Airfoil aerodynamics

1. A method of manufacturing an airfoil of a gas turbine engine, the method comprising:

fixing the airfoil in a workpiece space;

detecting a position of the airfoil in the workpiece space using a force-sensing element; and

removing material from the airfoil to reduce a dimension of the airfoil;

wherein removing material from the airfoil is performed substantially simultaneously as detecting the position of the airfoil in the workpiece space.

2. The method of claim 1 , wherein detecting the position of the airfoil comprises moving the force-sensing element across a surface of the airfoil.

3. The method of claim 2 , wherein the surface of the airfoil is a first surface, wherein removing material from the airfoil to reduce the dimension of the airfoil comprises removing material from a second surface of the airfoil opposite the first surface.

4. The method of claim 3 , wherein removing material from the second surface of the airfoil is performed without moving the force-sensing element across the second surface of the airfoil.

5. The method of claim 3 , wherein removing material from the second surface of the airfoil is performed substantially simultaneously as moving the force-sensing element across the first surface of the airfoil by using a clamp force-sensing element having a sensing portion and a cutting portion.

6. The method of claim 1 , wherein removing material from the airfoil to reduce a thickness of the airfoil comprises utilizing a diamond cutter to cut away material.

7. A method of manufacturing an airfoil of a gas turbine engine, the method comprising:

fixing the airfoil in a workpiece space, the airfoil having a leading edge, a leading edge portion, a trailing edge, and a trailing edge portion;

detecting a position of the airfoil in the workpiece space using a force-sensing element; and

removing material from at least one of the leading edge portion and the trailing edge portion of the airfoil to reduce a dimension of the one of the leading edge portion and the trailing edge portion, wherein removing material from the one of the leading edge portion and the trailing edge portion of the airfoil is performed while the trailing edge portion of the airfoil is uncooled.

8. The method of claim 7 , wherein detecting the position of the airfoil comprises moving the force-sensing element across a surface of the one of the leading edge portion and the trailing edge portion.

9. The method of claim 8 , wherein the surface is a first surface, wherein removing material from the at least one of the leading edge portion and the trailing edge portion of the airfoil comprises removing material from a second surface of the one of the leading edge portion and the trailing edge portion of the airfoil, the second surface being opposite the first surface.

10. The method of claim 9 , wherein removing material from the second surface is performed without moving the force-sensing element across the second surface of the at least one of the leading edge portion and the trailing edge portion of the airfoil.

11. The method of claim 9 , wherein the dimension is a thickness of the one of the leading edge portion and the trailing edge portion between the first surface and the second surface.

12. The method of claim 9 , wherein removing material from the second surface of the at least one of the leading edge portion and the trailing edge portion of the airfoil comprises blending a transition from a pressure side of the airfoil to the second surface.

13. The method of claim 9 , wherein removing material from the second surface of the at least one of the leading edge portion and the trailing edge portion of the airfoil comprises blending a transition from a suction side of the airfoil to the second surface.

14. The method of claim 7 , wherein removing material from the at least one of the leading edge portion and the trailing edge portion of the airfoil comprises utilizing a diamond cutter to cut away material.

15. The method of claim 7 , further comprising casting the airfoil from raw materials to form the leading edge, the leading edge portion, the trailing edge, and the trailing edge portion.

16. The method of claim 7 , wherein removing material from at least one of the leading edge portion and the trailing edge portion of the airfoil comprises removing body material of the airfoil.

17. The method of claim 7 , wherein removing material from at least one of the leading edge portion and the trailing edge portion of the airfoil comprises removing coating material of the airfoil.

18. The method of claim 7 , wherein removing material from the at least one of the leading edge portion and the trailing edge portion of the airfoil comprises reducing the dimension by between about 25% and about 75%.

19. A method of manufacturing an airfoil of a gas turbine engine, the method comprising:

fixing the airfoil in a workpiece space, the airfoil having a leading edge, a leading edge portion, a trailing edge, a trailing edge portion, a suction side, and a pressure side;

detecting a position of the airfoil in the workpiece space by moving a force-sensing element across a first surface of one of the leading edge portion and the trailing edge portion of the airfoil; and

removing material from a second surface, opposite the first surface, of the one of the leading edge portion and the trailing edge portion of the airfoil to reduce a dimension of the one of the leading edge portion and the trailing edge portion of the airfoil, wherein removing material from the second surface of the airfoil is performed substantially simultaneously as moving the force-sensing element across the first surface of the airfoil by using a clamp force-sensing element having a sensing portion and a cutting portion.