flow redirecting components  38  includes a first portion  44  having the previously described semi-circular geometry, which includes the flow redirecting surface  40  terminating in a first end  46  and a second end  48 . Extending axially upstream from at least one of the first end  46  and the second end  48  is a second portion  50  that provides additional axial structure for the impingement cross-flow  36  to flow along. The additional structure provided by the second portion  50  reduces the axial space between the plurality of flow redirecting components  38  and the plurality of cooling jets  34 , thereby reducing the likelihood of the impingement cross-flow  36  disrupting the plurality of cooling jets  34 . The third embodiment is illustrated with the plurality of holes  42  described above in relation to the second embodiment, however, it is to be appreciated that the third embodiment may include the second portion  50 , but not the plurality of holes  42 . 
         [0026]    Referring now to  FIGS. 8-10 , additional embodiments of the plurality of flow redirecting components  38  are illustrated. The additional embodiments are similar to the embodiments described above, but rather than a semi-circular geometry, the additional embodiments include a triangular geometry. Specifically, a fourth embodiment ( FIG. 8 ) of the plurality of flow redirecting components  38  includes a triangular geometry having a flow redirecting peak  52  arranged to interact with the impingement cross-flow  36 , as described above with respect to the flow redirecting surface  40  of the semi-circular embodiments. Additionally, a fifth embodiment ( FIG. 9 ) includes the plurality of holes  42 . As is the case with the embodiments described above containing the plurality of holes  42 , the plurality of holes  42  may be disposed at various angles and in various numbers and shapes and will be dependent upon the application of use. A sixth embodiment ( FIG. 10 ) includes a first triangular portion  54  extending from the flow redirecting peak  52  to a first end  56  and a second end  58 , where at least one second portion  60  may extend therefrom, similar to the third embodiment described above. As is the case with the third embodiment, although illustrated with the plurality of holes  42 , it is to be appreciated that the sixth embodiment may include the at least one second portion  60 , but not the plurality of holes  42 . The plurality of flow redirecting components  38  are described above as having particular geometric shapes, however, it is to be understood that any suitable geometric shape capable of diverting the impingement cross-flow  36  may be employed as the plurality of flow redirecting components  38 . 
         [0027]    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 can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, 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 be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

Technology Classification (CPC): 5