36results about "Efficient propulsion technologies" patented technology

There is disclosed a gas turbine shroud structure comprising: a shroud support component 12 attached to an inner surface of a gas turbine casing 3; a shroud segment 14 divided in a peripheral direction and supported by the inner surface of the shroud support component; and a heat-resistant restricting spring 18 held between the shroud segment and shroud support component to urge the shroud segment inwards in a radial direction. The shroud segment 14 is formed of a ceramic composite material, and includes a coating layer 15 having heat insulation and impact absorption effect on an inner surface of the segment.

An electric, inductively-energized, multi-bladed, controllable-pitch propeller hub is configured with an internal battery, electronic control unit and electric internal reversible hubmotor, when energized by a voltage inducted across an air gap into an annulus of receiver coils that is mounted onto said propeller hub and when said propeller hub is attached to and operated with complementary electrical, electronic and mechanical components that enable wireless command signals, together forming a novel and versatile device whose operation can provide near-instantaneous modulation of aircraft thrust, lift and drag by the action of said propeller hub to actuate precise and equal changes to the pitch of each propeller blade through a full range of useful pitch settings, both during rotation of said propeller hub and when said propeller hub is stationary, with an innovation including a coaxial driveshaft that facilitates the removal and installation of said propeller hub from a propmotor.

A write-once-read-many optical recording medium enabling excellent recording and reproducing properties at a wavelength of blue-laser wavelengths or shorter, i.e. 500 nm or less, particularly at wavelengths of near 405 nm and high density recording. To this end, a write-once-read-many optical recording medium of the invention comprises a recording layer using a material represented by BiOx (0<x<1.5), in which a recorded mark comprises crystal of Bi and/or crystal of a Bi oxide. Another write-once-read-many optical recording medium comprises a recording layer which comprises Bi, oxygen, and M (M represents at least one element selected from Mg, Al, Cr, Mn, Co, Fe, Cu, Zn, Li, Si, Ge, Zr, Ti, Hf, Sn, Mo, V, Nb, Y, and Ta), in which a recorded mark comprises crystal of the elements contained in the recording layer and crystal of an oxide of the elements.

Noise reduction conduit for non rotary components of aircraft engines, subjected to a characteristic range of temperatures of a gas turbine engine, constituted by an annular structure composed of an aerodynamic wet wall (10a, 10b), perforated and resistant mechanically and thermally; of a dry wall (12a, 12b), not resistant and of light weight; and of some intermediate elements to which both walls are mechanically attached and that define a jump or difference of temperature between the wet and dry walls; between which wet (10a, 10b) and dry walls (12a, 12b) there are partitions that define cavities (16a, 16b) isolated with regard to each other.

The invention relates to gas turbine engine seal systems having a rotating member with an abrasive tip surface disposed in rub relationship to a stationary seal member with an abradable surface. The abrasive tip surface is coated with a metallic alloy matrix having ceramic abrasive particles embedded in and projecting from the matrix. The abradable seal surface is coated with a ceramic coating. The rub relationship affords a tight operating clearance between the rotating member and the stationary seal member, thereby improving engine efficiency, reducing fuel consumption and minimizing overhaul downtime.

A system, including, a turbine combustor, including, a first wall disposed about a flow path of hot combustion gases, a second wall disposed about the first wall, and a damping system disposed between the first and second walls, wherein the damping system is configured to dampen vibration, and the damping system is tuned to dynamic drivers in the turbine combustor.

An airfoil refurbishment system is disclosed. The airfoil refurbishment system includes an environmentally safe stripper system and an aluminiding system. The environmentally safe stripper system includes a transportable environmentally safe compound that is capable of partially removing an aluminide coating from an airfoil. The aluminiding system is capable of restoring the aluminide coating to the airfoil.

An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

The disclosure relates to a cylinder head having at least one cylinder. The cylinder head comprises a radial turbine including a rotor arranged in a turbine casing and rotatably mounted on a shaft, an overall exhaust line which opens into an inlet zone of the radial turbine, said zone merging into a flow duct which carries exhaust gas, and at least one coolant duct integrated into the turbine casing to form a cooling system, the at least one coolant duct extending in a spiral around the shaft in the casing, wherein the at least one coolant duct extends circumferentially around and at a distance from the flow duct over an angle α, where α≦45°.

An electric charging system for a vessel, vehicle, or aircraft includes one or more energy storage modules on the vessel, vehicle, or aircraft; a pulse rectifier; a converter; and a voltage control transformer. The one or more energy storage modules are connected to outputs of the pulse rectifier. The voltage control transformer is connected to inputs of the pulse rectifier. The voltage control transformer includes a serial transformer having a plurality of pairs of transformer windings, connected together in series, one winding of each pair being adapted to be connected between the pulse rectifier and an input from an energy source and the other winding is connected to the converter.

A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one catch to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that a portion of the at least one spline seal is received within a recess defined within the turbine nozzle slot to facilitate retaining the at least one spline seal within the turbine nozzle slot.

A head part of an annular combustion chamber for a gas turbine, the head part comprising: an end wall with a passage opening for accommodating a burner, the end wall comprising a back side which faces towards the combustion chamber; a burner collar adapted to fit within the passage opening and receive the burner, the burner collar comprising a protruding portion radially protruding from an outer surface of the burner collar; and a ring member for receiving the protruding portion of the burner collar; wherein the head part of the annular combustion chamber is configured such that in an installed configuration a radially outer portion of the ring member engages with the end wall and a radially inner portion of the ring member receives the protruding portion of the burner collar.

A gas turbine engine system includes a gas turbine engine using vaporized liquefied gas as fuel. The gas turbine engine is configured to ingest intake air from an intake port and direct exhaust gases to an exhaust port. The gas turbine engine system also includes a heat exchanger with a heat transfer fluid therein. The heat exchanger is configured to create at least a part of the fuel by heating the liquefied gas. The gas turbine engine system also includes an intake air temperature control circuit. The intake air temperature control circuit includes conduits configured to direct the heat transfer fluid to the intake port and the exhaust port. The gas turbine engine system also includes a control system configured to selectively direct the heat transfer fluid to one of the intake port and the exhaust port.

The invention relates to a tetragonal phase high-entropy thermal barrier coating material. The material is formed by ZrO2, Y2O3, M2O3, Ta2O5 and Nb2O5 oxide powder, the component of the material is Zr1-4xYxMxTaxNbxO2, x is more than 0 and less than 0.25, and M is a trivalent rare earth element. The invention also relates to a preparation method of the tetragonal-phase high-entropy thermal barrier coating material. The preparation method comprises the following steps: calcining to remove adsorbed water and impurities in each oxide powder; performing high-energy ball milling; separating, washing and drying balls to obtain mixed powder; and pressing into a ceramic blank by using a ceramic tablet press, and heating to obtain the high-entropy ceramic block material. According to the tetragonal-phase high-entropy thermal barrier coating material, excellent thermodynamic properties are provided through multi-component high entropy, including reduction of heat conductivity, increase of thermal expansion coefficient, enhancement of fracture toughness, good high-temperature stability, excellent CMAS corrosion resistance and the like, and the tetragonal-phase high-entropy thermal barrier coating material has the potential of serving at a higher gas temperature.

A gas turbine engine including a component having a first and a second component that are attached or integrally formed with each other. The first and the second component define an enclosed void. An insert is positioned within the enclosed void which is formed of a material having a relatively low Young's modulus. The insert may prevent resin from filling the enclosed void during assembly/manufacture of the component, while also reducing a weight of the component and an amount of stress on the component. The component may be a fan platform positioned between a plurality of fan blades, an outlet guide vane, or another component of the gas turbine engine.

A composite material includes a polymeric matrix, at least one transparent region including a plurality of optically clear elements provided in the polymeric matrix and at least one opaque region including a plurality of opaque reinforcing elements provided in the polymeric matrix generally adjacent to the at least one transparent region. A structural window and a method for reinforcing a composite material are also disclosed.

A fuel cooled cooling air heat exchanger includes a fuel injector and an airflow body. The fuel injector has a fuel flow passage formed therein that includes a fuel inlet port and a fuel outlet port. The airflow body is coupled to and surrounds at least a portion of the fuel injector. The airflow body has an inner surface that is spaced apart from the fuel injector to define an airflow passage between the airflow body and the fuel injector, and the airflow passage includes an air inlet port and an air outlet port.

The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.

The present invention provides a bypass duct and boss assembly comprising: a bypass duct having an exterior surface, an interior surface, an edge surface, an inner bonding surface, and a side wall surface, wherein the edge surface further defines an aperture; a boss having a lip surface, a side surface, and a face surface, wherein the boss is disposed within the aperture of the bypass duct such that the lip surface of the boss forms matched bonding surfaces with a portion of the exterior surface of the bypass duct, and such that the side surface of the boss forms matched bonding surfaces with the edge surface of the bypass duct; a patch having a patch edge, a patch inner surface, and a patch outer surface, wherein the patch is disposed such that the patch inner surface forms matched bonding surfaces with the inner bonding surface of the bypass duct and the face surface of the boss, and such that the patch edge forms matched bonding surfaces with the side wall surface of the bypass duct, the patch further having a thickness and curvature, and the patch further disposed such that the patch outer surface forms a continuous curvature with the interior surface of the bypass duct; and adhesive disposed between the matched bonding surfaces so as to firmly bond the bypass duct, boss, and patch into the assembly.

A gas turbine engine has a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction, and includes a lubricant pump to supply an air/oil mixture to an inlet of a deaerator. The deaerator includes a separator for separating oil and air, delivering separated air to an air outlet, and delivering separated oil back into an oil tank. The separated oil is first delivered into a pipe outwardly of the oil tank, and then into a location beneath a minimum oil level in the tank. Air within the oil tank moves outwardly through an air exit into the deaerator. A method of designing a gas turbine engine is also disclosed.

An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve.

The invention provides a testing device for a motor of a miniature unmanned aerial vehicle. The testing device comprises a tension testing structure, a torque testing structure and a computer, wherein the tension testing structure, the torque testing mechanism and the computer are arranged on an experiment table. By adopting the testing device, the tension and the torque of the motor can be at least synchronously measured conveniently and quickly; moreover, the overall structure is simple in design; the cost is low; the testing device is high-efficiency and practical; measured data of the tension, the torque and the like can be transmitted to the computer in real time; the data processing is conveniently carried out.

Method of producing a gas-tight solid electrolyte layer for a high-temperature fuel cell, wherein a layer is produced from a metal oxide material and metal particles are incorporated in the layer during production of the layer, the metal particles being oxidizable, and wherein the metal particles are subsequently oxidized.

The invention relates to a method for manufacturing a thermal barrier comprising a ceramic coating layer and covering at least one portion of the surface of a substrate, in which the ceramic coating layer is deposited on the substrate solely by a cathodic electrodeposition process between at least one cathode (26) and an anode (28), the substrate being formed from an electronically conducting material and constituting the cathode. Characteristically, the electrolyte (24) comprises at least one salt chosen from the group comprising lanthanide, yttrium, zirconium, and hafnium salts, so that, through the electrodeposition process, the coating layer comprises at least one oxide chosen from the group comprising lanthanide, yttrium, zirconium, and hafnium oxides. The method further includes a step of heat-treating the ceramic coating layer between 400 DEG C and 2000 DEG C for at least 10 minutes.

The present invention provides a zirconium oxide powder, a method for producing.the same, and a material for thermal spraying. The material for thermal spraying comprises a zirconium oxide powder comprising polyhedral particles each having not less than 6 faces, wherein the zirconium oxide powder has D50 of not less than 5 μm and less than 15 μm and a D90/D10 of less than 3. D10, D50 and D90 correspond to the point where the cumulative mass from the small-particle-diameter side reaches 10%, 50%, and 90% in the cumulative particle size distribution.

An electrical storage system includes an electric storage zone, an electric storage positioned within the electric storage zone, a cooling fluid source in fluid communication with the electric storage zone via a fluid flow path, a modulating valve in the fluid flow path downstream from the cooling fluid source and upstream from the electric storage zone, and a detector in fluid communication with the electric storage zone. A method for operating an electrical storage system includes adjusting a modulating valve in a fluid flow path to reduce a cooling airflow to an electric storage zone, operating a detector in fluid communication with the electric storage zone configured and adapted to sense at least one of smoke, gas, or other particulates during a detection period with a detection system, and adjusting the modulating valve to increase the cooling airflow to the electric storage zone.