Patent Application
20100172746
The subject matter disclosed herein relates to aerodynamic improvements to the flow in a compressor discharge casing. More particularly the subject invention relates to the cooling of a transition piece of the combustor.
In many gas turbine systems, a relatively high frequency interval of inspection, maintenance and components replacement is driven by components that are exposed to the severe conditions of the hot gas path. This path includes a combustor and components downstream thereof such as nozzles, liners, and transition pieces. A transition piece is a duct component that transfers hot combusted airflow from the combustion chamber to the turbine through a compressor discharge can. Cool compressor discharge air enters the compressor discharge can and naturally flows across the transition piece, thereby cooling the transition piece, on its way from the compressor to the combustor. Sufficient cooling of the transition piece reduces inspection, maintenance and component replacement costs by increasing the life of the transition piece. Thus, improved cooling of the transition piece would be well received in the art.
According to one aspect of the invention, a compressor discharge can includes a transition piece and a flow redirector located about the transition piece, defining an airflow space therebetween, the flow redirector configured to reduce recirculation of flow in the airflow space.
According to another aspect of the invention, a compressor discharge can includes a transition piece and a flow redirector located about the transition piece, an airflow space being located between the flow redirector and the transition piece, the flow redirector configured to reduce recirculation of flow in the airflow space.
According to yet another aspect of the invention, a method for cooling a transition piece includes increasing velocity of a fluid flowing across a surface of a transition piece with a flow redirector and reducing the recirculation of flow of the fluid across the surface of the transition piece with the flow redirector.
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:
A detailed description of the hereinafter described embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures.
Additionally, the flow redirector 170 is configured to reduce recirculation of the airflow 110 across the surface 180 of the transition piece 150. In another embodiment, the flow redirector 170 is configured to increase the average flow velocity across the surface 180 about which the flow redirector 170 is located. The flow redirector 170 further includes a surface facing the transition piece 150 and an antipodal surface facing away from the transition piece 150. The flow redirector 170 is configured to move a recirculation zone 190 from a position adjacent to the surface 180 to a position adjacent the antipodal surface of the flow redirector 170. In this position, the recirculation zone 190 may not reduce heat transfer between the transition piece 150 and the airflow 110 because it is not in contact with the transition piece 150. In another embodiment, the flow redirector 170 is configured to reduce a flow velocity gradient of the airflow 110 across the outer wall of the transition piece 150.
In one embodiment, the flow redirector 170 is located about the surface 180. An airflow space 191 is located adjacent to the surface 180 between the flow redirector 170 and the transition piece 150. In one embodiment, an offset dimension between the flow redirector 170 and the transition piece 150 is substantially constant. Alternately, the offset dimension may vary. The flow redirector 170 is shown located radially outwardly of the transition piece 150 relative to an axis of the turbine 199, shown in
The flow redirector 170 is shown having a shape that is contoured around the outer wall of the transition piece 150. In this embodiment, the flow redirector 170 may have a substantially similar shape as the transition piece 150 about which it is be located. In yet another embodiment, the flow redirector 170 includes at least one opening 206 through which some flow may naturally enter.
The flow redirector 170 is attachable to the compressor discharge can 100 in one embodiment. In this embodiment, the flow redirector 170 is attachable to a turbine side can wall 220 of the compressor discharge can 100. The flow redirector 170 may be welded, screwed, adhesively applied, or attached by any other attachment means. Additionally, the compressor discharge can 100 may designedly include the flow redirector 170 attached to an inner wall of the compressor discharge can 100 during the manufacture of the compressor discharge can 100. In other embodiments, the flow redirector 170 is attached to more than one wall of the compressor discharge can 100.
In another embodiment shown in
In a further embodiment, shown in
In alternate embodiments, also depicted in
It is also contemplated that an embodiment of the present invention includes a plurality of the flow redirectors 170 to redirect the flow in the compressor discharge can 100, as shown in
In one embodiment, the flow redirector 170 is made of a metallic material including both ferrous metals such as carbon steel or stainless steel, and nonferrous metals such as copper, aluminum, titanium and magnesium. Alternately, the flow redirector 170 is a non-metallic material or any other material that is configurable to efficiently redirect airflow within the compressor discharge can 100. The flow redirector 170 may also be made of a combination of any of the above materials.
Referring back to
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.
