Method and apparatus for cooling combustor liner in combustor
a technology of combustor and combustor liner, which is applied in the direction of lighting and heating apparatus, machines/engines, stators, etc., can solve the problems of affecting the life of the combustor, and affecting the cooling effect of the combustor liner downstream end,
Inactive Publication Date: 2012-08-09
GENERAL ELECTRIC CO
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Benefits of technology
[0011]These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.
Problems solved by technology
During operation of the turbine system, various components in the system may be subjected to high temperature flows, which can cause the components to fail.
Combustion generally takes place within the combustor liner, thus subjecting the combustor liner to high temperature flows.
In particular, the downstream end of the combustor liner may be a life-limiting location for the combustor.
However, typical arrangements of these holes result in significant pressure losses and uneven cooling of the combustor liner.
However, these sleeves do not adequately cool the downstream end of the combustor liner.
Method used
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[0019]Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.
[0020]FIG. 1 is a schematic diagram of a gas turbine system 10. The system 10 may include a compressor 12, a combustor 14, and a turbine 16. Further, the system 10 may include a plurality of compressors 12, combustors 14, and turbines 16. The compressors 12...
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A method and apparatus for cooling a combustor liner in a combustor are disclosed. In one embodiment, a combustor is disclosed. The combustor includes a transition piece, and an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween. The combustor further includes an injection sleeve mounted to one of the transition piece or the impingement sleeve and positioned radially outward of the impingement sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid to the flow path. In another embodiment, a method for cooling a combustor liner in a combustor is disclosed. The method includes flowing a working fluid through a flow channel at least partially defined by an injection sleeve, and exhausting the working fluid from the flow channel into a flow path adjacent the combustor liner.
Description
FIELD OF THE INVENTION[0001]The subject matter disclosed herein relates generally to turbine systems, and more particularly to methods and apparatus for cooling combustor liners in combustors.BACKGROUND OF THE INVENTION[0002]Turbine systems are widely utilized in fields such as power generation. For example, a conventional gas turbine system includes a compressor, a combustor, and a turbine. During operation of the turbine system, various components in the system may be subjected to high temperature flows, which can cause the components to fail. Since higher temperature flows generally result in increased performance, efficiency, and power output of the gas turbine system, the components that are subjected to high temperature flows must be cooled to allow the gas turbine system to operate at increased temperatures.[0003]One such component that requires cooling during operation is the combustor liner. Combustion generally takes place within the combustor liner, thus subjecting the co...
Claims
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IPC IPC(8): F23R3/42
CPCF01D9/023F01D25/12F05D2260/201F23R3/002F23R3/54F23R3/02F23R3/10F23R3/26F23R3/46F23R2900/03044F02K1/822F23R3/06
Inventor CIHLAR, DAVID WILLIAMMELTON, PATRICK BENEDICT
Owner GENERAL ELECTRIC CO