US5160822A
Expired / Lapsed
US
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Method for depositing material on the tip of a gas turbine engine airfoil using linear translational welding
Assignee: General Electric Co
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Filing: 1991-05-14
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Granted: 1992-11-03
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Expires: 2011-05-14
Abstract
Abstract A method for depositing material on a tip of a gas turbine engine airfoil includes the steps of: selecting a linear principal weld path across the airfoil tip relative to an airfoil contour at the tip; selecting a weld bead stitch pattern to substantially completely cover the airfoil tip with the stitch pattern crisscrossing the linear principal weld path between opposite edges of the airfoil and advancing across the airfoil in the direction of the linear principal weld path; and depositing at least a first layer of tip material corresponding to the weld bead stitch pattern and the linear principal weld path by welding.
Inventors
- 👤 Stephen Aleshin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 08:17
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/20; B; B23; B23K; B23K26/00; B23K26/34; B23K26/342; B23K35/00; B23K35/02; B23K35/0222; B23K35/0244; B23K35/0255; C; C23; C23C; C23C24/00; C23C24/08; C23C24/10; B23K2101/00; B23K2101/001; F05; F05D; F05D2250/00; F05D2250/30; F05D2250/34
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
161 words
A method for depositing material on a tip of a gas turbine engine airfoil, comprising the steps of: (a) selecting a linear principal weld path across the airfoil tip relative to an airfoil contour at the tip, wherein the linear principal weld path is selected to correspond substantially to a longest linear dimension of the airfoil tip to cause substantially uniform propagation of a heat front, caused by the welding, across the longest linear dimension of the airfoil tip to utilize substantially a maximum amount of airfoil material as a heat sink; (b) selecting a weld bead stitch pattern to substantially completely cover the airfoil tip, the stitch pattern crisscrossing the linear principal weld path between opposite edges of the airfoil and advancing across the airfoil in the direction of the linear principal weld path; and (c) depositing at least a first layer of tip material corresponding to the weld bead stitch pattern and the linear principal weld path by welding.
Claim 2
Independent Claim
161 words
A method for depositing material on a tip of a gas turbine engine airfoil, comprising the steps of: (a) selecting a linear principal weld path across the airfoil tip relative to an airfoil contour at the tip, wherein the linear principal weld path is selected to correspond substantially to a longest linear dimension of the airfoil tip to cause substantially uniform propagation of a heat front, caused by the welding, across the longest linear dimension of the airfoil tip to utilize substantially a maximum amount of airfoil material as a heat sink; (b) selecting a weld bead stitch pattern to substantially completely cover the airfoil tip, the stitch pattern crisscrossing the linear principal weld path between opposite edges of the airfoil and advancing across the airfoil in the direction of the linear principal weld path; and (c) depositing at least a first layer of tip material corresponding to the weld bead stitch pattern and the linear principal weld path by welding.
Claim 3
Dependent Claim
42 words
The method of claim 1, wherein step (c) comprises the step of depositing the at least first layer of tip material by laser welding with a laser welding apparatus with a nozzle for concentrically feeding a powdered material around the laser beam.
Claim 4
Dependent Claim
17 words
The method of claim 2, further comprising the step of selecting a group of laser welding parameters.
Claim 5
Dependent Claim
27 words
The method of claim 3, further comprising the step of selecting a laser power as a function of tip material, airfoil material and airfoil heat sink properties.
Claim 6
Dependent Claim
28 words
The method of claim 3, further comprising the step of selecting a focus spot size of the laser beam to determine a width of the weld bead stitch.
Claim 7
Dependent Claim
28 words
The method of claim 3, further comprising the step of selecting the powder feed rate as a function of laser power density and a tip material deposition rate.
Claim 8
Dependent Claim
49 words
The method of claim 1, further comprising the step of selecting a laser welding dwell time at each of the airfoil edges to deposit sufficient tip material at each airfoil edge to provide an airfoil tip which is substantially continuous and integral with a side surface of the airfoil.
Claim 9
Dependent Claim
48 words
The method of claim 1, further comprising the step of depositing at least one second layer which is started in a position offset from a start position of the at least one first position to provide an airfoil tip which substantially corresponds to a contour of the airfoil.
Claim 10
Dependent Claim
12 words
The method of claim 1, wherein the powdered material is a metal.
Claim 11
Dependent Claim
12 words
The method of claim 1, wherein the powdered material is a ceramic.
Claim 12
Independent Claim
175 words
A method for depositing material on a tip of a gas turbine engine airfoil, comprising the steps of; (a) selecting a linear principal weld path across the airfoil tip relative to an airfoil contour at the tip, the weld path being selected to correspond substantially to a longest linear dimension of the airfoil tip; (b) selecting a weld bead stitch pattern to substantially completely cover the airfoil tip, the stitch pattern crisscrossing the linear principal weld path at substantially right angles thereto and between opposite edges of the airfoil and advancing across the airfoil in the direction of the linear principal weld path; (c) selecting a welding dwell time at each of the airfoil edges to cause deposition of sufficient tip material at each airfoil edge to provide an airfoil tip which has a uniform thickness and is substantially continuous and integral with a side surface of the airfoil; and (d) depositing at least a first layer of tip material corresponding to the weld bead stitch pattern and the linear principal weld path by welding.
Claim 13
Independent Claim
175 words
A method for depositing material on a tip of a gas turbine engine airfoil, comprising the steps of; (a) selecting a linear principal weld path across the airfoil tip relative to an airfoil contour at the tip, the weld path being selected to correspond substantially to a longest linear dimension of the airfoil tip; (b) selecting a weld bead stitch pattern to substantially completely cover the airfoil tip, the stitch pattern crisscrossing the linear principal weld path at substantially right angles thereto and between opposite edges of the airfoil and advancing across the airfoil in the direction of the linear principal weld path; (c) selecting a welding dwell time at each of the airfoil edges to cause deposition of sufficient tip material at each airfoil edge to provide an airfoil tip which has a uniform thickness and is substantially continuous and integral with a side surface of the airfoil; and (d) depositing at least a first layer of tip material corresponding to the weld bead stitch pattern and the linear principal weld path by welding.
Claim 14
Dependent Claim
39 words
The method of claim 11, wherein step (d) comprises the step of depositing the at least first layer by laser welding with a laser welding apparatus with a nozzle for concentrically feeding a powdered material around the laser beam.
Claim 15
Dependent Claim
48 words
The method of claim 11, further comprising the step of depositing at least one second layer which is started in a position offset from a start position of the at least one first position to provide an airfoil tip which substantially corresponds to a contour of the airfoil.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1995-11-03 | 1996-05-04 | 1996-11-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-11-03 | 2000-05-04 | 2000-11-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-11-03 | 2004-05-04 | 2004-11-03 | $7700.00 | Window Closed / Lapsed |