Forming cooling aperture(s) using electrical discharge machining
AssigneeRaytheon Technologies Corporation
InventorJames M. Koonankeil
Life of this patent
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Abstract
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.
Claims18
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.
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.
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.
Dependencies are inferred from the claim text.