Patent application number | Description | Published |
20080250641 | System for forming a gas cooled airfoil for use in a turbine engine - A turbine airfoil system for forming a turbine airfoil that is usable in a turbine engine. The airfoil may be formed from a porous material shaped into an outer airfoil shape. The porous material may include an inner central spar capable of supporting the turbine airfoil an outer porous region and an outer coating. The porous material facilitates efficient cooling of the turbine airfoil. | 10-16-2008 |
20080251165 | Heat treatment system for a composite turbine engine component - A heat treatment process for a component of a turbine engine formed from multiple materials, such as steel and nickel. The heat treatment process includes two stages: a first stage for austinitizing the steel and solutioning the nickel, and a second stage for ageing and tempering the materials. The heat treatment process may include heating a component formed from a steel portion and a nickel portion such that the steel portion austinitizes and the nickel portion undergoes solutioning, cooling the component to prevent the excessive formation of gamma prime ({grave over (γ)}), and subjecting the component to a temper heat treatment during which martensite tempering occurs. | 10-16-2008 |
20080253890 | Co-forged nickel-steel rotor component for steam and gas turbine engines - A method of forming a rotor for a turbine engine such that the rotor is formed of two materials including: an inner disk formed from a first material, such as steel, and an outer ring formed from a second material, such as a nickel alloy, having a larger thermal expansion coefficient than the first material forming the inner disk. The ring may include an inner aperture having a conical shape, and the disk may have an outer surface with a conical shape and a diameter with a portion that is larger than a portion of the ring. The ring may be heated such that the aperture expands to a size greater than the largest diameter of the inner disk. The ring may be positioned over the disk and allowed to cool to allow the ring to be attached to the disk. The ring and disk may then be co-forged. | 10-16-2008 |
20080253894 | Co-forged steel rotor component for steam and gas turbine engines - A method of forming a rotor for a turbine engine such that the rotor is formed of two materials including: an outer ring formed from a first steel material, and a disk formed from a second material, such as a low alloy steel, having a larger thermal expansion coefficient than the first material forming the inner disk. The ring may include an inner aperture having a conical shape, and the disk may have an outer surface with a conical shape and a diameter with a portion that is larger than a portion of the ring. The ring may be heated such that the aperture expands to a size greater than the largest diameter of the inner disk. The ring may be positioned over the disk and allowed to cool to allow the ring to be attached to the disk. The ring and disk may then be co-forged. | 10-16-2008 |
20080253923 | Superalloy forming highly adherent chromia surface layer - A nickel-based superalloy that forms a chromia scale in an oxidizing environment is disclosed. The alloy provides good oxidation resistance at temperatures below 900° C. in a dry or moist atmosphere. The superalloy is suited for components of gas or steam turbine engines including blades and vanes. | 10-16-2008 |
20080254276 | System for applying a continuous surface layer on porous substructures of turbine airfoils - A system for forming a surface coating on an outer surface of a foam for use with cooling system of turbine engines. The system may include removing filler from the outer surface of the foam to expose a porous structure of the foam, whereby portions of the porous structure extend outwardly from a newly formed outer surface of the filler. A surface layer may be applied to the outer surface of the filler and exposed portions of the porous structure, whereby the surface layer is attached to the porous structure at least in part due to mechanical interaction with the portions of the porous structure extending outwardly from the newly formed outer surface of the filler. The filler material may then be removed from the porous structure. | 10-16-2008 |
20080260571 | Oxidation resistant superalloy - A nickel-based superalloy that forms a chromia scale in an oxidizing environment is disclosed. The alloy provides good oxidation resistance at temperatures below 900° C. in a dry or moist atmosphere. The superalloy is well-suited for components of gas or steam turbine engines including blades and vanes. | 10-23-2008 |
20080260572 | Corrosion and oxidation resistant directionally solidified superalloy - A nickel-based superalloy having a good balance between corrosion and oxidation resistance. The alloy provides good mechanical properties. The superalloy is suited for directional solidification casting but can also be used for conventional or single crystal casting techniques. The superalloy is well suited for the hot section components such as blades, vanes and ring segments for gas turbine engines. The superalloys can be used with various thermal barrier coatings | 10-23-2008 |
20080298975 | Turbine airfoils with near surface cooling passages and method of making same - The present invention provides near-surface cooled airfoils that can be made with near-surface cooling passages that are completely free of any leachable or otherwise sacrificial material in the recessed portion of the outer surface of the core. The turbine airfoil comprises a metallic core or substrate having an outer surface and one or a plurality of recessed portions of the outer surface; an intermediate metallic skin or foil having a back surface and a top surface, the back surface of the intermediate skin being bonded to the outer surface of the core such that the recessed portion(s) is sufficiently enclosed so as to form at least one or more near-surface cooling passages or pathways; and at least one or more metallic coatings of a high temperature-resistant metallic material deposited on a top surface of the intermediate skin. | 12-04-2008 |
20090041615 | Corrosion Resistant Alloy Compositions with Enhanced Castability and Mechanical Properties - Disclosed are novel nickel-base alloy compositions that may be cast as a single crystal or directionally solidified alloy consisting essentially of, by weight: 8-12% Cr, 10-14% Co, 0.3-0.9% Mo, 3-7% W, 2-8% Ta, 2.0-5.5% Al, 1.5-5.0% Ti, up to 2% Nb, less than 0.1% B, less than 0.1% Zr, 0.05-0.15% C, less than 0.5% Hf, 2-4% Re, 0.05-0.2% Si, up to 0.015% S, up to 0.1% La, up to 0.1% Y, up to 0.1% Ce, up to 0.1% Nd, up to 0.1% Dy, up to 0.1% Pr, up to 0.1% Gd, balance is Ni, and wherein (La+Y+Ce+Nd+Dy+Pr+Gd) is 0.001-0.1%. The compositions for the nickel-base superalloy have a balance between oxidation resistance, corrosion resistance, castability, and mechanical properties, such as creep resistance and thermo-mechanical fatigue resistance. | 02-12-2009 |
20090075101 | Combustion Turbine Component Having Rare Earth CoNiCrAl Coating and Associated Methods - A combustion turbine component ( | 03-19-2009 |
20090075110 | Combustion Turbine Component Having Rare Earth NiCoCrAl Coating and Associated Methods - A combustion turbine component ( | 03-19-2009 |
20090075111 | Combustion Turbine Component Having Rare Earth NiCrAl Coating and Associated Methods - A combustion turbine component ( | 03-19-2009 |
20090075112 | Combustion Turbine Component Having Rare Earth FeCrAl Coating and Associated Methods - A combustion turbine component ( | 03-19-2009 |
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 |
20090196761 | METAL INJECTION JOINING - A method of joining a first part together with a second part is disclosed. The method may comprise providing a first part having a first joining portion including a first channel and a second part having a second joining portion including a second channel. The method may further comprise positioning the first part adjacent to the second part such that the first channel and second channel align with one another to define a cavity. The method may still further comprise preparing a mixture comprising at least one of a metal powder and a polymer binder, placing the mixture into the cavity so as to form a preform and solidifying the preform forming a metal element in the cavity. The metal element joins the first part together with the second part | 08-06-2009 |
20090235525 | Method of Producing a Turbine Component with Multiple Interconnected Layers of Cooling Channels - A method for making a gas turbine component ( | 09-24-2009 |
20090324841 | METHOD OF RESTORING NEAR-WALL COOLED TURBINE COMPONENTS - A method is provided for restoring a near-wall channeled gas turbine engine component ( | 12-31-2009 |
20100028131 | Component for a Turbine Engine - A component for use in a turbine engine including a first member and a second member associated with the first member. The second member includes a plurality of connecting elements extending therefrom. The connecting elements include securing portions at ends thereof that are received in corresponding cavities formed in the first member to attach the second member to the first member. The connecting elements are constructed to space apart a first surface of the second member from a first surface of the first member such that at least one cooling passage is formed between adjacent connecting elements and the first surface of the second member and the first surface of the first member. | 02-04-2010 |
20100028163 | Injection Molded Component - An intermediate component includes a first wall member, a leachable material layer, and a precursor wall member. The first wall member has an outer surface and first connecting structure. The leachable material layer is provided on the first wall member outer surface. The precursor wall member is formed adjacent to the leachable material layer from a metal powder mixed with a binder material, and includes second connecting structure. | 02-04-2010 |
20100043597 | METHOD OF MAKING RARE-EARTH STRENGTHENED COMPONENTS - A method of manufacturing a metallic component includes atomizing, in an inert atmosphere, a metallic liquid having at least one rare-earth element and at least one non rare-earth element to form a metallic powder. A series of heat treating steps are performed on the metallic powder. A first heat treating step is performed in an oxidizing atmosphere, and a second heat treating step is performed in an inert atmosphere. A third heat treating step is performed in a reducing atmosphere to form a metallic power having an increased proportion of rare-earth oxides compared to non rare-earth oxides. The metallic component is formed from the metallic powder having the increased proportion of rare-earth oxides compared to non rare-earth oxides. | 02-25-2010 |
20100054933 | STATIONARY TURBINE COMPONENT WITH LAMINATED SKIN - A stationary turbine engine component, such as a turbine vane, includes a internal spar and an external skin. The internal spar is made of a plurality of spar laminates, and the external skin is made of a plurality of skin laminates. The plurality of skin laminates interlockingly engage the plurality of spar laminates such that the external skin is located and held in place. This arrangement allows alternative high temperature materials to be used on turbine engine components in areas where their properties are needed without having to make the entire component out of such material. Thus, the manufacturing difficulties associated with making an entire component of such a material and the attendant high costs are avoided. The skin laminates can be made of advanced generation single crystal superalloys, intermetallics and refractory alloys. | 03-04-2010 |
20100061875 | Combustion Turbine Component Having Rare-Earth Elements and Associated Methods - A method of making a combustion turbine component includes forming a nanosized powder including a plurality of metals and at least one rare-earth element and agglomerating the nanosized powder to form a microsized powder including a plurality of metals and at least one rare-earth element. The microsized powder is processed to form a cohesive metallic mass and a primary aging heat treating is performed on the cohesive metallic mass. A solution heat treating may be performed on the cohesive metallic mass prior to the primary aging heat treating. A secondary aging treating may be performed on the cohesive metallic mass after the primary aging treating. | 03-11-2010 |
20100075111 | Structure and Method for Forming Detailed Channels for Thin Walled Components Using Thermal Spraying - A coated substrate with a subsurface cooling channel having no corner disposed proximate a seam between the substrate and the coating. A method for forming such a structure, including forming a groove in a surface of a substrate, forming a preform having a cooperating portion and a protruding portion, inserting the cooperating portion of the preform into the groove, leaving the protruding portion of the preform protruding beyond the surface of the substrate, applying a layer of a coating material to the surface of the substrate and the protruding portion of the perform, and removing the preform, thereby creating a cooling channel. | 03-25-2010 |
20100278680 | Combustion Turbine Component Having Rare-Earth Strengthened Alloy and Associated Methods - A method of making a combustion turbine component includes forming a metallic powder including at least one metal and at least one rare-earth element and processing the metallic powder including at least one metal and at least one rare-earth element to form a cohesive metallic mass. A primary aging heat treatment may be performed on the cohesive metallic mass. A homogenization heat treatment may be performed on the cohesive metallic mass prior to the primary aging heat treating. Furthermore, a secondary aging heat treatment may be performed on the cohesive metallic mass after the primary aging heat treating. | 11-04-2010 |
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 |