초록 ▼

A turbine engine component is provided that has a surface that contains a plurality of depressions that are effective to increase the surface area of the component. The depressions are generally concave in contour and improve the heat transfer characteristics of the component. Methods for forming th

A turbine engine component is provided that has a surface that contains a plurality of depressions that are effective to increase the surface area of the component. The depressions are generally concave in contour and improve the heat transfer characteristics of the component. Methods for forming the turbine engine components are also disclosed.

대표청구항 ▼

1. A method for forming a turbine engine component, the method comprising the steps of: providing a substrate; applying a layer on the substrate, said layer comprising a matrix phase and a discrete particulate phase; and removing selectively and completely at least the discrete particulate phas

1. A method for forming a turbine engine component, the method comprising the steps of: providing a substrate; applying a layer on the substrate, said layer comprising a matrix phase and a discrete particulate phase; and removing selectively and completely at least the discrete particulate phase, leaving behind a plurality of depressions in the matrix phase. 2. The method of claim 1, further comprising a step of heating the substrate to fuse the discrete particulate phase to the substrate, prior the step of removing. 3. The method of claim 1, wherein the discrete particulate phase is removed by etching. 4. The method of claim 1, wherein the substrate comprises a superalloy. 5. The method of claim 1, wherein the substrate is a nickel-based superalloy, and includes at least one, component from the group consisting of cobalt, aluminum, silicon, chromium, tungsten, molybdenum, titanium, and iron. 6. The method of claim 1, wherein the turbine engine component is a component from the group consisting of a combustor liner, a combustor dome, a bucket or blade, a nozzle or vane, a shroud, an airfoil, and a shroud clearance control component. 7. The method of claim 1, wherein the matrix phase comprises a braze alloy. 8. The method of claim 7, wherein the braze alloy comprises a nickel-based or a cobalt-based alloy. 9. The method of claim 1, wherein the discrete particulate phase comprises particles that are generally spherical. 10. The method of claim 9, wherein the particles have an average aspect ratio less than 2.0. 11. The method of claim 10, wherein the particles have an average aspect ratio less than about 1.5. 12. The method of claim 11, wherein the particles have an average aspect ratio less than about 1.2. 13. The method of claim 9, wherein the particles have an average particle size within a range of about 125 microns to about 4000 microns. 14. The method of claim 13, wherein the particles have an average particle size of about 125 to about 2050 microns. 15. A method for forming a turbine engine component, the method comprising the steps of: providing a substrate comprised of a nickel-based or cobalt-based superalloy; applying a layer on the substrate, said layer comprising a matrix phase and a discrete particulate phase comprising particles having an aspect ratio of not greater than 1.5; heating the substrate to fuse the discrete particulate phase to the substrate; and removing selectively and completely at least the discrete particulate phase, leaving behind a plurality of depressions in the matrix phase.