A thermal barrier coating for an internal combustion engine includes an insulating thermal spray coating, where a chosen material of the insulating thermal spray coating has a thermal conductivity lower than 2 W/mK in fully dense form and the chosen material includes a coefficient of thermal expansion within 5 ppm/K of a coefficient of thermal expansion of a material of a component of the internal combustion engine upon which the coating is placed.

Described herein is a method of constructing a landing pad using a rocket engine while in-flight. Among other benefits, this method can reduce ejecta that otherwise would occur during landing on an unimproved surface. While a spacecraft is hovering over an unimproved surface, the spacecraft can inject particles into its rocket engine, after which the particles absorb heat from the engine and are projected at ballistic speeds toward the unimproved surface to create a landing pad. After constructing the landing pad and waiting for the landing pad to cool, the spacecraft can land on the landing pad. Also described herein are landing pads created from such particles as they impact the surface in a disc splat mode into the unimproved surface.

A component for a processing chamber includes a ceramic body having at least one surface with a first average surface roughness. The component further includes a conformal protective layer on at least one surface of the ceramic body, wherein the conformal protective layer is a plasma resistant rare earth oxide film having a substantially uniform thickness of less than 300 μm over the at least one surface and having a second average surface roughness that is less than the first average surface roughness.

A component for a processing chamber includes a ceramic body having at least one surface with a first average surface roughness. The component further includes a conformal protective layer on at least one surface of the ceramic body, wherein the conformal protective layer is a plasma resistant rare earth oxide film having a substantially uniform thickness of less than 300 μm over the at least one surface and having a second average surface roughness that is less than the first average surface roughness.

Through the plasma spraying technology and the cold spraying high-speed deposition technology, an evenly distributed protective coating is formed on the surface of a plasma etching chamber. The protective coating, having a double-layer composite structure, includes a metal+Y.sub.2O.sub.3 coating as a metal+Y.sub.2O.sub.3 transition layer deposited by plasma spraying as a lower layer of the double-layer composite structure, and a high-purity Y.sub.2O.sub.3 ceramic coating coated on the metal+Y.sub.2O.sub.3 transition layer as an upper layer of the double-layer composite structure, the metal+Y.sub.2O.sub.3 transition layer is configured to reduce the difference in expansion coefficient between the Y.sub.2O.sub.3 ceramic coating and the metal substrate, and enhance the bonding force between the Y.sub.2O.sub.3 ceramic coating and the metal substrate; the high-purity Y.sub.2O.sub.3 ceramic coating is formed by depositing Y.sub.2O.sub.3 ceramic powders on the metal+Y.sub.2O.sub.3 transition layer at high speed through cold spraying high-speed deposition.

A coated article including an article having a surface; an oxidation resistant bond coat layer deposited on the surface, the oxidation resistant bond coat layer comprising a healing silica matrix and at least one oxygen scavenger forming a metal silicide network dispersed within the healing silica matrix; and a top coat layer disposed upon the oxidation resistant bond coat layer, whereby the oxidation resistant bond coat layer is operable to seal a crack in the top coat layer.

A coated article including an article having a surface; an oxidation resistant bond coat layer deposited on the surface, the oxidation resistant bond coat layer comprising a healing silica matrix and at least one oxygen scavenger forming a metal silicide network dispersed within the healing silica matrix; and a top coat layer disposed upon the oxidation resistant bond coat layer, whereby the oxidation resistant bond coat layer is operable to seal a crack in the top coat layer.

An embodiment relates to a cladded composite comprising a cladding layer of a bulk metallic glass and a substrate; wherein the bulk metallic glass comprises approximately 0% crystallinity, approximately 0% porosity, less than 50 MPa thermal stress, approximately 0% distortion, approximately 0 inch heat affected zone, approximately 0% dilution, and a strength of about 2,000-3,500 MPa.

An embodiment relates to a cladded composite comprising a cladding layer of a bulk metallic glass and a substrate; wherein the bulk metallic glass comprises approximately 0% crystallinity, approximately 0% porosity, less than 50 MPa thermal stress, approximately 0% distortion, approximately 0 inch heat affected zone, approximately 0% dilution, and a strength of about 2,000-3,500 MPa.

The present invention relates to a method for continuously manufacturing an abradable sealing element, this element comprising a support substrate covered by a coating comprising at least two successive layers, each comprising a sublayer of abradable material and a sublayer of erosion-control material. This method is noteworthy in that it comprises the steps consisting in: —a) placing at least one support substrate on a rotary carousel around which are placed at least two thermal spray torches enabling the sublayer of abradable material and that of erosion-control material to be deposited, —b) rotating the carousel so as to bring said support substrate successively opposite one then the other of the two torches and to carry out the deposition of the various sublayers and to repeat this operation so as to obtain said sealing element.