Patent application number | Description | Published |
20110311389 | METHODS FOR MANUFACTURING TURBINE COMPONENTS - A method is provided for manufacturing a turbine component. The method includes forming a first intermediate turbine article with an additive manufacturing process; encapsulating the first intermediate turbine article with an encapsulation layer to form a second intermediate turbine article; and consolidating the second intermediate turbine article to produce the turbine component. | 12-22-2011 |
20120003086 | TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME - A turbine nozzle is provided and includes a first ring having a first microstructure, a vane extending from the first ring, a first porous zone between the first ring and the vane that is more porous than the first microstructure to attenuate thermo-mechanical fatigue cracking between the vane and the first ring. Methods of manufacturing the turbine nozzle are also provided. | 01-05-2012 |
20120222306 | METHODS FOR REPAIRING TURBINE COMPONENTS - A method is provided for repairing a turbine component with a distressed portion. The method includes machining the turbine component into a first intermediate turbine article such that the distressed portion is removed; and rebuilding the first intermediate turbine article into the turbine component with an additive manufacturing process. | 09-06-2012 |
20130004680 | METHODS FOR MANUFACTURING ENGINE COMPONENTS WITH STRUCTURAL BRIDGE DEVICES - A method is provided for manufacturing an engine component. The method includes providing a structural bridge device on a base block; forming a component portion on the structural bridge device with an additive manufacturing technique; removing the component portion from the base block and the structural bridge device; and finishing the component portion to form the engine component. | 01-03-2013 |
20130071562 | METHODS FOR MANUFACTURING COMPONENTS FROM ARTICLES FORMED BY ADDITIVE-MANUFACTURING PROCESSES - A method is provided for manufacturing a component. The method includes forming a diffusion coating on a first intermediate article formed by an additive manufacturing process. The diffusion coating is removed from the first intermediate article forming a second intermediate article having at least one enhanced surface. The diffusion coating is formed by applying a layer of coating material on at least one surface of the first intermediate article and diffusion heat treating the first intermediate article and the layer. The diffusion coating comprises a surface additive layer and a diffusion layer below the surface additive layer. The formation of the diffusion coating and removal thereof may be repeated at least once. | 03-21-2013 |
20130195673 | MULTI-MATERIAL TURBINE COMPONENTS - A turbine component for a turbine of an engine is provided. The turbine component includes a blade portion of a first material; and an attachment portion coupled to the blade portion, the attachment portion being a second material. | 08-01-2013 |
20130236299 | TUBULAR HEAT EXCHANGE SYSTEMS - A heat exchange system includes a first flow passage and a second flow passage. The heat exchange system is configured to transfer heat between a first fluid flowing through the first flow passage and a second fluid flowing through the second flow passage. The first flow passage includes an inlet header, a plurality of tubes, and an outlet header. The inlet header includes a plurality of header-tube transition portions configured to allow the first fluid to flow from the inlet header and into the tubes, the plurality of header-tube transition portions each including a smoothly curved inlet portion and a tapered tube connection portion. | 09-12-2013 |
20130316084 | METHODS FOR MANUFACTURING COMPONENTS FROM ARTICLES FORMED BY ADDITIVE-MANUFACTURING PROCESSES - A method is provided for manufacturing a component. The method includes forming a diffusion coating on a first intermediate article formed by an additive manufacturing process. The diffusion coating is removed from the first intermediate article forming a second intermediate article. The diffusion coating is formed by applying a layer of coating material on at least one surface of the first intermediate article and diffusion heat treating the first intermediate article and the layer. The diffusion coating comprises a surface additive layer and a diffusion layer below the surface additive layer. The formation of the diffusion coating and removal thereof may be repeated at least once. | 11-28-2013 |
20140037983 | TITANIUM ALUMINIDE COMPONENTS AND METHODS FOR MANUFACTURING THE SAME FROM ARTICLES FORMED BY CONSOLIDATION PROCESSES - Substantially defect-free titanium aluminide components and methods are provided for manufacturing the same from articles formed by consolidation processes. The method includes providing an intermediate article comprised of a titanium aluminide alloy and formed by a consolidation process. The intermediate article is encapsulated with an aluminum-containing encapsulation layer. The intermediate article is compacted after the encapsulation step. A substantially defect-free titanium aluminide component comprises a compacted three-dimensional article comprised of titanium aluminide and formed by a consolidation process and an aluminum-containing encapsulation layer on at least one surface of the compacted three-dimensional article. The aluminum-containing encapsulation layer comprises an aluminide material, MCrAlY wherein M is cobalt, nickel, or a combination of cobalt and nickel, or TiAlCr. | 02-06-2014 |
20140060188 | NON-DESTRUCTIVE EVALUATION METHODS FOR AEROSPACE COMPONENTS - The disclosed embodiments generally relate to non-destructive evaluation methods. In an embodiment, a method for non-destructive evaluation of a aerospace component includes positioning a first plurality of sensors in the region of interest, positioning a second plurality of sensors in the region of interest, inducing a vibration in the region of interest using the first plurality of sensors and receiving a resonance frequency spectra using the second plurality of sensors, and comparing the received resonance frequency spectra against a reference spectra to determine the presence of an anomaly in the region of interest. | 03-06-2014 |
20140199175 | GAS TURBINE ENGINE COMPONENTS AND METHODS FOR THEIR MANUFACTURE USING ADDITIVE MANUFACTURING TECHNIQUES - In accordance with an exemplary embodiment, a method for manufacturing a component using additive manufacturing techniques includes providing a 3D design model for the component, adding one or more crack resistant features to the 3D design model of the component to produce an enhanced design model, and manufacturing the component using an additive manufacturing technique in accordance with the enhanced design model. The one or more crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured component. | 07-17-2014 |
20140259666 | METHODS FOR THE REPAIR OF GAS TURBINE ENGINE COMPONENTS USING ADDITIVE MANUFACTURING TECHNIQUES - In accordance with an exemplary embodiment, a method for repairing a damaged metallic component using additive manufacturing techniques includes separating a damaged portion of the damaged metallic component from an undamaged portion of the damaged metallic component, measuring the undamaged portion to determine the dimensions of the removed damaged portion, fabricating a replacement portion using additive manufacturing techniques in accordance with the determined dimensions of the removed damaged portion, and joining the replacement portion with the undamaged portion of the damaged metallic component to form a repaired metallic component. | 09-18-2014 |
20140271322 | METHODS FOR FORMING DISPERSION-STRENGTHENED ALUMINUM ALLOYS - In accordance with an exemplary embodiment, a method of forming a dispersion-strengthened aluminum alloy metal includes the steps of providing a dispersion-strengthened aluminum alloy composition in a powdered form, directing a low energy density laser beam at a portion of the powdered alloy composition, and withdrawing the laser beam from the portion of the powdered alloy composition. Subsequent to withdrawal of the laser beam, the portion of the powdered alloy composition cools at a rate greater than or equal to about 10 | 09-18-2014 |
20140360698 | UNITARY HEAT EXCHANGERS HAVING INTEGRALLY-FORMED COMPLIANT HEAT EXCHANGER TUBES AND HEAT EXCHANGE SYSTEMS INCLUDING THE SAME - Unitary heat exchangers having integrally-formed compliant heat exchanger tubes and heat exchange systems including the same are provided. The unitary heat exchanger comprises an inlet plenum and an outlet plenum and a plurality of integrally-formed compliant heat exchanger tubes. The plurality of integrally-formed compliant heat exchanger tubes extend between and are integral with the inlet and outlet plenums to define a heat exchanger first flow passage. Each integrally-formed compliant heat exchanger tube comprises a tubular member and a plurality of integral heat transfer fins extend radially outwardly from at least one portion of the tubular member. The tubular member has a proximal tube end and a distal tube end and comprises a tubular wall having an outer wall surface and an inner wall surface. | 12-11-2014 |
20150047935 | VIBRATION ISOLATOR ASSEMBLIES AND METHODS FOR THE MANUFACTURE THEREOF - A vibration isolator assembly includes a bellows component, a piston component, a shaft component, and a housing component, wherein at least one of the bellows component, the piston component, the shaft component, and the housing component is formed using additive manufacturing techniques. | 02-19-2015 |
20150052872 | THERMAL ISOLATING SERVICE TUBES AND ASSEMBLIES THEREOF FOR GAS TURBINE ENGINES - Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member. A spacing volume is defined between at least the inner tubular member and an adjacent outer tubular member. The thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both. | 02-26-2015 |