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Platform of gas turbine moving blade, a method of forming the moving blade, a sealing plate, and a gas turbine having these elements

A technology of rotating blades and gas turbines, which is applied in the direction of supporting elements of blades, machines/engines, and engine cooling, and can solve problems such as uncontrolled sealing gas temperature, blade rupture, and poor stability and reliability of gas turbine rotating blades

Inactive Publication Date: 2006-11-29
MITSUBISHI HEAVY IND LTD
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  • Abstract
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  • Claims
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Problems solved by technology

[0007] However, seal air is often used to prevent leakage of dry streams of high temperature gas, allowing the temperature of the seal gas to be uncontrolled
Therefore, if the seal air is used to cool the rotating blades and if the seal air is hot, the blades may crack
In addition, it is inappropriate to use a large amount of seal air for (except mainly for) preventing the leakage of high-temperature gas dry flow; because, the high flow rate of seal air can make the stability and reliability of the gas turbine rotating blades worse

Method used

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  • Platform of gas turbine moving blade, a method of forming the moving blade, a sealing plate, and a gas turbine having these elements
  • Platform of gas turbine moving blade, a method of forming the moving blade, a sealing plate, and a gas turbine having these elements
  • Platform of gas turbine moving blade, a method of forming the moving blade, a sealing plate, and a gas turbine having these elements

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Embodiment Construction

[0025] Exemplary embodiments of the present invention will be described below with reference to the accompanying drawings. The present invention is not limited to these Examples.

[0026] Fig. 1(a) is a sectional view of a rotary blade 1 according to a first embodiment of the present invention, and Fig. 1(b) is a sectional view along line A-A shown in Fig. 1(a).

[0027] The rotating blade 1 comprises a blade 2 forming a profile, a platform 3 connected to the root of the blade 2 and a shank 4 located below the platform 3 . The interior of the blade 2 is partially hollow so that cooling air is first supplied to the cooling air channel 5 from the blade root (in the shape of a Christmas tree, not shown here) leading to a rotor (not shown) placed below the blade 2 . Cooling air is then supplied to the leading edge channel 6 and the serpentine fluid channels 7, 8, both arranged inside the blade 2, to cool the inside of the blade. In the cooling channel 9, part of the cooling air ...

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Abstract

A platform of a gas turbine moving blade suppresses the effects of thermal elongation and thus improves cooling performance. A structure is constituted by a peripheral edge of a platform of a gas turbine moving blade, a bottom of the platform, and a shank of the moving blade. A cavity is blocked by disposing a sealing plate so as to seal the recessed section, while a supply route is formed for supplying air from cooling passages through an interior of the shank to the cavity, each of the passages being for air-cooling the interior of the gas turbine moving blade with air blown out from the cavity to a surface of the platform. A method of appropriately installing the sealing plate is also disclosed.

Description

[0001] related application [0002] This application is based on and claims the benefit of priority from US Patent Application No. 11 / 138,449, filed May 27, 2005, which is incorporated herein by reference in its entirety. technical field [0003] The present invention relates to techniques for introducing cooling air into the cavities of the platforms of the rotating blades of gas turbines. Background technique [0004] Figure 9 is a perspective view of a conventional rotating blade 101 used as a first stage rotating blade in a gas turbine. The rotating blade 101 includes a platform 103 and a blade 102 . The blade 102 has a profile and a root 151 . Roots 151 are formed under the platform 103 in the shape of a Christmas tree. And as shown in FIG. 10 , the root portion 151 cooperates with the groove 162 of the turntable 161 . The groove 162 has the opposite shape to the blade root 151 . The turntable 161 has a plurality of grooves at its periphery, and each blade 102 fit...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18F02C7/18
CPCF05D2260/2212F05D2260/2214F05B2260/224F05D2240/81F05B2240/801F01D5/187F05D2240/55F05B2260/222
Inventor 鸟井俊介由里雅则弗雷德里希·泽希廷
Owner MITSUBISHI HEAVY IND LTD
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