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turbine blades

A technology of blades and turbines, applied in the direction of supporting components of blades, engine components, machines/engines, etc., can solve the problems of high product cost, high failure possibility, complex structure, etc., and achieve the effect of simple cost-effectiveness

Inactive Publication Date: 2016-03-23
GENERAL ELECTRIC TECH GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] As can be seen from the references mentioned above, current axial retention systems require further work during the assembly process, or have a complex structure which leads to expensive cost and higher probability of failure of the product

Method used

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Examples

Experimental program
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Embodiment Construction

[0035] figure 1 A schematic view of a blade assembly of a turbine according to an embodiment of the invention is shown. The blade 100 includes an airfoil 111 , a platform 112 and a root portion 101 . The “fir tree” type root portion is configured to be received in a mounting notch of the rotor disk 102 . In order to show the complete root section 101, the rotor disk 102 is not in figure 1 shown in , but available from image 3 see in image 3 A cross-sectional view of the assembly of the root portion 101 and the rotor disk 102 is shown.

[0036] According to an embodiment of the invention, the blade 100 also comprises a locking member arranged on the root portion 101 and engaged with the rotor disk 102 for axial fixing of the blade relative to the rotor disk 102 .

[0037] In a preferred embodiment of the invention, the locking member is embodied as figure 1 The locking pin 106 is shown. A locking pin 106 is provided between the rotor part 101 and the rotor disc 102, wh...

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PUM

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Abstract

The invention relates to a blade for a turbine comprising an airfoil, a platform and a root portion configured to be slidably received in a mounting slot of a rotor disk. The blade also includes a locking member arranged on the root portion and engaged with the rotor disk for axial securing of the blade to the rotor disk. With the inventive solution it provides a blade with a simple and cost-effective axial locking system for axial fixing of the blade relative to the rotor disk and also provides a fail-safe solution during the assembly process.

Description

technical field [0001] The present invention relates to turbines, in particular to blades of turbines, and more particularly to blades having locking means for axially securing the blades relative to a rotor disk. Background technique [0002] A gas turbine has a rotor assembly that generally includes blades attached to a rotor disk. Each blade includes a root, a platform and an airfoil. The root of each blade is usually of so-called "fir tree" construction, so that it can be firmly attached to the outer circumference of the disc and still have room for thermal expansion. The "fir tree" attachment of the blades to the rotor disk effectively inhibits both radial and circumferential movement of the blades relative to the rotor disk against radial centrifugal forces. However, during high speed, high temperature operation of a gas turbine engine, the axial flow of air or gas through the rotor assembly exerts a constant axial force on the blades to move axially against the "fir...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/32
CPCF01D5/32F01D5/323F05D2230/64F05D2260/30F01D5/3015F01D5/303F01D5/3007F01D5/3053
Inventor I.鲁科蒂M.科伊尼格L.博格达尼
Owner GENERAL ELECTRIC TECH GMBH