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Internally-damped airfoil and method therefor

一种阻尼部件、翼型的技术,应用在翼型件领域,达到减小附连应力的效果

Active Publication Date: 2010-10-20
GENERAL ELECTRIC TECH GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, these damping techniques often encounter limitations related to structural integrity, aerodynamic efficiency, and manufacturing difficulty

Method used

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  • Internally-damped airfoil and method therefor
  • Internally-damped airfoil and method therefor
  • Internally-damped airfoil and method therefor

Examples

Experimental program
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Embodiment Construction

[0013] Figures 1 to 3 schematically depicts an airfoil member 10 according to a first embodiment of the invention, while Figure 4 An airfoil member 50 according to a second embodiment of the invention is schematically depicted. It should be noted that the drawings are drawn for clarity when viewed in conjunction with the following description, and therefore are not necessarily drawn to scale. The particular shape of members 10 and 50 is also not intended to limit the types of airfoil members encompassed by the present invention. In the drawings, like reference numerals designate like elements throughout the various views.

[0014] refer to Figures 1 to 3 In the illustrated embodiment, the member 10 can be seen to have an airfoil portion 12 and a root portion 14, wherein the root portion 14 has a dovetail feature 15 capable of interlocking with complementary features of a rotor disk (not shown) in a manner well known in the art. Consistent with industry terminology, airf...

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PUM

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Abstract

An airfoil component and method for producing the component. The component has root and airfoil portions, the latter having an airfoil tip and oppositely-disposed concave and convex surfaces that converge at leading and trailing edges of the airfoil portion. The airfoil portion has at least one stiffener between first and second walls thereof that define the concave and convex surfaces, respectively. The stiffener defines multiple internal cavities within the airfoil portion that extend in the span-wise direction of the airfoil portion. A polymeric material fills at least one of the internal cavities and is bonded to the airfoil portion only at an extremity of the internal cavity nearer the root portion, and not to the stiffener or to the first and second walls of the airfoil portion, to define an internal damping member that provides a vibratory damping effect to the airfoil portion.

Description

technical field [0001] The present invention relates generally to airfoils and, more particularly, to relatively lightweight airfoils that enhance efficiency when used as compressor blades for gas turbine engines. Background technique [0002] Efforts are continually being made to increase the work of each compression stage in gas turbine engines to reduce overall engine system cost. may be known in part by the AN 2 Factors evaluating this improvement, AN 2 It is the product of the area of ​​the inner flow path and the outer flow path of the compressor blade times the square of the mechanical speed. The compressor blades of gas turbines are usually mechanically attached to the rotor wheel / disc with fir tree or dovetail construction mechanical attachments, the life of fir tree or dovetail construction mechanical attachments Limited by the high loads that must be withstood due to the size and weight of the blades. Heavy blade airfoils require large blade attachments and cr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/16
CPCF04D29/324F04D29/023F05D2260/96F05D2300/43Y10S416/50F04D29/668
Inventor R·R·凯罗
Owner GENERAL ELECTRIC TECH GMBH