Method for depositing material on the tip of a gas turbine engine airfoil using linear translational welding

• US 5,160,822 A
• Filed: 05/14/1991
• Issued: 11/03/1992
• Est. Priority Date: 05/14/1991
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Aleshin, Stephen
• Primary Examiner(s): ALBRITTON, CLARENCE
• Application Number:
  US07/701,403
• Time in Patent Office: 539 Days
• Field of Search: 219/121.63, 219/121.64, 219/121.6, 219/12.85, 219/121.65, 219/121.66, 219/121.82, 219/121.8
• US Class Current: 219/121.64
• CPC Class Codes: B23K 2101/001 Turbines
• CPC Class Codes: B23K 26/342 Build-up welding
• CPC Class Codes: B23K 35/0244 Powders, particles or spheres; Preforms made therefrom
• CPC Class Codes: B23K 35/0255 for use in welding B23K35/0205 takes precedence
• CPC Class Codes: C23C 24/10 with intermediate formation of a liquid phase in the layer
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F05D 2250/34 translated

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.

Claims

1. 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.

2. 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.

3. The method of claim 2, further comprising the step of selecting a group of laser welding parameters.

4. 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.

5. 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.

6. 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.

7. 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.

8. 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.

9. The method of claim 1, wherein the powdered material is a metal.

10. The method of claim 1, wherein the powdered material is a ceramic.

11. 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.

12. 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.

13. 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.