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Method and apparatus for increasing fatigue notch capability of airfoils

一种翼型件、设备的技术，应用在金属加工设备、制造工具、抛光机床等方向，能够解决激光冲击处理昂贵等问题

Inactive Publication Date: 2008-09-03
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Laser shock treatment can be expensive due to required specimen preparation, equipment used, and personnel training requirements
Additionally, shot peening and laser shock processing can be relatively slow processes

Method used

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  • Method and apparatus for increasing fatigue notch capability of airfoils
  • Method and apparatus for increasing fatigue notch capability of airfoils
  • Method and apparatus for increasing fatigue notch capability of airfoils

Examples

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Embodiment Construction

[0016] Referring to the drawings, in which like numerals denote like elements throughout the various views, figure 1 An exemplary gas turbine engine compressor blade 20 is shown prior to processing. This component is only used as an example of a part to which the method of the invention can be applied. The invention is equally applicable to other types of components that are susceptible to cracking due to fatigue or damage, such as compressor stator vanes, fan blades, turbine blades, shafts and rotors, mounts, actuator hardware, and the like. The part may be made of metal alloys, ceramics or composite materials such as carbon fiber composites. Usually, the blade is made of alloys based on titanium, iron or nickel. Examples of commercially available alloys of this type include Ti 6-4, Ti 6-2-4-2, A-286, C 450, and In 718. Compressor blade 20 includes an airfoil 22 , a platform 24 and a shank 26 . In this particular example, the handle 26 includes a dovetail 28 that is recei...

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Abstract

The present invention provides a method and apparatus for increasing fatigue notch capability of airfoils. The method of reducing crack propagation in an airfoil includes: providing an airfoil having a root spaced apart from a tip, spaced-apart leading and trailing edges, a suction side extending from the leading edge to the trailing edge, and an opposed pressure side extending from the leading edge and the trailing edge, supporting the airfoil against bending loads; and burnishing the airfoil using a burnishing element, so as to create at least one burnished section of residual compressive stress, the at least one burnished section being located adjacent the leading edge and spaced from the leading edge by an offset distance selected so as to avoid deformation of the leading edge.

Description

technical field [0001] The present invention relates generally to fatigue resistant and damage tolerant components and methods of making such components. Background technique [0002] Various metallic, ceramic and composite components, such as gas turbine engine fans and compressor blades, are susceptible to crack formation due to fatigue and damage such as impact from foreign objects. This damage reduces the life of the part, requiring repair or replacement. [0003] It is well known that components are protected from crack propagation by inducing residual compressive stresses within them. Methods of applying these stresses include shot peening, laser peening (LSP), pinch peening, and low plasticity polishing (LPB). These methods are generally accomplished by imposing a "bump" of residual compressive stress on the area to be protected from crack propagation, such as the leading edge of a compressor blade of a gas turbine engine. However, shot peening is detrimental to su...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B24B1/00B24B39/00C01F1/00
CPCY10T29/49336Y10T29/47C21D7/04Y10T29/471B23P9/02B24B39/00Y10T29/479C21D7/08B23P6/002
Inventor A·卢纳J·L·米勒W·T·丁韦尔M·J·布伦克W·L·英霍夫P·蒙塞勒D·R·龙巴多A·P·伍德菲尔德
Owner GENERAL ELECTRIC CO
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