Abstract: A thermally protective coating (21), such as may be used over a nickel-based superalloy substrate (24). The protective coating (21) includes a CoNiCrAlY or a NiCoCrAlY material and addition of given amounts of one or more secondary elements. The secondary element(s) facilitate and/or join in one or more precipitation mechanisms (??, B2) that retain an aluminum reservoir in the protective coating (21), reducing aluminum diffusion into the substrate (24). This aluminum reservoir maintains a protective alumina scale (38) on the coating (21), thus improving coating life and allowing higher operating temperatures.

Abstract: A turbine airfoil seal system of a turbine engine having a seal base with a plurality of seal strips extending therefrom for sealing gaps between rotational airfoils and adjacent stationary components. The seal strips may overlap each other and may be generally aligned with each other. The seal strips may flex during operation to further reduce the gap between the rotational airfoils and adjacent stationary components.

Abstract: A disc seal assembly for use in a turbine engine. The disc seal assembly includes a plurality of outwardly extending sealing flange members that define a plurality of fluid pockets. The sealing flange members define a labyrinth flow path therebetween to limit leakage between a hot gas path and a disc cavity in the turbine engine.

Abstract: A ceramic matrix composite (CMC) anchor (20, 100) joining a metal substrate (40) and a ceramic thermal barrier (38). The CMC anchor extends into and interlocks with the ceramic barrier, and extends into and interlocks with the metal substrate. The CMC anchor may be a honeycomb (20) or other extending-into-and-interlocking geometry. A CMC honeycomb may be formed with first (22) and second (24) arrays of cells (26) with open distal ends (28) on respective opposite sides of a sheet (30). The cells may have walls (32) with transverse passages (36). A metal (40) may be deposited into the cells and passages on one side of the sheet, forming a metal substrate locked into the honeycomb. A ceramic insulation material (38) may be deposited into the cells and passages on the opposite side of the sheet, forming a layer of ceramic insulation locked into the honeycomb.

Abstract: A sealing arrangement for use in a turbine engine having ceramic components. The sealing arrangement is retained in a seal gap formed between adjacent segments and is compliant to accommodate variations in the size of the seal gap as the adjacent segments move relative to one another.

Abstract: 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.

Abstract: A multiple piece turbine airfoil having an outer shell with an airfoil tip that is attached to a root with an internal structural spar is disclosed. The root may be formed from first and second sections that include an internal cavity configured to receive and secure the one or more components forming the generally elongated airfoil. The internal structural spar may be attached to an airfoil tip and place the generally elongated airfoil in compression. The configuration enables each component to be formed from different materials to reduce the cost of the materials and to optimize the choice of material for each component.

Abstract: A hybrid ceramic matrix composite structure and method for fabricating such an structure are provided. A ceramic matrix composite substrate 12 includes a plurality of layers of ceramic fibers. A plurality of spaced apart imprints 22 is disposed in at least one of the plurality of layers. An outer surface of a subsequent layer disposed over the layer with the imprints to influence a texture of the outer surface of the substrate by defining a plurality of indent regions 32 on the outer surface of the substrate. A ceramic coating 14 is deposited on the surface of the substrate. The plurality of indent regions 32 constitutes a bond-enhancing arrangement between the surface of the substrate and a corresponding boundary of the coating.

Abstract: A fuel nozzle for delivery of fuel to a gas turbine engine. The fuel nozzle includes an outer nozzle wall and a center body located centrally within the nozzle wall. A gap is defined between an inner wall surface of the nozzle wall and an outer body surface of the center body for providing fuel flow in a longitudinal direction from an inlet end to an outlet end of the fuel nozzle. A turbulating feature is defined on at least one of the central body and the inner wall for causing at least a portion of the fuel flow in the gap to flow transverse to the longitudinal direction. The gap is effective to provide a substantially uniform temperature distribution along the nozzle wall in the circumferential direction.

Abstract: A gas turbine combustor for producing hot gas by burning a fuel in compressed air comprising a combustor central axis and multiple main swirlers with respective swirler axes disposed about and parallel to the combustor central axis, each main swirler delivering an air fuel mixture flowing through it and about its swirler axis, wherein each swirler imparts rotation to the air fuel mixture flowing through it in a direction opposite that of adjacent swirlers. This combustor configuration reduces shear where the outer edges of adjacent flows meet, allowing for greater tuning of the combustion chamber and reduced NOx and CO emissions.

Abstract: A pilot burner (150, 350) for a gas turbine engine delivers an inner non-swirling fuel-oxidant mixture surrounded by an outer swirling fuel-oxidant mixture, thereby providing enhanced mixing with no recirculation zone. At least one fluid-restricting inlet port (166, 366) provides an oxidant to an inner mixing passage (160, 360). The inner mixing passage (160, 360) includes a plurality of fuel outlets (168). An outer annular mixing passage (180) receives oxidant from an upstream port (181) surrounding the inner mixing passage and includes at least one swirler element (186, 386) and fuel outlets (188).

Abstract: A hybrid ceramic matrix composite (CMC) structure 10 and method for fabricating such an structure are provided. A CMC substrate 12 includes layers 16, 18, 20 of ceramic fibers. Fugitive objects 22 are disposed on at least one of the plurality of layers prior to laying a subsequent layer of ceramic fibers. An outer surface of the subsequent layer influences a shape of the outer surface of the substrate by defining protuberances 24 on the outer surface of the substrate where respective cavities 26 are formed beneath respective protuberances upon dissipation of the fugitives. A liquefied ceramic coating 34 is deposited on the outer surface of the ceramic substrate to fill the cavities. When the ceramic coating is cured to a solidified state, the cavities containing the solidified coating constitute an anchoring arrangement between the ceramic substrate and the ceramic coating.

Abstract: A method and system for monitoring the operating conditions of an electric generator. The system includes a triad sensor array formed within a predetermined section of a fiber optic conductor. The triad sensor array is formed of a group of sensors including a first sensor including a Bragg grating for producing a first signal representative of strain in a stator bar of the generator, a second sensor including a Bragg grating for producing a second signal representative of temperature in the stator bar, and a third sensor including a Bragg grating for producing a third signal representative of vibration amplitude in the stator bar.

Abstract: 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.

Abstract: A method and system for controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine. A liquid fuel is conveyed from a single stage fuel supply through a plurality of primary fuel supply lines to a first nozzle stage including a plurality of primary nozzles. A predetermined operating condition of the gas turbine is identified and a signal is produced in response to the identified operating condition. The signal effects actuation of valves located on secondary fuel supply lines extending from each of the primary fuel supply lines to supply fuel to respective secondary nozzles.

Abstract: A method of making a composite blade that is attachable to a rotating shaft using a conventional metal blade attachment. A blade is formed from a composite material with a blade root at one end thereof. A metallic member having an external shape conforming to a conventional metal blade root is shaped with an interior cavity having an opening for receipt of the blade root. Before the composite material is fully cured, a bladder is formed into or is inserted into an end of the blade root and inflated, thereby forcing the composite material into intimate contact with the interior cavity of the metallic member, thereby ensuring a fret-free interface upon final curing of the composite material. The interior cavity of the metallic member may be shaped or surfaced to improve the load carrying capability there between.

Abstract: The invention refers to a computer-implemented method and system for loading a loadware file on a CANopen device. The CANopen device comprises an electronic data sheet, which is extended to comprise a load object. After reading the load object with the load parameters, the respective loadware file is located, selected and accessed. Accessing the loadware file is done by applying the read load parameters.

Abstract: Protective insert plates (54, 56) installed on a working gas face (42) of a turbine vane platform (26) provide replaceable portions of a turbine shroud for improved maintenance. The plates act as tiles, and may be formed of ceramic materials for thermal protection. Two cages (58, 60) in the vane platform slidably receive the two insert plates (54, 56) from opposite circumferential sides (36, 38) of the platform. The plates slide into the cages up to the pressure and suction sides (32, 34) of the vane airfoil (22). The plates may have proximal edges (62, 64) shaped to fit the respective pressure and suction sides of the vane airfoil. A retainer plate 66 may be attached to a flange (72) on the cooled face (48) of each platform, and may contact each insert plate with a locking device (74, 76) to prevent sliding of the plate in the cage.

Abstract: A holding structure associated with a lifting device for supporting a removed turbine engine cover plate assembly. The holding structure includes an upper support member and a lower support member. The upper support member is formed with a plurality of service areas, where each service area is configured for servicing a cover plate assembly. Each service area includes a plurality of slots extending inwardly from a peripheral edge of the upper support member to receive and support components of the cover plate assembly during a disassembly and service operation.

Abstract: A circuit assembly (34) resistant to high-temperature and high g centrifugal force is disclosed. A printed circuit board (42) is first fabricated from alumina and has conductive traces of said circuit formed thereon by the use of a thick film gold paste. Active and passive components of the circuit assembly are attached to the printed circuit board by means of gold powder diffused under high temperature. Gold wire is used for bonding between the circuit traces and the active components in order to complete the circuit assembly (34). Also, a method for manufacturing a circuit assembly resistant to elevated temperature is disclosed.