Abstract: A dome assembly for a gas turbine engine combustor includes an annular combustor dome with a substantially annular flat dome plate and at least one circular opening in the dome plate. A seal plate flange with a flat aft facing surface has a central ring circumscribed about a centerline axis and extends aftwardly from the seal plate flange. The central ring is disposed through the circular opening in the dome plate and the central ring includes a central bore coaxially aligned with the circular opening. A baffle has a cylindrical tubular mounting portion extending upstream through the central bore and is fixedly joined to the seal plate and a flare portion extending aft from the seal plate flange. A carburetor including an air swirler having an annular exit cone is joined to the baffle with the exit cone disposed within the cylindrical tubular mounting portion of the baffle. An aft end of the central ring is joined to the dome plate by a swage joint.

Abstract: A compressor stator vane includes pressure and suction sides extending chordally between leading and trailing edges, and longitudinally between a root and a tip. The vane narrows in chord to a waist between the root and tip. The vane may also be bowed at its trailing edge in cooperation with the narrow waist.

Abstract: Sensor selection status monitoring and maintenance logic for generating messages relating to intermittent and “in-range” faults are described. In one embodiment, a transition count is generated indicating a number of times the selection status number changes during a flight. A time duration table is generated indicating an amount of time a selection status number is recorded in each of its possible states during the flight. The maintenance logic utilizes outputs from the monitoring logic to generate maintenance messages.

Abstract: A clevis pin joins a thrust link to a support in an aircraft engine thrust mount. The pin includes a shank having a semicircular section for carrying in shear thrust load between the link and support. A head is disposed at one end of the shank, and a tip is disposed at an opposite end of the shank. In a preferred embodiment, a pair of the pins are nested together for collectively effecting a circular cross sectional area for carrying the thrust load in shear therethrough.

Abstract: A process for reclaiming aluminum alloy donor from a vapor phase deposition process used to form a diffusion aluminide coating on a component, such as the high-temperature superalloy components of gas turbine engines. The process generally entails recycling a particulate aluminum alloy donor material that, as a result of having been used as the donor material for depositing a diffusion aluminide coating on an article by vapor phase deposition, particles of the donor material comprise an aluminum alloy core encased in an aluminum-depleted shell. The process generally entails tumbling the donor material in a manner that removes the aluminum-depleted shell, followed by sieving the donor material to remove shell fragments and undersized particles.

Abstract: A gas turbine engine hot section component having a ceramic thermal barrier coating is repaired by removing the ceramic thermal barrier coating, removing oxidation products and corrosion products from the metallic bond coating beneath the ceramic thermal barrier coating, applying a noble metal to the component, diffusing the noble metal into the component substrate, and aluminiding the component to provide an outermost noble metal-Al layer.

Abstract: A coating for use on a superalloy substrate comprising a diffusion barrier as an intermediate layer overlying the substrate and underlying a protective coating having a high aluminum content. The diffusion barrier layer is characterized by having low solubility for aluminum from either the substrate or the protective coating. Further, the diffusion barrier layer has low interdiffusivity for elements from the substrate and the coating, a minimal impact on the mechanical properties of the article which is coated, a minimal thermal expansion mismatch with both the substrate and the high aluminum content protective coating, and can be applied readily using existing coating application techniques. The diffusion barrier is preferably a single phase alloy or intermetallic compound.

Abstract: A fluid distribution system for transporting pressurized fluid. The system includes a plate having a first face and a slot extending along the face between opposite first and second ends of the slot. In addition, the system includes a body having a surface sealingly engaging the first face of the plate and overlying the slot so that a portion of the surface and the slot at least partially define a passage for transporting pressurized fluid between the first and second ends of the slot. A method of making the system is also disclosed.

Abstract: A tumble medium for surface treatment of an article having a first radiographic signature comprises material having a second radiographic signature different from the first radiographic signature sufficient to enable radiographic detection of the material as distinct from the article. The tumble medium is used in a method for treatment of a surface of an article including there through openings communicating with an interior of the article. After tumbling, the article is inspected by radiography to detect any tumble medium within the interior of the article.

Abstract: A combustor dome module includes a mixer tube having a hollow heat shield sealingly joined around the outlet end thereof. The modules may then be assembled in an array for defining the combustor dome, with each module being individually removable therefrom.

Abstract: A compressor airfoil includes pressure and suction sides extending from root to tip and between leading and trailing edges. Transverse sections have respective chords and camber lines. Centers of gravity of the sections are aligned along a bowed stacking axis either tangentially, axially, or both, for improving performance.

Abstract: A process for depositing a mullite coating on a silicon-based material, such as those used to form articles exposed to high temperatures and including the hostile thermal environment of a gas turbine engine. The process is generally to thermally spray a mullite powder to form a mullite layer on a substrate, in which the thermal spraying process is performed so that the mullite powder absorbs a sufficient low level of energy from the thermal source to prevent evaporation of silica from the mullite powder. Processing includes deposition parameter adjustments or annealing to maintain or reestablish phase equilibrium in the mullite layer, so that through-thickness cracks in the mullite layer are avoided.

Abstract: A seating spring is provided for a gas turbine engine compressor stator having a casing with a circumferential casing slot for mounting a plurality of vane sectors at outer bands thereof. The seating spring has at least one reaction tab configured to abut the casing at one side of the casing slot and a spring arm connected to the reaction tab and configured to abut a respective one of the outer bands to bias the outer band against the casing at a second side of the casing slot. A retention arm is connected to the reaction tab and engages the casing so as to be prevented from moving radially outward. The spring arm is thereby retained in contact with the outer band.

Abstract: A heating apparatus and method for pre-weld heat treating, welding and post-weld heat treating a superalloy article in a single enclosure while avoiding oxidation of the article. The enclosure is preferably equipped with a one-way valve that permits the escape of gases, but otherwise seals the enclosure to prevent the ingress of air during welding and heat treatment as a result of thermal gradients induced when the article is inductively heated. To provide access to the article and a device used to weld the article, the enclosure is equipped with gloves by which the welding device and the article can be manipulated while a nonreactive atmosphere is fully maintained within the enclosure and the article is inductively heating.

Abstract: An article and method for laser shock peening the article to form pairs of longitudinally spaced apart first and second laser shock peened spots that are on opposite sides of the article, simultaneously laser shock peened, and transversely offset from each other.

Abstract: A fuel injection system for a gas turbine engine combustor, wherein the combustor includes a dome inlet module having a plurality of flow passages formed therein and at least one cavity formed in a liner downstream of said dome inlet module. The fuel injection system includes a fuel supply and a plurality of fuel injector bars positioned circumferentially around and interfacing with the inlet dome module. The fuel injector bars are in flow communication with the fuel supply, with each of the fuel injector bars further including a body portion having an upstream end a downstream end, and a pair of sides. A plurality of injectors formed in the body portion and in flow communication with the fuel supply, whereby fuel is provided to the dome inlet module flow passages and/or the cavity through the fuel injector bars.

Abstract: A gas turbine component includes a platform having a first coating on at least a portion thereof, where the first coating is a diffusion aluminide coating. An airfoil extends from the platform and has an external surface and an internal surface defining cooling passages therethrough. The airfoil has an airfoil shape made of a substrate alloy, a second coating on the external surface of the airfoil shape, the second coating comprising an overlay coating, and a third coating on the internal surface of the airfoil shape, the third coating comprising a diffusion aluminide coating different in composition from the second coating.

Abstract: A thrust mount includes a platform mountable to an aircraft pylon, and includes end clevises and a center clevis therebetween. An equalizer lever includes opposite ends, and a center therebetween pivotally joined to the center clevis. Thrust links are pivotally joined to the lever ends. And, a pair of elastomeric snubbers are disposed adjacent respective ends of the lever inside the end clevises in frictional abutment therebetween.

Abstract: An environmental overlay coating for articles used in hostile thermal environments, such as turbine, combustor and augmentor components of a gas turbine engine. The overlay coating is predominantly beta-phase NiAl with limited alloying additions of zirconium and chromium. The overlay coating is useful as an environmental coating and as a bond coat that improves the spallation resistance of a thermal barrier coating (TBC) system.

Abstract: A preferred embodiment of said present invention is a gas turbine engine blade root shim for use between a composite blade root and a wall of a slot for receiving the root in a rotor of the engine. An exemplary embodiment of the shim includes a longitudinally extending base having distal first and second transversely spaced apart ends, first and second longitudinally extending legs acutely angled inwardly towards the base from the first and second ends, and first and second low coefficient of friction coatings on first and second outwardly facing surfaces of the first and second legs, respectively. Among coatings suitable for use in the present invention are polytetrafluoroethylene powder dispersed in a resin binder and other coatings which include polytetrafluoroethylene.