FURNACE BRAZE DEPOSITION OF HARDFACE COATING ON WEAR SURFACE

A disclosed method of hard coating a wear surface of a valve of an aircraft air management system is performed by depositing a hardface alloy powder onto the wear surface, heating the wear surface and the hardface alloy powder to transform the hardface alloy powder into a molten liquid mass, and subsequently cooling the molten liquid hardface alloy mass to solidify the hardface alloy onto the wear surface. The disclosed process provides for localized application and subsequent bonding of the hardface alloy to discrete portions of the wear surface. The solidified hardface alloy coating may then be machined to obtain specific wear surface geometries. 1. An air management system for an aircraft comprising:a valve plate movable for controlling airflow through a passage;a valve shaft including an axial end supporting the valve plate within the passage; anda thrust plate for controlling axial movement of the valve shaft, the thrust plate including a thrust surface in contact with the axial end of the valve shaft, the thrust surface including a hardface alloy coating formed from a hardface alloy powder melted and solidified on the thrust surface.2. The air management system as recited in claim 1 , wherein the thrust surface is recessed and at least partially surrounded by walls.3. The air management system as recited in claim 2 , wherein the hardface alloy powder is disposed only on the thrust surface and not the walls.5. The air management system as recited in claim 2 , wherein the thrust surface is spaced apart from the walls.6. The air management system as recited in claim 2 , wherein the valve shaft includes a first diameter received within the thrust plate that is less than a second diameter outside of the thrust plate.7. The air management system as recited in claim 1 , wherein the hardface alloy is deposited onto the thrust surface as a powder and transformed into a mostly molten liquid mass on the thrust surface by elevating the thrust plate and the hardface alloy ...

Thrust plate for butterfly valve

A thrust plate for a butterfly valve includes a thrust plate body that defines a recess. The recess extends between a bottom thrust surface, side walls and an open top. A wear-resistant coating is located on the bottom thrust surface.

Thrust plate for butterfly valve

A thrust plate for a butterfly valve includes a thrust plate body that defines a recess. The recess extends between a bottom thrust surface, side walls and an open top. A wear-resistant coating is located on the bottom thrust surface.

THRUST PLATE FOR BUTTERFLY VALVE

A thrust plate for a butterfly valve includes a thrust plate body that defines a recess that extends between a bottom thrust surface, side walls, and an open top. There is a nickel-based or cobalt-based wear-resistant coating located on the bottom thrust surface. The wear-resistant coating is harder than the thrust plate body. 1. A thrust plate for a butterfly valve , the thrust plate comprising:a thrust plate body defining a recess that extends between a bottom thrust surface, side walls, and an open top; anda nickel-based or cobalt-based wear-resistant coating located on the bottom thrust surface, the wear-resistant coating being harder than the thrust plate body.2. The thrust plate as recited in claim 1 , wherein the wear-resistant coating is a nickel-based alloy.3. The thrust plate as recited in claim 1 , wherein the wear-resistant coating includes chromium boride.4. The thrust plate as recited in claim 1 , wherein the wear-resistant coating includes chromium carbide.5. The thrust plate as recited in claim 1 , wherein the thrust plate body is stainless steel.6. The thrust plate as recited in claim 5 , wherein a ratio of a hardness of the wear-resistant coating to a hardness of the stainless steel is at least 2.3.711. The thrust plate as recited in claim 6 , wherein the recess defines a recess diameter (RD) and the wear-resistant coating defines an average coating thickness (CT) claim 6 , and ratio RD/CT is between 33.2 and 56.67.822. The thrust plate as recited in claim 7 , wherein the recess defines a recess depth (RD) and the wear-resistant coating defines an average coating thickness (CT) claim 7 , and a ratio RD/CT is between 5 and 10.33.9. The thrust plate as recited in claim 8 , wherein the thrust plate body claim 8 , with the exception of the bottom thrust surface claim 8 , is free of the wear-resistant coating.10. The thrust plate as recited in claim 1 , wherein the thrust plate body is a material selected from a group consisting of nickel-based alloy ...

Furnace braze deposition of hardface coating on wear surface

A disclosed method of hard coating a wear surface (34;70) of a valve of an aircraft air management system (12) is performed by depositing a hardface alloy powder (42) onto the wear surface (34;70), heating the wear surface (34;70) and the hardface alloy powder (42) to transform the hardface alloy powder (42) into a molten liquid mass (46), and subsequently cooling the molten liquid hardface alloy mass (46) to solidify the hardface alloy (48;64) onto the wear surface (34;70). The disclosed process provides for localized application and subsequent bonding of the hardface alloy (48;64) to discrete portions of the wear surface (34;70). The solidified hardface alloy coating (38) may then be machined to obtain specific wear surface geometries.

Wear interface for butterfly valve

Interlocking dovetail geometry joint

A method of manufacturing a heat exchanger. The method includes additively manufacturing a first body with a first plurality of passages extending through the first body. Additively manufacturing a second body with a second plurality of passages extending through the second body. The method also includes, interlocking the first body with the second body such that the first plurality of passages is aligned with the second plurality of passages and fluidically connected with the second plurality of passages.

Furnace braze deposition of hardface coating on wear surface

A disclosed method of hard coating a wear surface of a valve of an aircraft air management system is performed by depositing a hardface alloy powder onto the wear surface, heating the wear surface and the hardface alloy powder to transform the hardface alloy powder into a molten liquid mass, and subsequently cooling the molten liquid hardface alloy mass to solidify the hardface alloy onto the wear surface. The disclosed process provides for localized application and subsequent bonding of the hardface alloy to discrete portions of the wear surface. The solidified hardface alloy coating may then be machined to obtain specific wear surface geometries.