Ceramic matrix composite surface roughness

1. A method of improving surface roughness of ceramic matrix composites (CMCs), the method comprising:

completing a formation of the CMCs and a chemical vapor infiltration (CVI) process to initially coat the CMCs;

inspecting a CMC surface;

identifying, from a result of the inspecting, a defect in the CMC surface in a form of a deviation of a fiber of the CMC surface from a nominal shape of the fiber that negatively impacts a surface roughness characteristic thereof;

locally targeting and ablating the defect by smoothing the fiber of the CMC surface; and

re-inspecting the CMC surface to ensure that the defect is corrected,

wherein the ablating comprises one of laser machining and an abrasive process to smooth the fiber of the CMC surface at and around a location of the defect without smoothing neighboring fibers.

2. The method according to claim 1 , wherein the inspecting, the locally targeting and ablating and the reinspecting comprises programing tooling to follow a macroscopic contour of the CMC surface and to follow a microscopic contour of the fiber and other fibers of the CMCs of the CMC surface.

3. The method according to claim 1 , wherein the inspecting comprises one of a structured light inspection and a digital inspection.

4. The method according to claim 1 , wherein the inspecting is executed at a resolution of about 2/10000″.

5. The method according to claim 1 , further comprising repeating the CVI process at and around a location of the defect to re-initially coat the CMCs at and around the location of the defect.

6. The method according to claim 1 , further comprising:

applying an environmental barrier coating (EBC) comprising a bond coat and a top coat to the CMC surface; and

repeating the inspecting, the identifying, the locally targeting and ablating and the re-inspecting with respect to defects in the EBC.

7. A method of improving surface roughness of an aerodynamic component formed of ceramic matrix composites (CMCs), the method comprising:

completing a formation of the aerodynamic component formed of the CMCs and a chemical vapor infiltration (CVI) process to initially coat the CMCs;

inspecting a CMC surface of the aerodynamic component;

identifying, from a result of the inspecting, a defect in the CMC surface in a form of a deviation of a fiber of the CMC surface from a nominal shape of the fiber that negatively impacts a surface roughness characteristic thereof;

locally targeting and ablating the defect by smoothing the fiber of the CMC surface; and

re-inspecting the surface to ensure that the defect is corrected,

wherein the ablating comprises one of laser machining and an abrasive process to smooth the fiber of the CMC surface at and around a location of the defect without smoothing neighboring fibers.

8. The method according to claim 7 , wherein the aerodynamic component comprises one of a vane, an airfoil and a blade outer air seal (BOAS) of a gas turbine engine.

9. The method according to claim 7 , wherein the inspecting, the locally targeting and ablating and the reinspecting comprises programing tooling to follow a macroscopic contour of the CMC surface and to follow a microscopic contour of the fiber and other fibers of the CMCs of the CMC surface.

10. The method according to claim 7 , wherein the inspecting comprises one of a structured light inspection and a digital inspection.

11. The method according to claim 7 , wherein the inspecting is executed at a resolution of about 2/10000″.

12. The method according to claim 7 , further comprising repeating the CVI process at and around a location of the defect to re-initially coat the CMCs at and around the location of the defect.

13. The method according to claim 7 , further comprising:

applying an environmental barrier coating (EBC) comprising a bond coat and a top coat to the CMC surface; and

repeating the inspecting, the identifying, the locally targeting and ablating and the re-inspecting with respect to defects in the EBC.