Energy beam positioning during formation of a cooling aperture
A manufacturing method is provided during which a preform component for a turbine engine is provided. A cooling aperture is formed in the preform component. The cooling aperture includes a centerline, an inlet and an outlet. The cooling aperture extends longitudinally along the centerline through a wall of the preform component from the inlet to the outlet. The forming of the cooling aperture includes forming a first portion of the cooling aperture using a machining tool implement with a first toolpath that is angularly offset from the centerline by a first angle between thirty-five degrees and ninety degrees.
1. A manufacturing method, comprising:
providing a preform component for a turbine engine; and
forming a cooling aperture in the preform component, the cooling aperture including a centerline, an inlet and an outlet, and the cooling aperture extending longitudinally along the centerline through a wall of the preform component from the inlet to the outlet;
the forming of the cooling aperture comprising forming a first portion of the cooling aperture using a machining tool implement with a first toolpath that is angularly offset from the centerline by a first angle between thirty-five degrees and ninety degrees.
2. The manufacturing method of claim 1 , wherein the first angle is equal to or greater than forty-five degrees.
3. The manufacturing method of claim 1 , wherein the first angle is equal to or greater than sixty degrees.
4. The manufacturing method of claim 1 , wherein the first angle is equal to or greater than seventy-five degrees.
5. The manufacturing method of claim 1 , wherein the forming of the cooling aperture further comprises forming a second portion of the cooling aperture using the machining tool implement with a second toolpath that is angularly offset from the centerline by a second angle less than or equal to thirty-five degrees.
6. The manufacturing method of claim 1 , wherein the forming of the cooling aperture further comprises forming a second portion of the cooling aperture using the machining tool implement with a second toolpath that is parallel with the centerline.
7. The manufacturing method of claim 1 , wherein
the machining tool implement removes material from the preform component to form a sidewall surface of the cooling aperture; and
the first toolpath is coincident with the sidewall surface.
8. The manufacturing method of claim 7 , wherein the first toolpath is angularly offset from the sidewall surface by a second angle that is equal to or greater than forty-five degrees.
9. The manufacturing method of claim 1 , wherein
the forming of the cooling aperture further comprises forming a second portion of the cooling aperture using the machining tool implement with a second toolpath that is angularly offset from the centerline by a second angle; and
the first toolpath is angularly offset from the second toolpath by a third angle equal to or greater than forty-five degrees.
10. The manufacturing method of claim 9 , wherein the third angle is equal to or greater than sixty degrees.
11. The manufacturing method of claim 9 , wherein the second angle is between thirty-five degrees and ninety degrees.
12. The manufacturing method of claim 1 , wherein
the forming of the cooling aperture further comprises forming a second portion of the cooling aperture using the machining tool implement with a second toolpath that is angularly offset from the centerline by a second angle between thirty-five degrees and ninety degrees; and
the first toolpath is non-coplanar with the second toolpath.
13. The manufacturing method of claim 1 , wherein the cooling aperture includes a meter section and a diffuser section.
14. The manufacturing method of claim 1 , wherein the preform component comprises at least one of
a preform of an airfoil for the turbine engine; or
a preform of a flowpath wall for the turbine engine.
15. The manufacturing method of claim 1 , wherein the machining tool implement comprises an energy beam, and the first toolpath comprises a first trajectory of the energy beam.
16. The manufacturing method of claim 1 , wherein the machining tool implement comprises a fluid jet, and the first toolpath comprises a first trajectory of the fluid jet.
17. The manufacturing method of claim 1 , wherein the machining tool implement comprises a machining bit, and the first toolpath comprises a centerline of the machining bit.
18. The manufacturing method of claim 1 , wherein the cooling aperture is formed with a compound intersection between a curved surface and a second surface.
19. A manufacturing method, comprising:
providing a preform component for a turbine engine; and
forming a cooling aperture in the preform component, the cooling aperture including a centerline, an inlet and an outlet, and the cooling aperture extending longitudinally along the centerline through a wall of the preform component from the inlet to the outlet;
the forming of the cooling aperture comprising
forming a first portion of the cooling aperture using a machining tool implement with a first toolpath; and
forming a second portion of the cooling aperture using the machining tool implement with a second toolpath that is angularly offset from the first toolpath by a first angle greater than forty-five degrees.
20. A manufacturing method, comprising:
providing a preform component for a turbine engine; and
forming a cooling aperture in the preform component, the cooling aperture including a centerline, an inlet and an outlet, and the cooling aperture extending longitudinally along the centerline through a wall of the preform component from the inlet to the outlet;
the forming of the cooling aperture comprising removing material from the preform component using a machining tool implement to form a sidewall surface of the cooling aperture, and the machining tool implement having a first toolpath that is coincident with the sidewall surface.