摘要:
A method for improving the surface of an aluminum alloy article includes manufacturing the aluminum alloy article using an additive manufacturing technique, wherein the article as-manufactured includes one or more of cracks, roughness, or porosity at a surface of the article; coating the surface of the aluminum alloy article with a diffusion element, the diffusion element being capable of diffusing at least 0.2 mils into the article; heating the aluminum alloy article coated with the diffusion element to cause the diffusion element to diffuse the at least 0.2 mils into the article, thereby forming a diffusion layer of at least 0.2 mils in thickness comprising both aluminum alloy and diffusion element; and removing the diffusion layer from the aluminum alloy article, whereby upon the removing, a resulting improved surface of the article comprises fewer or smaller cracks, reduced roughness, or reduced porosity.
摘要:
A method for improving the surface of an aluminum alloy article includes manufacturing the aluminum alloy article using an additive manufacturing technique, wherein the article as-manufactured includes one or more of cracks, roughness, or porosity at a surface of the article; coating the surface of the aluminum alloy article with a diffusion element, the diffusion element being capable of diffusing at least 0.2 mils into the article; heating the aluminum alloy article coated with the diffusion element to cause the diffusion element to diffuse the at least 0.2 mils into the article, thereby forming a diffusion layer of at least 0.2 mils in thickness comprising both aluminum alloy and diffusion element; and removing the diffusion layer from the aluminum alloy article, whereby upon the removing, a resulting improved surface of the article comprises fewer or smaller cracks, reduced roughness, or reduced porosity.
摘要:
An airfoil assembly for a turbine engine can comprise an airfoil including an outer wall extending between a root and a tip, a tip opening fluidly coupled to a first source of air, a root opening fluidly coupled to a second source of air, and an insert with impingement openings.
摘要:
An axial fan includes a fan frame, an impeller and a motor. The fan frame has a frame body, a base and plural connecting members. The base is disposed at the center of a side of the frame body. The connecting members connect the frame body to the base. The impeller is accommodated in the frame body and disposed on the base. The impeller has a rotating shaft, a hub and plural blades disposed around the hub. The motor is disposed on the base and connects with the rotating shaft to drive the impeller to rotate. When the impeller rotates forwardly, the airflow is induced to flow through the connecting members, blades, and one side of the frame body away from the base. When the impeller rotates reversely, the airflow is induced to flow through the side of the frame body, blades and connecting members.
摘要:
A composite component is disclosed. The composite component may comprise a metal plating deposited on a surface of the composite component, and a metallic feature adhesively bonded to the metal plating. The composite component may further comprise an adhesive layer between the metal plating and the metallic feature. The metal plating may provide a metal-to-metal interface between the surface of the composite component and the metallic feature.
摘要:
A system may include a fluid source fluidically coupled to a plenum; a thermal camera; at least one flow meter; and a computing device communicatively connected to the at least one flow meter and the thermal camera. The computing device may be configured to receive flow rate values from the at least one flow meter relating to flow testing of a first component fluidically coupled to the plenum; receive thermographic image data captured by the thermal camera during flowing thermographic testing of a second component fluidically coupled to the plenum; and associate the flow rate values with the thermographic image data to produce quantitative flowing thermographic image data.
摘要:
A method for fabricating a turbomachine blade or vane of composite material including fiber reinforcement densified by a matrix is disclosed. The method includes: making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a blade platform preform; and densifying the preform with a matrix to obtain a composite material blade or vane having fiber reinforcement constituted by the preform and densified by the matrix, forming a single part with at least one incorporated platform.
摘要:
A system may include a fluid source fluidically coupled to a plenum; a thermal camera; at least one flow meter; and a computing device communicatively connected to the at least one flow meter and the thermal camera. The computing device may be configured to receive flow rate values from the at least one flow meter relating to flow testing of a first component fluidically coupled to the plenum; receive thermographic image data captured by the thermal camera during flowing thermographic testing of a second component fluidically coupled to the plenum; and associate the flow rate values with the thermographic image data to produce quantitative flowing thermographic image data.
摘要:
A method for producing a solid component which in succession includes deforming a metal bar by forging using two dies in order to obtain an intermediate component including two fins one on each side of a solid part capable of forming the base of the metal reinforcement, the two fins being at a divergent angle α; deforming the two fins of the intermediate component, altering the divergent angle α, so as to obtain the final shape of the turbomachine blade leading edge or trailing edge metal reinforcement.
摘要:
A method of measuring creep strain in a gas turbine engine component, where at least a portion of the component has a material disposed thereon, and where the material has a plurality of markings providing a visually distinct pattern. The method may include capturing an image of at least a portion of the markings after an operational period of the gas turbine engine, and determining creep strain information of the component. The creep strain information may be determined by correlating the image captured after the operational period to an image captured before the operational period.