Nano-coating thermal barrier and method for making the same
AssigneeThe Boeing Company
InventorsJames C. Russell, Tresha L. White, Bryan Shiflett, Pazion Cherinet, Scott Wadley, Carol Barnhart, Vyacheslav Khozikov, Kyle Nakamoto
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Abstract
A coating is adapted to be applied to a substrate for managing the flow of heat traveling through the substrate. The coating comprises an array of metal nano-particles held in a glassy matrix.
Claims60
A coating adapted to be applied to a substrate for managing the flow of heat traveling through the substrate, comprising:
- an array of metal nano-particles held in a glassy matrix material.
A coating adapted to be applied to a substrate for managing the flow of heat traveling through the substrate, comprising:
- an array of nano-particles held in a matrix material, wherein the nano-particles have a thermal conductivity substantially greater than that of the matrix material.
A thermal barrier coating, comprising:
- at least two layers each including an array of metal nano-particles held in a glass matrix, wherein the layers have characteristics respectively tailored to reduce thermal transport in two ranges of temperatures.
A thermal barrier coating for an aircraft part, comprising:
- a glassy enamel matrix;
- and
- a plurality of metal nano-particles held in the matrix, the nano-particles being arranged in a 3-D array and spaced apart at substantially constant distances substantially equal to the wavelength of phonons transporting thermal energy through the coating.
A method of making a thermal barrier coating, comprising:
- applying a glassy compound to metal nano-particles;
- and
- fusing the glassy compound into a glass matrix holding the nano-particles.
A method of forming a thermal barrier coating on a substrate, comprising:
- coating metal nano-particles with a glassy compound;
- self-assembling the coated nano-particles into a quasi-regular 3-D array;
- applying the assembled nano-particles to the substrate;
- and,
- fusing the glassy compound coatings into a substantially homogeneous matrix.
A method for managing the flow of heat traveling through a substrate, comprising:
- applying a coating on the substrate, including assembling a 3-D array of metal particles in a matrix.
A thermal barrier coating for an aerospace vehicle component, comprising:
- a glassy compound matrix selected from the group consisting of—
- fused quartz,
- soda lime glass,
- boro-silicate glass, and
- alumino-silica glass.
- a quasi-regular 3-D array of spherically shaped metal nano-particles held in the matrix and selected from the group consisting of Tungsten and Cobalt, the metal nano-particles having a thermal conductivity substantially greater than that of the matrix and being spaced apart from each other a distance substantially equal to the wavelength of phonons transporting thermal energy through the matrix.
A method of forming a thermal barrier on a component of an aerospace vehicle, comprising:
- selecting a temperature range within which the thermal barrier is to reduce the thermal energy transported to the component;
- selecting metal nano-particles for use in the coating, including selecting a material for the nano-particles and selecting the size for the nano-particles based on the selected temperature range;
- selecting a glassy compound matrix material in which the nano-particle may be held based on the thermal conductivity of the material selected for use as the nano-particles;
- forming a glassy compound shell around the nano-particles by spraying a glassy compound powder onto the nano-particles;
- forming a slurry by mixing a solvent with the coated nano-particles;
- applying the slurry to the surface of the component;
- self-assembling the coated nano-particles into a quasi-regular 3-D array, including evaporating the solvent from the slurry;
- and,
- forming a substantially homogeneous matrix for supporting the 3-D array of nano-particles and bonding the matrix to the surface of the component by fusing the glassy compound shells together, including heating the glassy compound to at least its melting point.
Dependencies are inferred from the claim text.