Cooled turbine ring segments with intermediate pressure plenums
a technology of gas turbine ring segments and pressure plenums, which is applied in the direction of machines/engines, engine fuctions, non-positive displacement fluid engines, etc., can solve the problems of the ability of the turbine components to withstand increased temperatures and the inability to increase the combustion firing temperatur
Inactive Publication Date: 2014-09-25
SIEMENS AG
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Benefits of technology
The invention provides a cooling system for a gas turbine engine ring segment that includes a panel with side edges and mating edges. The panel has an inner side that defines a hot gas flow path and an outer side that receives cooling fluid. The cooling system includes elongated intermediate plenums and convective cooling passages that cool the inner side of the panel. The cooling system also includes a cooling fluid feed system that supplies cooling fluid to the intermediate plenums and convective cooling passages. The technical effect of the invention is to improve the cooling efficiency of the gas turbine engine ring segment and reduce thermal stresses.
Problems solved by technology
One aspect limiting the ability to increase the combustion firing temperature is the ability of the turbine components to withstand increased temperatures.
Method used
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[0027]In the following detailed description of the preferred embodiment, reference is made to the accompanying drawings that form a part hereof, and in which is shown by way of illustration, and not by way of limitation, a specific preferred embodiment in which the invention may be practiced. It is to be understood that other embodiments may be utilized and that changes may be made without departing from the spirit and scope of the present invention.
[0028]The present invention provides a ring segment including a panel provided with a cooling system that enables increased cooling effectiveness within the edges of the ring segment and facilitates cooling of an inner segment surface facing the hot gas path. The cooling system includes intermediate plenums of a predetermined size to supply a flow of cooling air through a plurality of convective cooling passages located generally parallel to, and closely adjacent to the inner segment surface. The configuration of the cooling passages pro...
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A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes an elongated intermediate plenum extending parallel to leading and trailing edges of the ring segment, and is located radially between an inner side of the panel and a hook structure extending from an outer side of the panel. A plurality of cooling fluid feed passages supply cooling fluid to the intermediate plenum, and a plurality of convective cooling passages extend through the panel from the intermediate plenum to one of the leading and trailing edges for cooling the inner side of the panel. The intermediate plenum is located in axial alignment with and defines an area of reduced thermal mass receiving impingement cooling adjacent to the hook structure.
Description
CROSS REFERENCE TO RELATED APPLICATION[0001]This application claims the benefit of U.S. Provisional Patent Application Ser. No. 61 / 592,102, filed Jan. 30, 2012, entitled “IMPINGEMENT CONCEPT WITH INTERMEDIATE PRESSURE PLENUMS FOR COOLED TURBINE RING SEGMENTS”, the entire disclosure of which is incorporated by reference herein.FIELD OF THE INVENTION[0002]The present invention relates to ring segments for gas turbine engines and, more particularly, to cooling of ring segments in gas turbine engines.BACKGROUND OF THE INVENTION[0003]It is known that the maximum power output of a combustion turbine is achieved by heating the gas flowing through the combustion section to as high a temperature as is feasible. The hot gas, however, heats the various turbine components, such as airfoils and ring segments, which it passes when flowing through the turbine section. One aspect limiting the ability to increase the combustion firing temperature is the ability of the turbine components to withstand...
Claims
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IPC IPC(8): F01D25/08
CPCF01D25/08F01D11/24F05D2240/11F05D2260/205
Inventor BRUNELLI, MARCO CLAUDIO PIOKHAN, SAMEER AHMEDLANDIS, KENNETH K.MARUSSICH, WALTER H.MARTIN, JR., NICHOLAS F.SUAREZ-CROSSE, BEATRIZTAYLOR, BRIAN E.
Owner SIEMENS AG