Patent application number | Description | Published |
20090183850 | Method of Making a Combustion Turbine Component from Metallic Combustion Turbine Subcomponent Greenbodies - A method of making a combustion turbine component includes assembling a plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly and sintering the metallic greenbody assembly to thereby form the combustion turbine component. Each of the plurality of metallic combustion turbine subcomponent greenbodies may be formed by direct metal fabrication (DMF). In addition, each of plurality of metallic combustion turbine subcomponent greenbodies may include an activatable binder and the activatable binder may be activated prior to sintering. | 07-23-2009 |
20100015394 | CERAMIC MATRIX COMPOSITE WALL WITH POST LAMINATE STITCHING - A stitching geometry and method for selective interlaminar reinforcement of a CMC wall ( | 01-21-2010 |
20100019412 | METHOD OF MANUFACTURING A THERMAL INSULATION ARTICLE - A method of manufacturing a thermal insulation article may include positioning, between opposing mold walls, a first layer comprising a ceramic matrix composite (CMC) material and a second layer comprising a plurality of tiles. The method may further include moving the opposing mold walls together to compress together the first and second layers, and curing the compressed together first and second layers to produce the thermal insulation article. | 01-28-2010 |
20100021643 | Method of Forming a Turbine Engine Component Having a Vapor Resistant Layer - A method of forming a turbine component that includes a ceramic matrix composite-ceramic insulation composite with a vapor resistant layer is disclosed. The method includes providing an inner tool and an outer tool, wherein the inner and outer tools define a mold for forming a turbine component. A vapor resistant layer can be applied to the inner tool, and a ceramic insulation layer can be applied over the vapor resistant layer in the mold. The vapor resistant layer and the ceramic insulation layer can be partially fired to form a bisque turbine component, and the outer tool can be removed. The inner tool can include a transitory material. A layer of ceramic matrix composite material can be applied to the outside of the bisque turbine component to form a component, and the component can be fired to form a turbine component. | 01-28-2010 |
20100021713 | STRUCTURE AND METHOD FOR PROTECTING A HYBRID CERAMIC STRUCTURE FROM MOISTURE ATTACK IN A HIGH TEMPERATURE ENVIRONMENT - A hybrid ceramic structure and a method for protecting the hybrid ceramic structure from moisture attack in a high temperature combustion environment are provided. The structure includes a ceramic matrix composite (CMC) substrate ( | 01-28-2010 |
20120000072 | Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components - A method of making a combustion turbine component includes forming a metallic body by direct metal fabrication (DMF) to have at least one surface portion defining a first plurality of surface cooling features each having a first dimension and at least one second surface cooling feature on at least one of the first plurality of surface cooling features and having a second dimension less than said first dimension and less than 200 μm. Forming the metallic body by DMF may include forming a plurality of metallic combustion turbine subcomponent greenbodies by DMF and assembling the plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly. The metallic greenbody assembly may be sintered to thereby form the metallic body. | 01-05-2012 |
20140294652 | Method of Making a Combustion Turbine Component from Metallic Combustion Turbine Subcomponent Greenbodies - A method of making a combustion turbine component includes assembling a plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly and sintering the metallic greenbody assembly to thereby form the combustion turbine component. Each of the plurality of metallic combustion turbine subcomponent greenbodies may be formed by direct metal fabrication (DMF). In addition, each of plurality of metallic combustion turbine subcomponent greenbodies may include an activatable binder and the activatable binder may be activated prior to sintering. | 10-02-2014 |
20140311163 | METHOD OF MANUFACTURING A TURBOMACHINE COMPONENT, AN AIRFOIL AND A GAS TURBINE ENGINE - One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 10-23-2014 |