Abstract: A folding wing for an aircraft comprises first and second inboard wing sections, and first and second outboard wing sections. The first and second inboard wing sections rotate about a centerline hinge, and a centerline spring applies force to the first and second inboard wing sections to rotate the first and second inboard wing sections from a stowed position to a deployed position. At least one of the first and second inboard wing sections translates along the axis of rotation of the first and second inboard wing sections as they move from the stowed to the deployed positions. The first and second outboard wing sections rotate between the stowed and the deployed positions about first and second outboard hinges.

Abstract: A folding wing for an aircraft comprises first and second inboard wing sections, and first and second outboard wing sections. The first and second inboard wing sections rotate about a centerline hinge, and a centerline spring applies force to the first and second inboard wing sections to rotate the first and second inboard wing sections from a stowed position to a deployed position. At least one of the first and second inboard wing sections translates along the axis of rotation of the first and second inboard wing sections as they move from the stowed to the deployed positions. The first and second outboard wing sections rotate between the stowed and the deployed positions about first and second outboard hinges.

Abstract: A gas turbine component article has an airfoil section and is formed of a nickel-base superalloy. An unmasked region of the airfoil section has a platinum aluminide protective coating, and a masked region of the airfoil section has an aluminide coating. The platinum aluminide preferably is deposited at a trailing edge of the airfoil section that is susceptible to low-cycle fatigue damage when a platinum aluminide coating is present.

Abstract: A thermal barrier coating (TBC) system and method for forming the TBC system on a component designed for use in a hostile thermal environment, such as superalloy turbine, combustor and augmentor components of a gas turbine engine. The TBC system exhibits improved spallation resistance as a result of having a bond coat formed to contain a dispersion of oxide particles in its outer surface region. A method for preferentially entrapping oxide particles in a bond coat entails depositing the oxide particles on the surface of the component prior to forming the bond coat, which may be a diffusion aluminide or an aluminized overlay coating. Deposition of the bond coat causes the oxide particles to become dispersed in the outer surface region of the bond coat. A particular feature of this invention is the ability to preferentially entrap oxides of elements that are not present in the bond coat or a substrate region of the component on which the bond coat is formed.

Abstract: A gas turbine component article has an airfoil section and is formed of a nickel-base superalloy. An unmasked region of the airfoil section has a platinum aluminide protective coating, and a masked region of the airfoil section has an aluminide coating. The platinum aluminide preferably is deposited at a trailing edge of the airfoil section that is susceptible to low-cycle fatigue damage when a platinum aluminide coating is present.

Abstract: A gas turbine component article has an airfoil section and is formed of a nickel-base superalloy. An unmasked region of the airfoil section has a platinum aluminide protective coating, and a masked region of the airfoil section has an aluminide coating. The platinum aluminide preferably is deposited at a trailing edge of the airfoil section that is susceptible to low-cycle fatigue damage when a platinum aluminide coating is present.

Abstract: An article comprising an airfoil surface is provided with a thermal insulating outer layer on at least one region, but not all, of the airfoil surface. The region is selected from the airfoil surface which has been observed to experience more strenuous environmental operating conditions during service operation than the airfoil surface outside of the region. In one form, the thermal insulating outer layer is applied to at least one region of each of a plurality of airfoil surfaces. Each airfoil surface is disposed about an axis of rotation with the region of each airfoil surface facing generally outwardly from the axis of rotation and from each other. The airfoil surfaces are rotated about the axis of rotation while a thermal insulating material contacts at least the regions.

Abstract: A computer-implemented system, method, and product associate words, phrases, or other characters (“words”) to be translated with previous translations of such words, if a previous translation exists. The words to be translated, and their identifying attributes (such as, for example, formatting information), are extracted from one or more source files. The previous translations, and their identifying attributes, are extracted from one or more target files. If a previous translation does not exist, the words to be translated, and their attributes, are copied to create a pseudo-previous translation, with attributes. Each word to be translated is associated with a corresponding previous translation based upon commonalities of their attributes. Such words may also be associated based upon their respective locations in their respective files. Each word to be translated, and its attributes, may be stored with a previous translation in a source-target pair record of a source-target pair database.

Abstract: A computer-implemented system, method, and product are provided to propagate an externally produced translation of a first occurrence of a word, phrase, or other group of characters to be translated (referred to herein as a “translatable source segment”) in a first source file to at least one occurrence of a corresponding target segment in one or more target files of a target project. The corresponding target segment corresponds with a second occurrence of the translatable source segment in any of the one or more source files. The source files may have the same file format, or two or more of the source files may have different file formats. Also, two or more source files may have character formats that are different from each other, and/or they may be written in different languages. In one implementation, the propagator propagates the externally produced translation to all corresponding target segments in the target project that correspond with the translatable source segment.

Abstract: A tip cap hole is loaded with a first composition comprising particles of a first alloy having a solidus temperature above the brazing temperature. The first composition is covered with a second composition comprising particles of a second alloy having a liquidus temperature below the brazing temperature. The second composition is heated to the brazing temperature to cause particles of the second alloy to melt to form a liquid of the second alloy which is carried into spaces between the particles of the first alloy by capillarity. The liquid of the second alloy is cooled to form a solid securely bonding the particles of the first alloy. By weight, the second alloy has no more than 1% B and from 3% to 11% Si. The first alloy has Cr and at least about 5% Al, at least about 0.5% Hf, no more than 0.5% Ti.

Abstract: An article having a design external aerodynamic shape includes a body with a body external surface and an outer portion external surface of an outer portion bonded with a part of but less than substantially all of the body surface. The external surfaces of the body and outer portion each define less than the design external aerodynamic shape. However, together they define such shape. The article is made by selecting the design external aerodynamic shape from an existing article having a first body and a first outer portion. A replacement outer portion is selected in an amount less than the first outer portion and bonded with a region less than substantially all of a replacement body external surface. The replacement body has a replacement body external surface and replacement body external shape different from the first body substantially by that amount. The replacement body is made with the replacement body external shape.

Abstract: A curved component such as a turbine airfoil, shroud, or combustor centerbody is prepared with a platinum or a platinum-aluminide protective coating over only a portion of the surface thereof. The coating may serve as an environmental coating, or as a bond coat of a thermal barrier coating system. The partial coverage is achieved by depositing platinum only over a portion of the surface of the component, typically including the concave portion in the case of an airfoil, optionally depositing an aluminum layer, and optionally interdiffusing the platinum and aluminum layers.

Abstract: A tip cap hole is loaded with a first composition comprising particles of a first alloy having a solidus temperature above the brazing temperature. The first composition is covered with a second composition comprising particles of a second alloy having a liquidus temperature below the brazing temperature. The second composition is heated to the brazing temperature to cause particles of the second alloy to melt to form a liquid of the second alloy which is carried into spaces between the particles of the first alloy by capillarity. The liquid of the second alloy is cooled to form a solid securely bonding the particles of the first alloy. By weight, the second alloy has no more than 1% B and from 3% to 11% Si. The first alloy has Cr and at least about 5% Al, at least about 0.5% Hf, no more than 0.5% Ti.

Abstract: An article comprising an airfoil surface is provided with a thermal insulating outer layer on at least one region, but not all, of the airfoil surface. The region is selected from the airfoil surface which has been observed to experience more strenuous environmental operating conditions during service operation than the airfoil surface outside of the region. In one form, the thermal insulating outer layer is applied to at least one region of each of a plurality of airfoil surfaces. Each airfoil surface is disposed about an axis of rotation with the region of each airfoil surface facing generally outwardly from the axis of rotation and from each other. The airfoil surfaces are rotated about the axis of rotation while a thermal insulating material contacts at least the regions.

Abstract: An airfoil core die includes a tab for forming a continuous and smooth contour and extension of a first trailing edge slot recessed wall to a bottom of the airfoil. The contour is formed on each airfoil core at injection and is maintained through to finish casting of the airfoil.

Abstract: A fan case liner for a gas turbine engine includes a foreign body impact resistant area and a sound suppression area. The foreign body impact resistant area includes a face sheet of a high impact resistant material which substantially resists denting when struck by a foreign body. A first honeycombed layer of aluminum or an aluminum alloy is disposed over and attached to the face sheet. The first layer has a selected compressive strength to distribute loading forces caused by the impact of a foreign body and to resist plastic deformation. The hexagonally shaped voids in the honeycombed structure of the first layer are filled with a microballoon/resin filler material to further improve resistance to damage or denting. At least one second honeycombed layer of a aluminum or an aluminum alloy is disposed over and attached to the first honeycombed layer.