Patent Number: 6,168,871

Title: Method of forming high-temperature components and components formed thereby

Abstract: A method for forming an exterior surface of a high-temperature component, such as a blade or vane of a gas turbine engine. The method entails forming a shell by a powder metallurgy technique that yields an airfoil whose composition can be readily tailored for the particular service conditions of the component. The method generally entails providing a pair of inner and outer mold members that form a cavity therebetween. One or more powders and any desired reinforcement material are then placed in the cavity and then consolidated at an elevated temperature and pressure in a non-oxidizing atmosphere. Thereafter, at least the outer mold member is removed to expose the consolidated powder structure. By appropriately shaping the mold members to tailor the shape of the cavity, the consolidated powder structure has the desired shape for the exterior shell of a component, such that subsequent processing of the component does not require substantially altering the configuration of the exterior shell. The airfoil can be produced as a free-standing article or produced directly on a mandrel that subsequently forms the interior structure of the component. In one embodiment, an airfoil is configured to have double walls through which cooling air flows.

Inventors: Ritter; Ann Melinda (Albany, NY), Dupree; Paul Leonard (Scotia, NY), Jackson; Melvin Robert (Niskayuna, NY), Wemple, Jr.; Donald Norman (Schenectady, NY)

Assignee: General Electric Company

International Classification: B22F 3/12 (20060101); B22F 7/06 (20060101); B22F 5/04 (20060101); B23P 15/04 (20060101); F01D 5/28 (20060101); F01D 5/18 (20060101); B22F 007/02 ()

Expiration Date: 01/02/2018