Gas turbine component and process for producing gas turbine component
First Claim
1. A process of producing a ceramic matrix composite gas turbine component, the process comprising:
- modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers;
wherein modifying the surface includes machining with a non-abrasive material, machining with the non-abrasive material applying a contact pressure on the surface and depositing at least a portion of the non-abrasive material into crevasses on the surface.
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Accused Products
Abstract
A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.
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Citations
42 Claims
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1. A process of producing a ceramic matrix composite gas turbine component, the process comprising:
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modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers; wherein modifying the surface includes machining with a non-abrasive material, machining with the non-abrasive material applying a contact pressure on the surface and depositing at least a portion of the non-abrasive material into crevasses on the surface. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20)
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21. A process of producing a ceramic matrix composite gas turbine component, the process comprising:
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modifying a surface positioned in a seal slot along a hot gas path of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 3 micrometers; and positioning a seal in the seal slot; wherein the modified surface is substantially devoid of fibers; and wherein modifying includes vapor depositing silicon, and then machining with a non-abrasive material, machining with the non-abrasive material applying a contact pressure on the surface and depositing at least a portion of the non-abrasive material into crevasses on the surface.
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22. A process of machining a ceramic matrix composite surface of a gas turbine component, the process comprising:
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providing a non-abrasive material; positioning the non-abrasive material adjacent to the ceramic matrix composite surface of the gas turbine component; and applying a contact pressure on the surface and depositing at least a portion of the non-abrasive material into crevasses on the ceramic matrix composite surface by conducting at least about 300 machining cycles; wherein each of the machining cycles comprises moving at least one of the non-abrasive material or the ceramic matrix composite surface relative to the other. - View Dependent Claims (23, 24, 25, 26, 27, 28, 29, 30, 31, 32)
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33. A process of producing a ceramic matrix composite gas turbine component, the process comprising:
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modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers, wherein the surface is selected from the group consisting of a damper cavity surface for a damper pin in the ceramic matrix composite gas turbine component, a dovetail attachment face of a ceramic matrix composite gas turbine rotating airfoil, and the dovetail attachment face of a ceramic matrix composite gas turbine non-rotating airfoil; wherein modifying includes machining with a non-abrasive material, machining with the non-abrasive material applying a contact pressure on the surface and depositing at least a portion of the non-abrasive material into crevasses on the surface, the crevasses being formed by plies selected from the group consisting of the unreinforced matrix plies and fiber-reinforced plies. - View Dependent Claims (34, 35, 36, 37, 38, 39, 40, 41, 42)
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Specification