摘要:
A turbulator fabrication process (100) and a fabricated article are provided. The turbulator fabrication process includes providing a system (200) configured for directing a first fusion energy (201) and a second fusion energy (202), positioning a turbulator material (205) on a substrate (207), and directing the first fusion energy (201) and the second fusion energy (202) toward the turbulator material (205) and the substrate (207). The directing of the first fusion energy (201) and the second fusion energy (202) modifies the turbulator material (205) forming one or more turbulators (210) on the substrate (207). The fabricated article includes a substrate (207) and one or more turbulators (210) formed on the substrate (207). Each of the one or more turbulators (210) includes at least one root portion providing a concave transition between the substrate (207) and the turbulator (210).
摘要:
Laser cladding systems (10) include a metal-filled wire (25) comprising a metal shell (26) surrounding a metal-filled core (27), wherein the metal-filled core (27) comprises at least one of a powder metal (28) or a fine wire metal (29), and, a laser (30) that produces a laser beam (32) directed onto at least a portion of a tip (22) of the metal-filled wire (25) to melt the metal shell (26) and metal-filled core (27) to produce a molten pool (47) for depositing on a substrate (40).
摘要:
According to one aspect of the invention, a method for manufacturing a hot gas path component of a turbine is provided, the method including forming cooling channels in a surface of a member. The method also includes disposing a layer on the surface of the member to enclose the cooling channels, the layer being disposed on a portion of the member to be cooled and bonding the layer to the surface, wherein bonding comprises heating the member and the layer.
摘要:
A device for diverting energy away from an arc flash occurring within an electrical power system is provided. The device comprising an arc source configured to create a second arc flash, a plasma gun configured and disposed to inject plasma in proximity of said arc source in response to the arc flash, an arc containment device configured and disposed to house said arc source and said plasma gun, said arc containment device comprising a cover configured and disposed to cover said arc source and said plasma gun, said cover comprising an inner surface and an outer surface, said inner surface being proximal to said arc source and said plasma gun, said inner surface including an insulative ceramic plasma spray coating.
摘要:
A method is provided for high velocity air plasma spraying (APS) application of a protective coating system, such as a bond coat with or without an overlying ceramic thermal barrier coat, to a superalloy metal substrate. Application of MCrAlY alloy bond particles (where M is at least one of iron, cobalt, or nickel) onto the metal substrate is maintained at a particle velocity of at least 400 meters per second (m/s), for example within a range of 400 m/s to 700 m/s. The resulting bond coat on the metal substrate has a surface roughness of about 300 to about 500 µinch Ra, and a density of at least 90% of theoretical density. The protective coating may include a ceramic thermal barrier coat applied over the bond coat by any suitable process.
摘要:
A sacrificial and erosion-resistant turbine compressor airfoil (1) includes a turbine compressor airfoil (1) having a modified airfoil surface (32). The airfoil surface (32) has an airfoil coating (61) that includes a sacrificial coating (62) comprising a layer of Al, Cr, Zn, an Ni-Al alloy, an Al-Si alloy, an Al-based alloy, a Cr-based alloy or a Zn-based alloy, an Al polymer composite, or a combination thereof, or a layer of a conductive undercoat (70) and an overcoat (72) of an inorganic matrix binder having a plurality of ceramic particles and conductive particles embedded therein disposed on the undercoat. The airfoil coating (61) also includes an sacrificial coating (62), wherein one of the sacrificial coating (62) or the erosion-resistant coating (64) is disposed on the airfoil surface (32) and the other of the corrosion-resistant coating or the erosion-resistant coating (64) is disposed on the respective one, and wherein the sacrificial coating (62) is more anodic than the airfoil surface (32) or the erosion-resistant coating (64).
摘要:
A method for modifying a wear characteristic of a rotor component in a turbine system and a modified rotor component for a turbine system are disclosed. The method includes implanting ions of one of a Group 6 element, a Group 13 element, or a metalloid element through an exterior surface of a rotor component. The rotor component is one of a rotor wheel or a distance wheel.
摘要:
A method of coating a metal substrate (17) such as the components in second and third stages of gas turbine engines in order to increase the oxidation and corrosion resistance of the metal substrate (17) under high temperature operating conditions, the method including the steps of forming a powdered mixture of a high-melt superalloy or MCrAIY component (14), where M comprises Fe, Ni and/or Co, and a low-melt component (15) containing about 2-5 wt.% silicon, boron or hafnium, applying the powdered mixture to the surface of the metal substrate (17) at room temperature using an atomized spray to form a uniform surface coating, and then heating the coated substrate surface under vacuum conditions to a temperature in the range of about 1900°F to 2275°F to obtain a uniform coating composition (19) providing oxidation resistance to the underlying substrate.