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Seal assembly for turbine coolant passageways

A technology for sealing components, turbines, applied in the direction of engine components, blade support components, mechanical equipment, etc., which can solve problems such as difficulty in maintaining the correct position of wire seals

Inactive Publication Date: 2013-08-14
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The downside of these devices is that during installation it can be difficult to maintain the correct position of the wire seal when installing the segmented seal plate to the rotor

Method used

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  • Seal assembly for turbine coolant passageways
  • Seal assembly for turbine coolant passageways
  • Seal assembly for turbine coolant passageways

Examples

Experimental program
Comparison scheme
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Embodiment Construction

[0013] figure 1 A rotor assembly 9 that may be used in a turbine system is depicted. The rotor assembly 9 rotates about a shaft 10 and may include at least one turbine blade 11 having a blade flange 12 . Blade flanges 12 project from the turbine blades 11 and are angled towards the axis of rotation of the rotor assembly 9 . The turbine blades 11 are fastened to the rotor 13 by conventional methods such as dovetail construction. The rotor 13 may be provided with a rotor flange 14 protruding from the rotor 13 and angled away from the axis of rotation of the rotor assembly 9 . The blade flange 12 and the rotor flange 14 delimit an opening 15 and a chamber 16 .

[0014] In the chamber 16 a sealing assembly 18 is provided which may comprise a sealing plate segment 19 . The sealing plate segment 19 may include an upper sealing arm 21 and a plate segment flange 23 . The sealing plate segment 19 may also be provided with a beveled end 25 . The radial dimension of the sealing ass...

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PUM

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Abstract

A seal assembly (18) for use with a turbine having a rotor (13) and at least one turbine blade (11) facilitates the use of a wire seal with seal plate segments (19). The seal assembly includes a plurality of seal plate segments (19) and a plurality of retainers (31,33) disposed on a rotor flange (14) on the rotor (13). A seal member (29) is disposed between the retainers (31,33) and the seal plate segments (19). The seal assembly (18) includes at least one attachment member (35) disposed through the rotor flange (14) that limits radial displacement of the seal plate segments (19).

Description

technical field [0001] The present invention relates to gas turbine rotors and, more particularly, to seal assemblies for sealing coolant passages in turbine rotor blades disposed at the periphery of a turbine rotor disk. Background technique [0002] A typical gas turbine has a rotor (wheel) with a plurality of blades (blades) distributed around the circumference of the rotor. The blades may be secured to the rotor using a conventional dovetail configuration. The blades are driven by hot gases from the combustion chamber and are cooled using coolant that flows through channels in the blades. It is important to avoid contact of hot gases with the rotor. [0003] Various sealing arrangements have been developed to prevent hot gases from coming into contact with the rotor. In some cases, a seal assembly may be positioned around the rim of the rotor to seal out the hot gas. In some applications, a more effective seal may be provided by providing a wire seal in a groove in t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D11/00F16J15/3204F16J15/3268
CPCF01D11/008F01D5/3015F01D11/001F01D11/006F05D2240/55Y10T29/49297
Inventor M.T.黑夫纳
Owner GENERAL ELECTRIC CO