Insert element, annular segment, gas turbine and mounting method

A technology for gas turbines and installation methods, applied in the direction of safety devices, engine components, blade support components, etc., can solve the problems of heavy lifting, etc., and achieve the effect of fast setting and execution

Inactive Publication Date: 2016-05-18
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Hood lifting is very taxing

Method used

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  • Insert element, annular segment, gas turbine and mounting method
  • Insert element, annular segment, gas turbine and mounting method
  • Insert element, annular segment, gas turbine and mounting method

Examples

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Embodiment Construction

[0029] figure 1 A gas turbine 10 according to the invention is shown in an exemplary embodiment. The gas turbine 10 comprises a turbine 11 in which at least one rotor blade row 12 is arranged. A ring composed of a plurality of ring segments is arranged around the rotor blade row 12 . The rotor blade row 12 is arranged in such a manner that it can rotate about an axis of rotation 20 .

[0030] A rotor blade row 12 is in particular a rotor blade row located downstream of other rotor blade rows. exist figure 1 , the corresponding rotor blade row 12 is the fourth rotor blade row of the turbine 11 of the gas turbine 10 .

[0031] The gas turbine 10 according to the invention has at least one ring segment 13 according to the invention. figure 2 Ring segment 13 is shown in an exemplary embodiment.

[0032] The ring segment 13 comprises a ring segment body 25 and an insert element 14 according to the invention.

[0033] The ring segment body 25 includes a hot gas side 27 . In...

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PUM

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Abstract

The invention relates to an insert element (14) for fastening to a annular segment body (25) of a turbine (11) of a gas turbine (10). The annular segment body (25) has a recess (23) on a hot-gas side (27). The insert element (14) is designed to cover the recess (23) and has a concave front side (15) and a rear side (16) having at least one shaped portion (17, 18) for positioning on the annular segment body (25). The invention also relates to an annular segment (13) comprising the insert element (14), a gas turbine (10) comprising the insert element (14) and a mounting method for mounting the insert element (14).

Description

technical field [0001] The invention relates to an insert element, a turbine ring segment of a gas turbine and a gas turbine, and a method of installation. Background technique [0002] It is known and common for the rotor blade rows of the turbine of a gas turbine to have a so-called shroud at the upper end of the blade airfoil. [0003] A cooling turbine ring segment for a gas turbine is known from US 2004 / 120803 A1, which ring segment comprises an axially oriented shroud ring segment with an inner surface, an outer surface, an upstream flange and a downstream flange. The flange retains the shroud ring in the engine case. A perforated cooling air impingement plate is disposed on the outer surface of the shroud ring between the upstream flange and the downstream flange, defining an impingement cavity therebetween. Axially oriented cooling holes in the ring segment extend between the impingement chamber and the outlet. The cavity adjacent to the outlet directs cooling air...

Claims

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Application Information

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IPC IPC(8): F01D5/14F01D11/08F01D21/00
CPCF01D5/143F01D5/02F01D5/12F01D11/08F01D21/003F05D2220/32F05D2230/60F05D2260/30F05D2260/83
InventorF·阿玛德M·亨德勒K·坎普卡C·科瓦尔斯基C·科瓦尔齐克N·库尔特S·施密特P·施罗德
OwnerSIEMENS AG