Abstract: A coating process and system for an article having a substrate formed of a metal alloy that is prone to the formation of a secondary reaction zone (SRZ). The coating system includes an aluminum-containing overlay coating and a stabilizing layer between the overlay coating and the substrate. The overlay coating contains aluminum in an amount greater by atomic percent than the metal alloy of the substrate, such that there is a tendency for aluminum to diffuse from the overlay coating into the substrate. The stabilizing layer is predominantly or entirely formed of at least one platinum group metal (PGM), namely, platinum, rhodium, iridium, and/or palladium. The stabilizing layer is sufficient to inhibit diffusion of aluminum from the overlay coating into the substrate so that the substrate remains essentially free of an SRZ that would be deleterious to the mechanical properties of the alloy.

Abstract: An axial flow positive displacement engine has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet through first, second, and third sections of a core assembly in serial downstream flow relationship. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes respectively. The inner and outer helical blades extend radially outwardly and inwardly respectively and have first, second, and third twist slopes in the first, second, and third sections respectively. The first twist slopes are less than the second twist slopes and the third twist slopes are less than the second twist slopes. A combustion section extends axially downstream from the second section through at least a portion of the third section.

Abstract: A random access recording method and system for recording and playing back of avionics data, includes: storing data received from a plurality of data channels in respective data files. The method and system also includes storing timeline pointers that signify when the data from the respective plurality of data files was stored. The method and system further includes determining a particular position of a timeline icon provided on a graphical user interface (GUI) display, the timeline icon signifying a point in time that a user desires to review avionics data stored. The method and system still further includes playing back data stored based on the particular position of the timeline icon with respect to corresponding values of the timeline pointers stored.

Abstract: A thermal barrier coating (TBC) for a component intended for use in a hostile environment, such as a component of a gas turbine engine. The TBC exhibits improved impact and erosion resistance as a result of being a composite material consisting essentially of particles of a ceramic reinforcement material dispersed in a ceramic matrix material. The ceramic reinforcement material has a yield strength greater than the ceramic matrix material at about 1100° C., and the particles of the ceramic reinforcement material have an average maximum dimension of greater than five micrometers.

Abstract: A composite blading member includes an airfoil and a base of composite material layers and a platform of composite material layers interfused with the airfoil and base. The platform comprises a platform shelf and a plurality of spaced-apart platform supports integral with the platform shelf and interfused with surfaces of the base. Such blading member was made by providing a partially cured airfoil-base preform and a platform preform, including an airfoil shaped opening therethrough and preforms of the platform supports. The airfoil-base preform was inserted through the airfoil shaped opening whereby cooperating surfaces of the platform preform and airfoil-base preform were in juxtaposition. The preforms were heated to partially cure them together. Then they were interfused with a binder compatible with material of the preforms under conditions to substantially fully cure the structures.

Abstract: A ceramic material suitable for use as a coating, such as a porous thermal barrier coating (TBC) on a component intended for use in a hostile thermal environments. The coating material consists essentially of zirconia stabilized by at least one rare-earth metal oxide and further alloyed to contain a limited amount of titania. Rare-earth metal oxides of particular interest are lanthana, ceria, neodymia, europia, gadolinia, erbia, dysprosia, and ytterbia, individually or in combination. Zirconia, the rare-earth metal oxide, and titania are present in the coating material in amounts to yield a predominantly tetragonal phase crystal structure. The amount of titania in the coating is tailored to allow higher levels of stabilizer while maintaining the tetragonal phase, i.e., avoiding the cubic (fluorite) phase.

Abstract: An exemplary thermal air exhaust system includes circumferentially extending exhaust passages to exhaust thermal control air from an annular region between an outer casing and a distribution manifold encircling an axially extending portion of the casing after the thermal control air has been sprayed on at least one thermal control ring attached to the outer casing and/or onto the outer casing by spray tubes with spray holes. Baffles attached to base panels of the distribution manifold and contoured to form the exhaust passages between the baffles and base panels. The exhaust passages having exhaust passage inlets formed by radially facing exhaust holes through the baffles and exhaust passage outlets formed by circumferentially facing exhaust passage outlets between the baffles and the base panels. Thermal control air is sprayed on at least one thermal control ring and/or onto the outer casing and then circumferentially exhausted through the exhaust passages.

Abstract: A computing network uses Time Division Multiplexing (TDM) to divide the time on a bus into a plurality of frames, each frame having a plurality of time slots. Each time slot is assigned no more than one of the plurality of devices within a collision domain, the assignments indicating the identity of the device permitted to transmit packets onto the network during the assigned time slot. A bus cadence unit simultaneously sends an epoch packet initiating the frame. The epoch packet contains a time slot assignment table containing the time slot assignments, the device identification, as well as a time slot offset and duration. Each device on the network is configured to measure a frame interval between repeating epoch packets. The measured frame interval is further processed in each receiving node to obtain a calibrated frame interval. The calibrated frame interval is used to accurately synchronize transmissions of data from the various devices onto the network.

Abstract: A vectorable nozzle includes convergent and divergent sections and a throat therebetween. Heightwise spaced apart upper and lower walls outwardly bound a nozzle flowpath and extend aftwardly through the convergent and divergent sections from the nozzle inlet to the nozzle outlet. The upper wall includes triangular left and right side convergent upper panels pivotably mounted to a triangular convergent upper ramp in the convergent section along left and right side convergent angled hinge lines respectively. The upper wall further includes triangular left and right side divergent upper panels pivotably attached to a triangular divergent upper ramp in the divergent section along left and right side divergent angled hinge lines respectively. The left and right side convergent upper panels are in sealing engagement with the left and right side divergent upper panels along left and right side upper interfaces, respectively.

Abstract: A gas turbine engine augmentor includes an externally fueled annular trapped vortex cavity having a cavity opening open to an exhaust flowpath and a sole source of fuel located upstream of the trapped vortex cavity and being operable for injecting fuel into the exhaust flowpath such that at least a portion of the fuel flows into the cavity through a cavity opening. An exemplary sole source of fuel includes fuel holes in fuel tubes within spray bars operable for injecting the fuel through heat shield openings in heat shields surrounding the tubes wherein the fuel holes are located in a radially outermost portion of the exhaust flowpath. The sole source of fuel may include circumferentially spaced apart radial spray bars and/or integral spray bars integral with radial flameholders and extending radially inwardly into the exhaust flowpath wherein the radial flameholders and radial spray bars are interdigitated.

Abstract: A turbofan gas turbine engine augmenter includes a fuel/air swirler disposed between an axially extending bypass flowpath and an axially extending exhaust flowpath. A swirler inlet is axially open to and positioned substantially normal to the bypass flowpath and a swirler outlet is open to and positioned substantially parallel to the exhaust flowpath. A swirl chamber within the fuel/air swirler is between the swirler inlet and the swirler outlet. A swirl axis of the fuel/air swirler extends through the swirler outlet substantially normal to the exhaust flowpath. An air swirler may be centered about the swirl axis within the fuel/air swirler. The air swirler may be a louvered or have a plurality of swirling vanes. The swirler inlet may be radially offset with respect to the swirl axis. An air scoop may lead from the swirler inlet to a rounded swirler housing within which the air swirler is disposed.

Abstract: An automatic engine protection system for use when electronic parts of the control system are exposed to overtemperature conditions. A thermally sensitive component, such as an engine electronic control or an electronic overspeed control, is mounted on the engine. A thermal fuse is mounted adjacent, or in thermal contact with, the speed control. The thermal fuse is placed in electrical series with a valve which controls fuel delivery to the engine. If the temperature of the fuse exceeds its melting point, indicating a possible danger to the electronic control, the fuse melts, thereby terminating fuel to the engine.

Abstract: A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or welding. The first vane assembly member includes the outer band, the airfoil, an inner flange, and a first segment of the inner band with a first edge, spaced from the flange and extending between and through inner band circumferential edge portions. The second vane assembly member includes a second segment of the inner band including a second edge of shape and size matched with the first edge and extending through the inner band circumferential edge portions.

Abstract: A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.

Abstract: A method for introducing an inert carrier gas into a coating container used to provide a metallic coating on articles. The method includes introducing the inert carrier gas into the coating container as a plurality of carrier gas streams proximate the top of the coating container. The carrier gas streams are formed and introduced into the coating container before encountering a source material for the metallic coating, and each carrier gas stream is introduced so that the inert carrier gas at least initially moves within the coating container in a circular swirling fashion above and before encountering the source material and the article.

Abstract: A coating process and system suitable for use on components subjected to high temperatures. The coating system includes an overlay coating of predominantly B2 phase rhodium aluminide (RhAl) intermetallic compound containing about 25 to about 90 atomic percent rhodium, about 10 to about 60 atomic percent aluminum, optionally up to a combined total of about 25 atomic percent of one or more platinum group metals chosen from the group consisting of platinum, palladium, ruthenium, and iridium, and up to about 20 atomic percent of the base metal and alloying constituents of the substrate. The RhAl intermetallic coating may serve as an environmental coating, a diffusion barrier layer for an overlying environmental coating, or both, with or without an outer ceramic coating.

Abstract: A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed therein, wherein a radial section is defined between each adjacent opening; and, a mixer assembly located upstream of and in substantial alignment with each of the openings in the dome plate, with the mixer assembly including a forward portion and an aft portion. Each mixer assembly is retained in a manner so as to be movable in a radial and axial direction without obstructing the radial sections of the dome plate. A first pair of tabs are positioned on the forward surface of the dome plate adjacent each opening and a second pair of tabs are positioned on the aft portion of each mixer assembly, wherein the dome plate tabs interface with the mixer assembly tabs to prevent rotation of each mixer assembly.

Abstract: A coating system for Si-containing materials, particularly Si-based composites used to produce articles exposed to high temperatures. The coating system is a compositionally-graded thermal/environmental barrier coating (T/EBC) system that includes an intermediate layer containing yttria-stabilized hafnia (YSHf) and mullite, alumina and/or an aluminosilicate, which is used in combination with an inner layer between a Si-containing substrate and the intermediate layer and a thermal-insulating top coat overlying the intermediate layer. The intermediate layer provides environmental protection to the silicon-containing substrate, and has a coefficient of thermal expansion between that of the top coat and that of the inner layer so as to serve as a transition layer therebetween. The intermediate layer is particular well suited for use in combination with an inner layer of an alkaline earth metal aluminosilicate (such as BSAS) and a top coat formed of YSZ or YSHf.

Abstract: A high energy system comprising a high energy electrical device powered by an electrical generator both of which are cooled by a cryogenic liquid oxidant stored in a storage tank. A power turbine powered by a combustor using fuel and the oxidant drives the electrical generator. A turbopump powered by a portion of exhaust flow from the power turbine pumps the cryogenic liquid oxidant from the storage tank to the generator and the device. In an exemplary embodiment of the system, the electrical device is a directed energy weapon, uses liquid air as the liquid oxidant, and uses a variable geometry turbine nozzle in the power turbine. A reheater may be used between a high pressure turbine and a lower pressure turbine of the power turbine. Compressor bleed from a gas turbine engine may provide air augmentation to the power turbine.

Abstract: A refueling drogue adapted to connect to a refueling hose extending from a refueling aircraft. The refueling drogue may include an active control system, wherein, in an exemplary embodiment, the active control system is adapted to regulate the position of the drogue to maintain a substantially fixed orientation relative to a refueling aircraft.