Patent Application
20130333388
The subject matter disclosed herein relates to gas turbine systems, and more particularly to a combustor liner cooling assembly.
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.
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.
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.
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.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
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:
The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
Referring to
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.
Referring to
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.
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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.
