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Cooled ring segment

a technology of ring segments and gas turbine engines, which is applied in the direction of machines/engines, liquid fuel engines, mechanical equipment, etc., can solve the problems of the turbine components' ability to withstand increased temperatures and the inability to increase the combustion firing temperatur

Inactive Publication Date: 2013-01-10
SIEMENS ENERGY INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The invention provides a ring segment for a gas turbine engine. The segment includes a panel with a leading edge, trailing edge, mating edges, and inner and outer sides. Cooling fluid is provided to the outer side of the panel, and the inner side defines a hot gas flow path. The panel also has an impingement chamber with a metering supply and discharge passages that cool the panel at its mating edges. A central recessed portion is surrounded by a rim portion and walls to direct the cooling fluid to the mating edges. Overall, the invention improves the cooling efficiency of the gas turbine engine.

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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  • Cooled ring segment
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Examples

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Embodiment Construction

[0012]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.

[0013]FIG. 1 illustrates in cross section a portion of a turbine section 10 of a gas turbine engine. Within the turbine section 10 are a series of rows of stationary vanes and rotating blades. In FIG. 1, a single blade 12 forming a row 12a of blades is illustrated. Also illustrated in FIG. 1 is part of an upstream vane 14 forming a row 14a of upstream vanes, and part of a downstream vane 16 forming a row 16a of downstream vanes. The blades 12 are coupled to a disc (not shown) of a rotor assembly. A hot working gas from a combustor (not s...

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PUM

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Abstract

A ring segment for a gas turbine engine includes a panel and a first mating edge cooling system. Cooling fluid is provided to an outer side of the panel and an inner side of the panel defines at least a portion of a hot gas flow path. A cooling system receives a portion of the cooling fluid provided to the outer side and includes at least one impingement chamber. Each impingement chamber includes at least one metering supply passage and at least one metering discharge passage. The metering supply passage(s) extends from the outer side of the panel to the impingement chamber. Cooling fluid impinges on a surface of the panel defining the impingement chamber as it flows therein through the metering supply passage(s). The metering discharge passage(s) extends from the impingement chamber to a first or second mating edge of the panel.

Description

FIELD OF THE INVENTION[0001]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[0002]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 the combustor and transition ducts, and vanes 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 increased temperatures. Consequently, various cooling methods have been developed to cool turbine hot parts.[0003]In the case of ring segments, ring segments typically may include an impingement tube, also known as an impingement plate, associated with the ring segment and defining a plenu...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D25/12
CPCF01D25/12F01D11/006F05D2260/202F05D2240/11F05D2240/81F05B2240/40F01D11/24
Inventor LIANG, GEORGESALAZAR, SANTIAGO R.
Owner SIEMENS ENERGY INC