Forming cooling aperture(s) using electrical discharge machining
A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate comprising electrically conductive material having an outer coating comprising non-electrically conductive material applied over a surface of the substrate. A preform aperture is formed in the preform component using an electrical discharge machining electrode. The preform aperture includes a meter section of a cooling aperture in the substrate. The preform aperture also includes a pilot hole in the outer coating. A diffuser section of the cooling aperture is formed in at least the outer coating using a second machining process.
1. A manufacturing method, comprising:
providing a preform component for a turbine engine, the preform component comprising a substrate comprising electrically conductive material having an outer coating comprising non-electrically conductive material applied over a surface of the substrate;
forming a preform aperture in the preform component using an electrical discharge machining electrode, the preform aperture including a meter section in the substrate, the preform aperture further including a pilot hole in the outer coating, and the forming of the preform aperture comprising
removing a portion of the substrate using an electric current discharged from the electrical discharge machining electrode to form the meter section; and
directing fluid through a bore of the electrical discharge machining electrode to puncture the outer coating and form the pilot hole; and
forming a diffuser section in at least the outer coating using a second machining process;
wherein a cooling aperture includes the meter section and the diffuser section.
2. The manufacturing method of claim 1 , wherein the diffuser section is formed in the preform component based on a location of the pilot hole.
3. The manufacturing method of claim 1 , wherein the pilot hole is expanded within the outer coating during the forming of the diffuser section.
4. The manufacturing method of claim 1 , wherein the diffuser section extends into the substrate.
5. The manufacturing method of claim 1 , wherein the preform component further comprises an inner coating between the substrate and the outer coating, and the preform aperture extends through the inner coating.
6. The manufacturing method of claim 5 , wherein the inner coating comprises electrically conductive material that is different than the electrically conductive material of the substrate.
7. The manufacturing method of claim 1 , wherein the electrically conductive material comprises metal, and the non-electrically conductive material comprises ceramic.
8. The manufacturing method of claim 1 , wherein the second machining process comprises a laser machining process.
9. The manufacturing method of claim 1 , wherein the second machining process comprises a water-jet guided laser machining process.
10. The manufacturing method of claim 1 , wherein the second machining process comprises an abrasive water jet machining process.
11. The manufacturing method of claim 1 , wherein the providing of the preform component comprises applying the outer coating over the substrate.
12. The manufacturing method of claim 1 , wherein the diffuser section is configured as a single lobe diffuser section.
13. The manufacturing method of claim 1 , wherein the diffuser section is configured as a multi lobe diffuser section.
14. The manufacturing method of claim 1 , wherein the preform component comprises a preform of an airfoil for the turbine engine.
15. The manufacturing method of claim 1 , wherein the preform component comprises a preform of a flowpath wall for the turbine engine.
16. A manufacturing method, comprising:
providing a preform component for a turbine engine, the preform component extending between a component first surface and a component second surface, the preform component comprising a substrate comprising metal and an outer coating comprising ceramic applied over a surface of the substrate;
forming a preform aperture in the preform component starting at the component first surface using an electrical discharge machining process, the preform aperture including a meter section in the substrate, the preform aperture further including a pilot hole in the outer coating, and the forming of the preform aperture comprising
removing a portion of the substrate using an electric current discharged from an electrode to form the meter section; and
directing fluid through a bore of the electrode to liberate a portion of the outer coating and form the pilot hole; and
forming a diffuser section in at least the outer coating using a second machining process;
wherein a cooling aperture includes the meter section and the diffuser section.
17. The manufacturing method of claim 16 , wherein the diffuser section is aligned with the meter section based on a location of the pilot hole.
18. A manufacturing method, comprising:
providing a preform component for a turbine engine, the preform component comprising a substrate comprising electrically conductive material and an outer coating comprising non-electrically conductive material applied over a surface of the substrate;
removing a portion of the substrate using an electric current discharged from an electrode to form a meter section in the substrate;
directing fluid through a bore of the electrode against a backside of the outer coating to form a pilot hole in the outer coating; and
forming a diffuser section in at least the outer coating using a laser machining process;
wherein a cooling aperture includes the meter section and the diffuser section.