Gas turbine hot gas component repair method
First Claim
1. A gas turbine engine hot gas component repair method for defects that do not extend through a thickness of the component, comprising:
- a) machining at least one cavity in a surface of the component to remove at least one defect from the component;
b) manufacturing at least one coupon fittable within the cavity;
c) applying a brazing medium to the coupon to enable brazing of the coupon to the component;
d) fitting the coupon as a fitted coupon into the cavity;
e) joining the fitted coupon to the component at an outer edge of the fitted coupon;
f) applying foil or sheet brazing medium to the joined coupon to cover the joined coupon and form an outer surface of the component to provide a thickness of the component; and
g) subjecting the component to a thermal cycle wherein the foil or sheet brazing medium is brazed to an outer surface of the coupon.
3 Assignments
0 Petitions
Accused Products
Abstract
A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.
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Citations
23 Claims
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1. A gas turbine engine hot gas component repair method for defects that do not extend through a thickness of the component, comprising:
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a) machining at least one cavity in a surface of the component to remove at least one defect from the component; b) manufacturing at least one coupon fittable within the cavity; c) applying a brazing medium to the coupon to enable brazing of the coupon to the component; d) fitting the coupon as a fitted coupon into the cavity; e) joining the fitted coupon to the component at an outer edge of the fitted coupon; f) applying foil or sheet brazing medium to the joined coupon to cover the joined coupon and form an outer surface of the component to provide a thickness of the component; and g) subjecting the component to a thermal cycle wherein the foil or sheet brazing medium is brazed to an outer surface of the coupon. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 23)
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12. A gas turbine engine hot gas component repair method for defects that do not extend through a thickness of the component, comprising:
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a) machining at least one cavity in a surface of the component to remove at least one defect from the component; b) manufacturing at least one coupon fittable within the cavity; c) applying a brazing medium to the coupon to enable brazing of the coupon to the component; d) fitting the coupon as a fitted coupon into the cavity; e) joining the fitted coupon to the component at an outer edge of the fitted coupon; f) applying foil or sheet brazing medium to the joined coupon to cover the joined coupon and form an outer surface of the component to provide a thickness of the component; and g) subjecting the component to a single thermal cycle wherein the foil or sheet brazing medium is brazed to an outer surface of the coupon and the coupon is brazed to the component. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19, 20, 21, 22)
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Specification