Tailored material property tuning for turbine engine fan blades

1. A method of making a blade for a gas turbine engine, the method comprising

calculating a strain profile for a first natural frequency of a virtual blade having a predetermined shape, the strain profile correlating to a deflection of the virtual blade vibrating at the first natural frequency,

identifying a first discrete region of the virtual blade,

applying at least one of heat and a force to a first discrete region of a stock of material, and

forming a physical blade having the predetermined shape from the stock of material such that the first discrete region of the stock of material forms a first region of the physical blade that corresponds in location with the first discrete region of the virtual blade so that at least one of a first natural frequency of the physical blade corresponding to the first natural frequency of the virtual blade and a deflection of the physical blade at the first natural frequency of the physical blade is different from at least one of the first natural frequency of the virtual blade and the deflection of the virtual blade at the first natural frequency of the virtual blade,

further comprising determining a second natural frequency of the virtual blade and the step of identifying the first discrete region of the virtual blade includes identifying a discrete region of the virtual blade in which the first natural frequency of the physical blade will be altered more than a second natural frequency of the physical blade that corresponds with the second natural frequency of the virtual blade.

2. The method of claim 1 , wherein identifying the first discrete region of the virtual blade includes identifying a discrete region of the virtual blade having a greatest magnitude of strain based on the strain profile.

3. The method of claim 1 , wherein the first discrete region is spaced apart from a leading edge, trailing edge, and tip of the blade.

4. The method of claim 1 , wherein the first discrete region is at a trailing edge of the blade.

5. The method of claim 1 , wherein the first natural frequency corresponds with one of a first order bend mode of the virtual blade and a first order torsion mode of the virtual blade.

6. A method of making a blade for a gas turbine engine, the method comprising

determining a strain profile of a blade having a first crystallographic texture profile for a first natural frequency of the blade,

identifying a first discrete region of the blade in which the strain profile has a greatest magnitude of strain based on the strain profile, and

treating the blade at or adjacent the first discrete region to alter the first crystallographic texture profile of the blade around the first discrete region such that the blade has a second crystallographic texture profile that is different from the first crystallographic texture profile and change an elastic modulus of the blade around the first discrete region to modify at least one of a deflection of the blade and the first natural frequency of the blade,

further comprising determining a second natural frequency of the blade and the step of treating the first discrete region causes the first natural frequency to change in magnitude greater than it causes a change in magnitude of the second natural frequency of the blade.

7. The method of claim 6 , wherein the step of treating the blade includes at least one of heat treating and forging the blade at or adjacent the first discrete region to alter the first crystallographic texture profile of the blade.

8. The method of claim 6 , wherein the first natural frequency corresponds with a first order bend mode of the blade.

9. The method of claim 6 , wherein the first natural frequency corresponds with a first order torsion mode of the blade.

10. The method of claim 6 , wherein the first discrete region is spaced apart from a leading edge, trailing edge, and tip of the blade.

11. The method of claim 6 , wherein the first discrete region is at a trailing edge of the blade.

12. The method of claim 6 , further comprising identifying a second discrete region of the blade in which the strain profile is at a second greatest magnitude based on the strain profile and treating the blade at or adjacent the second discrete region to alter the first crystallographic texture profile of the blade.

13. A method of making a blade for a gas turbine engine, the method comprising

determining a first natural frequency associated with a first vibrational mode of a blade, and

treating the blade at a first discrete region to alter a crystallographic texture of the blade at the first discrete region to alter at least one of a deflection of the blade at the first natural frequency and the first natural frequency of the blade,

further comprising determining a second natural frequency associated with a second vibrational mode of the blade and the first discrete region is chosen to cause the first natural frequency of the blade to change in magnitude greater than a change in the second natural frequency of the blade.

14. The method of claim 13 , further comprising the step of determining the first discrete region based on a calculated strain profile of a virtual blade having same dimensions as the blade.

15. The method of claim 13 , further comprising providing the blade in physical form having its final external dimensions before the treating step.

16. The method of claim 13 , further comprising identifying a second discrete region of the blade and treating the blade at the second discrete region to alter the crystallographic texture of the blade at the second discrete region.