Backside coating cooling passage
AssigneeUnited Technologies Corporation
InventorSteven W. Burd
Life of this patent
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Abstract
A component is provided for a gas turbine engine includes a substrate with an aperture. The component also includes a backside coating on a backside of the substrate and at least partially onto an inner boundary of the aperture, where the backside coating forms a passage with the aperture. A method of forming a shaped aperture in a component of a gas turbine engine is provided. The method includes applying a backside coating on a backside of a substrate and at least partially onto an inner boundary of an aperture. The backside coating forms a passage with the aperture including a convergent section, a divergent section and a throat therebetween.
Claims20
A component for a gas turbine engine, the component comprising:
- a substrate with an aperture;
- and
- a backside coating on a backside of the substrate to form a shaped passage with the aperture.
A liner assembly for a gas turbine engine, the liner assembly comprising:
- a hot sheet with a multiple of apertures;
- and
- a backside coating on a backside of the hot sheet and at least partially onto an inner boundary of each of the multiple of apertures, the backside coating forming a passage with each of the multiple of apertures including a convergent section, a divergent section and a throat therebetween.
A method of forming a shaped aperture in a component of a gas turbine engine, the method comprising:
- applying a backside coating on a backside of a substrate and at least partially onto an inner boundary of an aperture, the backside coating forming a passage with the aperture including a convergent section, a divergent section and a throat therebetween.
Dependencies are inferred from the claim text.