Sequencing of multi-pass laser shock peening applications

Patent metadata

Field	Value
Publication number	US-9764422-B2
Application number	US-201314763109-A
Country	US
Kind code	B2
Filing date	Dec 18, 2013
Priority date	Mar 15, 2013
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

A method for laser shock peening (LSP) a workpiece is disclosed. The method may include identifying a geometry of the workpiece, determining a number of applications of LSP upon a first side and a second side of the workpiece, and sequencing the applications among the first side and the second side to minimize distortion.

First claim

What is claimed is:

1. A method for laser shock peening (LSP) a workpiece, comprising: identifying a geometry of the workpiece;
determining a number of non-simultaneous applications of LSP upon a first side and a second side of the workpiece; and
sequencing the non-simultaneous applications among the first side and the second side to minimize distortion, wherein each non-simultaneous application of LSP on the first side occurs at a different time than each non-simultaneous application of LSP on the second side.

2. The method of claim 1 , further comprising providing one application to the first side of the workpiece, and measuring a change in geometry of the workpiece.

3. The method of claim 1 , further comprising providing one application to the second side of the workpiece, and measuring a change in geometry of the workpiece.

4. The method of claim 1 , further comprising determining which side of the workpiece to provide a first application of LSP.

5. The method of claim 1 , further comprising determining a sequence of the non-simultaneous applications based on measured changes in geometry of the workpiece after each successive application.

6. The method of claim 1 , further comprising using a coordinate measuring machine (CMM) to measure the geometry of the workpiece.

7. A method for laser shock peening (LSP) an airfoil, comprising: identifying an initial geometry of the airfoil;
determining a number of non-simultaneous applications of LSP upon each of a first side and a second side of the airfoil; and
providing the non-simultaneous applications in a sequence having a minimum amount of variation from the initial geometry of the airfoil, wherein each non-simultaneous application of LSP on the first side occurs at a different time than each non-simultaneous application of LSP on the second side.

8. The method of claim 7 , further comprising further comprising providing three non-simultaneous applications to each of the first side and the second side of the airfoil.

9. The method of claim 7 , further comprising determining the sequence based on an amount of variation from the initial geometry of the airfoil after each application.

10. The method of claim 7 , further comprising providing the sequence as a first application to the first side, a second application to the second side, a third application to the second side, a fourth application to the first side, a fifth application to the first side, and a sixth application to the second side.

11. A method for manufacturing an airfoil of a gas turbine engine, comprising: measuring an initial geometry of the airfoil;
determining a number of non-simultaneous applications of laser shock peening to provide on the airfoil;
determining a sequence for the non-simultaneous applications, wherein each non-simultaneous application of LSP on the first side occurs at a different time than each non-simultaneous application of LSP on the second side;
determining a new geometry for the airfoil based on the initial geometry and the sequence;
providing an airfoil according to the new geometry; and

applying the sequence on the airfoil having the new geometry.

12. The method of claim 11 , further comprising measuring the initial geometry of the airfoil, including at least one of thickness, chord length, camber, twist, and lean.

13. The method of claim 11 , further comprising providing a first application to a pressure side of the airfoil.

14. The method of claim 13 , further comprising providing a second application to a suction side, a third application to the suction side, a fourth application to the pressure side, a fifth application to the pressure side, and a sixth application to the suction side.

15. The method of claim 11 , further comprising providing non-simultaneous applications to the pressure and suction sides of the airfoil and measuring variations in geometry to determine the sequence.

16. The method of claim 15 , further comprising determining the sequence based on a sequence having a smallest amount of variation in geometry.

17. The method of claim 16 , further comprising applying the sequence to an airfoil having the initial geometry.

18. The method of claim 17 , further comprising measuring an amount of variation in geometry from the initial geometry after applying the sequence.

19. The method of claim 18 , further comprising designing the new geometry of the airfoil to compensate for the measured amount of variation in geometry.

20. The method of claim 19 , further comprising compensating for the measured amount of variation in geometry by offsetting a lean and a twist in the new geometry of the airfoil.

Assignees

• United Technologies Corp

Inventors

• Filewich Paul

Classifications

• C21D10/005 Primary

  by laser shock processing · CPC title

• F01D21/003

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• B23K26/356 Primary

  by shock processing · CPC title

• B23K26/03

  Observing, e.g. monitoring, the workpiece · CPC title

• F01D5/286

  Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion (F01D5/288 takes precedence) · CPC title