Method for repairing a turbine vane
AssigneeUnited Technologies Corporation
InventorDavid J. Hiskes
Life of this patent
Estimating the term…
Abstract
The present invention relates to a method for repairing a vane used in a gas turbine engine. The method broadly comprises the steps of providing a vane to be repaired, which vane has a first platform, a first buttress, a second platform, a second buttress, and an airfoil extending between the first and second platforms, removing the first platform, the first buttress, and the airfoil from the vane in their entirety and removing part of the second platform and the second buttress leaving a machined vane portion, providing a replacement detail having at least a replacement first platform, a replacement first buttress and a replacement airfoil, positioning the replacement detail relative to the machined vane portion, and forming a joint between the machined vane portion and the replacement detail.
Claims18
A method for repairing a vane used on a turbine engine which comprises the steps of:
- providing a vane to be repaired, said vane having at least a first platform, a second platform, and an airfoil extending between the first and second platforms;
- removing entirely said first platform and said airfoil from said vane and removing part of said second platform leaving a machined vane portion;
- providing a replacement detail having at least a replacement airfoil and a replacement first platform;
- positioning said replacement detail relative to said machined vane portion;
- forming a joint between surfaces of said machined vane portion and said replacement shell;
- said vane being repaired further has a first buttress and a second buttress with a trailing edge extension;
- and
- said removing step comprising removing entirely said first buttress and removing a portion of said second buttress and said trailing edge extension so as to create a notch in said second buttress.
A method for repairing a vane used on a turbine engine which comprises the steps of:
- providing a vane to be repaired, said vane having at least a first platform, a second platform, and an airfoil extending between the first and second platforms;
- removing entirely said first platform and said airfoil from said vane and removing part of said second platform leaving a machined vane portion;
- providing a replacement detail having at least a replacement airfoil and a replacement first platform;
- positioning said replacement detail relative to said machined vane portion;
- forming a joint between surfaces of said machined vane portion and said replacement shell;
- said joint forming step comprising diffusion brazing said replacement detail and machined vane portion surfaces;
- and
- said diffusion brazing step comprising applying a brazing material to said surfaces to be joined together prior to said joint forming step, placing said machined vane portion with said replacement detail in a furnace after said brazing material applying step, and heating said machined vane portion and said replacement detail at a first temperature in the range of 2190° F. to 2240° F. for a time period in the range of 1 minute to 20 minutes.
A replacement detail for use in repair of a turbine vane comprising a first platform and a portion of a second platform, a replacement airfoil extending between said first platform and said second platform portion, and a raised portion which extends above a surface of said second platform surface and a replacement buttress trailing edge extension portion.
Dependencies are inferred from the claim text.