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Cooled blade for a gas turbine

A technology of cooled and gas turbines, applied in the direction of blade support components, mechanical equipment, engine manufacturing, etc., can solve the problems of cooling channel pressure relationship and flow ratio change, difficult to adapt to changes, etc., to achieve the improvement of shroud cooling, cooling Improved effect

Active Publication Date: 2010-12-08
ANSALDO ENERGIA IP UK LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] This known type of multiple supply of cooling medium has various disadvantages: the pressure relationship and the flow ratio in the cooling channel are greatly changed by means of injectors compared to a single supply configuration through the cooling channel inlet on the front edge
This depends on a completely new structural design of blade cooling, which is difficult to adapt to changing requirements

Method used

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  • Cooled blade for a gas turbine
  • Cooled blade for a gas turbine
  • Cooled blade for a gas turbine

Examples

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Embodiment Construction

[0021] exist Figures 1 to 4 A preferred embodiment of a cooled gas turbine blade according to the invention with multiple feeds of cooling medium is given in . The main flow of the cooling medium enters the cooling channel 13 from below through a main cooling inlet 16 in the region of the blade shank 25 and partially through openings in the shroud section 21 ( Figures 5 to 8 boreholes 27, 28, 29) and partly through the rear edge 20 and then discharged (see figure 1 arrows on the shroud section 21 and the rear edge 20 as indicated in ).

[0022] The additional cooling medium is supplied via the blade shank 25 and a core hole 24 provided in the blade root by means of the two bores 22 , 23 . These boreholes 22, 23 - as from Figures 2 to 4 It can be clearly seen in - are graded radially and axially and relative to each other ( image 3 , 4). The boreholes 22 , 23 are inclined at an angle between 30° and 90° relative to the vertical, wherein the boreholes run obliquely upwa...

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Abstract

The invention relates to a cooled blade (10) for a gas turbine. Said blade comprises a paddle (11) leading from a blade root (12) and a blade shaft (25), said paddle having a leading edge (19) and a trailing edge (20), in addition to a plurality of radially extending cooling channels (13, 14, 15) in its interior that are fluidically connected in sequence. A first cooling channel (13) is traversedalong the leading edge (19) and a second cooling channel (15) is traversed along the trailing edge (20), from the blade root (12) to the tip of the paddle (11), by a primary stream of coolant and theoutlet of the first cooling channel (13) is connected to the inlet of the second cooling channel (15) via a first deviation zone (17), a third cooling channel (14) that is situated between the first and the second cooling channels (13, 15) and a second deviation zone (18). The blade is provided with elements (22, 23, 24), by means of which a supplementary stream of cooler coolant is added externally to the heated primary stream of coolant that flows from the third cooling channel (14) into the second cooling channel (15).

Description

technical field [0001] The invention relates to the technical field of gas turbines. It relates to a cooling blade for a gas turbine. Background technique [0002] Such blades are known, for example, from the publication US-A-4,278,400. [0003] Deckbanded blades are used in modern high-efficiency gas turbines, which are exposed to hot gas at a temperature of more than 1200 K and a pressure of more than 6 bar during operation. [0004] figure 1 The basic configuration of one such shrouded blade is shown in FIG. The blade 10 comprises an airfoil 11 , which merges downwards via a blade shank 25 into a blade root 12 . At the upper end, the blade airfoil 11 merges into a shroud section 21 which, over a complete blade ring, forms a closed annular shroud together with the shroud sections of the other blades. The blade airfoil 11 has a front edge 19 and a rear edge 20 which faces the hot gas. In the interior of the blade airfoil 11 there are radial cooling channels 13, 14, 15...

Claims

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Application Information

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IPC IPC(8): F01D5/18F01D25/12
CPCF01D5/187F05D2250/185F01D25/12F05D2260/211F01D5/18F01D25/08
Inventor 赛伦德拉·奈克萨哈·帕尔内乌尔里希·拉特曼海伦妮·萨克瑟-费利西斯特凡·施勒希特里姆贝亚特·冯阿尔克斯
Owner ANSALDO ENERGIA IP UK LTD
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