Patent application number | Description | Published |
20090114797 | REFRACTORY METAL CORE COATINGS - A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating includes at least one oxide and a silicon containing material. In a second embodiment, the coating includes an oxide selected from the group of calcia, magnesia, alumina, zirconia, chromia, yttria, silica, hafnia, and mixtures thereof. In a third embodiment, the coating includes a nitride selected from the group of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure. | 05-07-2009 |
20090269208 | REPAIR METHOD AND REPAIRED ARTICLE - A method of repairing an article includes removing an undesirable section of the article, attaching a repair section to the article at a location from which the undesirable section has been removed, and mechanically working the repair section to achieve a reduction in a cross-sectional area of the repair section. | 10-29-2009 |
20110030456 | NON-DESTRUCTIVE INSPECTION METHOD FOR METALLIC ALLOYS - A non-destructive inspection method for detecting the presence of a contaminant that has alloyed with a metallic alloy of a part includes exposing the metallic alloy of the part to an extraction solution. The extraction solution extracts at least a portion of any of the contaminant that has alloyed with the metallic alloy. The extraction solution can then be analyzed to determine whether the solution includes any of the contaminant element, which indicates whether the part includes any of the contaminant element. | 02-10-2011 |
20110233378 | DIE INSERTS FOR DIE CASTING - An apparatus for casting material has a die for receiving a compressive force, the die having a shaped-opening for receiving a die insert. The die insert has an exterior shape that is adapted to cooperate with and be received in the opening such that compressive forces impinging upon the die are focused upon the die insert such that tensile forces within the die and impinging upon the die insert are minimized. | 09-29-2011 |
20120110848 | LOW AND EXTRA LOW SULFUR ALLOYS FOR REPAIR - A method for repairing, refurbishing, or replacing a turbine engine component or sub-component includes the steps of providing a turbine engine component or sub-component having a site to be repaired, refurbished, or replaced providing a repair or replacement material having a sulfur content, which sulfur content is less than 10 ppm, and applying the repair or replacement material to the site on the turbine engine component to effect the repair, the refurbishment, or the replacement. | 05-10-2012 |
20130047735 | BACKING RING FOR SENSOR ASSEMBLY - Disclosed is a sensor assembly including a port, which may support one or more headers, and a header affixed to the port by a weld joint. The header may support a sensor, such as a pressure sensor. A backing ring protects the assembly from damage that may be caused by welding. | 02-28-2013 |
20130195674 | ALUMINUM AIRFOIL - A method of making an aluminum airfoil includes brazing a first airfoil piece and a second airfoil piece together using a braze material that includes an element selected from magnesium and zinc, to form a braze joint between the first airfoil piece and the second airfoil piece. At least one of the first airfoil piece or the second airfoil piece has an aluminum alloy composition that includes greater than 0.8% by weight of zinc. | 08-01-2013 |
20130343901 | REPAIR METHOD AND REPAIRED ARTICLE - A repaired article includes a body extending between a first side and a second side. The body has a repair section with an associated thickness between the first side and the second side. The repair section includes regions of plastic deformation distributed through the thickness. A gas turbine engine including the body is also disclosed. | 12-26-2013 |
20140090753 | METHOD FOR SOLUTION HEAT TREATED ALLOY COMPONENTS - A method for adjusting properties of components made of an alloy includes providing historical data for one or more properties of components made of an alloy and produced at different times. The components are solution heat treated at a pre-established solution heat treatment condition. A trending change in the one or more properties is then identified and test specimens made of the alloy are provided. The test specimens are divided into a plurality of groups and solution heat treated at different conditions. The test specimens are then mechanically tested to provide empirical data. The empirical data is compared to performance criteria and a solution heat treatment condition is identified over which the empirical data meets the performance criteria. The pre-established solution heat treatment condition is then adjusted for future ones of the plurality of components according to the identified solution heat treatment condition. | 04-03-2014 |
20140140859 | UBER-COOLED MULTI-ALLOY INTEGRALLY BLADED ROTOR - Uber-cooled multi-alloy integrally bladed rotors (IBR) are made having blades with internal cooling passages with a cavity in the root portion attached to a disk having a protrusion on the periphery of the disk. The blades are put on the protrusion and the blade and disk are forced together, followed by locally heating the blade cavity/disk protrusion to a temperature between the blade and disk material softening temperatures, causing the protrusion to deform against the blade cavity, and holding them in place until bonding occurs. Subsequent to bonding the portion of the blade that defines the cavity is removed. | 05-22-2014 |
20140169981 | UBER-COOLED TURBINE SECTION COMPONENT MADE BY ADDITIVE MANUFACTURING - A gas turbine airfoil having internal cooling passages is formed by additive manufacturing. Layers of superalloy powder are fused by an energy beam using a two-dimensional pattern providing unmelted areas forming passageways therein. Layers of the powder are added and fused using sufficient two-dimensional patterns to form the entire airfoil with the desired pattern of internal cooling passages. After completion of the formation of the airfoil, it may be hot isostatic pressed, directionally recrystallized, bond coated, and covered with a thermal barrier layer. | 06-19-2014 |
20140241897 | ALUMINUM BRAZING OF HOLLOW TITANIUM FAN BLADES - A fan blade includes first and second titanium portions that are secured to one another with an aluminum alloy braze. A method of manufacturing a fan blade includes providing first and second titanium portions, applying an aluminum alloy braze to at least one of the first and second titanium portions, and heating the fan blade to melt the aluminum alloy braze and join the first and second portions to one another to provide a fan blade with an airfoil exterior contour. | 08-28-2014 |