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Methods for repairing a gas turbine component

  • US 8,978,249 B2
  • Filed: 10/29/2010
  • Issued: 03/17/2015
  • Est. Priority Date: 10/30/2009
  • Status: Active Grant
First Claim
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1. A method for repairing a gas turbine component comprising:

  • identifying on said gas turbine component a worn out location at which said gas turbine component is damaged;

    removing said damaged location and creating a missing zone;

    manufacturing an insert which fits into said missing zone, wherein the insert is pre-cast with built-in features;

    putting said insert into said missing zone;

    adjusting said insert in said gas turbine component;

    joining said adjusted insert to said gas turbine component;

    measuring the worn out location with a 3-D measuring system to determine the actual geometry of the missing zone;

    wherein a nominal geometry for the insert is defined by said actual geometry of the missing zone by establishing a component-specific reference coordinate system using characteristic features of the damaged gas turbine component including predefined gap tolerances and user-defined reference marks;

    wherein measuring the actual geometry of the insert comprises measuring during said manufacturing an insert;

    comparing the nominal geometry and the actual geometry of the insert based on the component-specific reference coordinate system;

    wherein manufacturing an insert comprises adaptive machining the insert based on said comparing;

    wherein the built-in features of the insert are not needed for functionality of the insert in the repaired gas turbine component, the built-in features being configured and arranged to allow clamping during at least one of the putting, adjusting, and forming steps, and assisting during the adaptive machining operation; and

    removing said built-in features not needed for functionality of the insert by machining after said joining.

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