18828results about "Efficient propulsion technologies" patented technology

Embodiments of the invention provide methods for depositing dielectric materials on substrates during vapor deposition processes, such as atomic layer deposition (ALD). In one example, a method includes sequentially exposing a substrate to a hafnium precursor and an oxidizing gas to deposit a hafnium oxide material thereon. In another example, a hafnium silicate material is deposited by sequentially exposing a substrate to the oxidizing gas and a process gas containing a hafnium precursor and a silicon precursor. The oxidizing gas usually contains water vapor formed by flowing a hydrogen source gas and an oxygen source gas through a water vapor generator. In another example, a method includes sequentially exposing a substrate to the oxidizing gas and at least one precursor to deposit hafnium oxide, zirconium oxide, lanthanum oxide, tantalum oxide, titanium oxide, aluminum oxide, silicon oxide, aluminates thereof, silicates thereof, derivatives thereof or combinations thereof.

Embodiments of the invention provide apparatuses and methods for depositing materials on substrates during vapor deposition processes, such as atomic layer deposition (ALD). In one embodiment, a chamber contains a substrate support with a receiving surface and a chamber lid containing an expanding channel formed within a thermally insulating material. The chamber further includes at least one conduit coupled to a gas inlet within the expanding channel and positioned to provide a gas flow through the expanding channel in a circular direction, such as a vortex, a helix, a spiral or derivatives thereof. The expanding channel may be formed directly within the chamber lid or formed within a funnel liner attached thereon. The chamber may contain a retaining ring, an upper process liner, a lower process liner or a slip valve liner. Liners usually have a polished surface finish and contain a thermally insulating material such as fused quartz or ceramic. In an alternative embodiment, a deposition system contains a catalytic water vapor generator connected to an ALD chamber.

In a combined steam and gas turbine engine cycle, a combustion chamber is made durable against high pressure and enlarged in length to increase the operation pressure ratio, without exceeding the heat durability temperature of the system while increasing the fuel combustion gas mass flow four times as much as the conventional turbine system and simultaneously for greatly raising the thermal efficiency of the system and specific power of the combined steam and gas turbine engine.Water pipes and steam pipes are arranged inside the combustion chamber so that the combustion chamber can function as a heat exchanger and thereby convert most of the combustion thermal energy into super-critical steam energy for driving a steam turbine and subsequently raising the operation pressure ratio and the thermal efficiencies of the steam turbine cycle and gas turbine cycle. The combustion gas mass flow can be also increased by four times as much as the conventional turbine system (up to the theoretical air to fuel ratio) and the thermal efficiency and the specific power of the gas turbine cycle are considerably increased.Further, the thermal efficiency of the combined system is improved by installing a magnetic friction power transmission system to transmit the power of the system to outer loads.

A coupling system for connecting a sun gear to a shaft within a planetary gear train, includes a sun gear coupling connecting the sun gear to the shaft. The sun gear coupling has at least one undulant flexible section joined to an inflexible spindle for accommodating misalignment between the sun gear and the shaft. The flexible section comprises a cylindrical ring having a diameter greater than the diameter of the spindle, and joined to the spindle by two longitudinally spaced apart diaphragms. The juncture between the diaphragms, the ring, and the spindle is curved in cross section on an outer side to improve flexibility and minimize stress concentrations, and the inner sides of the diaphragms are straight edges which result in a non-symmetric contour of the diaphragm walls.

An article is described, including an inner surface which can be exposed to a first fluid; an inlet; and an outer surface spaced from the inner surface, which can be exposed to a hotter second fluid. The article further includes at least one row or other pattern of passage holes. Each passage hole includes an inlet bore extending through the substrate from the inlet at the inner surface to a passage hole-exit proximate to the outer surface, with the inlet bore terminating in a chevron outlet adjacent the hole-exit. The chevron outlet includes a pair of wing troughs having a common surface region between them. The common surface region includes a valley which is adjacent the hole-exit; and a plateau adjacent the valley. The article can be an airfoil. Related methods for preparing the passage holes are also described.

A rechargeable battery energized unmanned aerial vehicle having surveillance capability and an ability to clandestinely collect propulsion and other energy needs from a conveniently located and possibly enemy owned energy transmission line. Energy collection is by way of a parked vehicle engagement with the transmission line in a current flow dependent, magnetic field determined, rather than shunt, voltage dependent, conductor coupling. Surveillance during both a parked or docked condition and during aerial vehicle movement is contemplated.

An aircraft engine turbine frame includes a first structural ring, a second structural ring disposed co-axially with and radially spaced inwardly of the first structural ring about a centerline axis. A plurality of circumferentially spaced apart struts extend between the first and second structural rings. Forward and aft sump members having forward and aft central bores are fixedly joined to forward and aft portions of the turbine frame respectively. A frame connecting means for connecting the engine to an aircraft is disposed on the first structural ring. The frame connecting means may include a U-shaped clevis. The frame may be an inter-turbine frame axially located between first and second turbines of first and second rotors of a gas turbine engine assembly. An axial center of gravity of the second turbine passes though or very near a second turbine frame bearing supported by the aft sump member.

A turbofan includes a row of fan blades extending from a supporting disk inside an annular casing. Each blade includes an airfoil having opposite pressure and suction sides extending radially in span between a root and tip and axially in chord between leading and trailing edges. Adjacent airfoils define corresponding flow passages therebetween for pressurizing air. Each airfoil includes stagger increasing between the root and tip, and the flow passage has a mouth between the airfoil leading edge and the suction side of an adjacent airfoil and converges to a throat aft from the mouth. The row includes no more than twenty fan blades having low tip solidity for increasing the width of the passage throat.

Components (1) have a thermal barrier coating (2-6) on the surface thereof, wherein the thermal barrier coating includes at least one layer (3) having chemically stabilized zirconia, and wherein at least indirectly adjacent to the layer (3) with chemically stabilized zirconia and on its surface facing side, there is provided a protective layer (4) and / or a infiltration zone (5) which does not react with environmental contaminant compositions that contain oxides of calcium and which does not react with the material of the layer (3) having chemically stabilized zirconia. Methods for making such components as well as to uses of specific systems for coating thermal barrier coatings, can prevent CMAS.

What has been created is a plurality and a variety of processes and a variety of devices correspondingly supportive to each process, wherein, a new partnership between; (1) a heat absorbing radiator compressed air pipes / tubes and (2) a gas turbine engine or a reciprocating piston engine,—is used to recapture and reconvert the, otherwise wasted, heat energies expelled by engines, by factories, by smelting plants, by distillation plants, by chillers / coolers / freezers, by cooking ovens, by lamps / stoves, by trash burners, and the heat energies created by the solar heat on the desert / ocean water,—into electric power and finally into hydrogen-deuterium fuel,—by having the engine's tailpipes submerged in cold compressed air inside the heat absorbing radiator pipes in reverse air flow, to further drive and re-drive the same engine; wherein, in order to capture fusion heat energy the hydrogen bomb is detonated in the deep ocean to catch the flames by the water and the hot water is used to energize the compressed air inside the heat absorbing radiator pipes; wherein, in order to produce fusion energy, an abundant electric arc is passed across liquid deuterium or across gaseous deuterium by the electro-plasma torch and sparkplug in the internal combustion engine, and by detonating a dynamite inside a liquid deuterium; wherein diamond is produced by placing carbon inside the hydrogen bomb; and wherein, deuterium fusion flame is used first in smelting glass to large sizes before running an engine.

A supercharging system for gas turbine power plants (11). The system includes a supercharging fan (30, 32) and controller (50) for limiting turbine power output to prevent overload of the generator (28) at lower ambient temperatures. The controller can limit power output by burner control, inlet temperature control, control of supercharging fan pressure and other options. The system can be retrofit on an existing turbine without replacing the generator and associated parts.

A method of manufacturing a monolithic composite wing without using mechanical fasteners is described. The process begins with the formation of a center wing box in combination with a pair of spars, riblets and a pair of skin-molds including the wrapping and binding of the box by means of resin impregnated composite tapes. Next, additional cells are adjoined contiguously on either side of the current framework and an overlap wrapping and bonding process is continued around the current framework. The overlap wrapping and binding procedure provides increased torsion stiffness and reduced structural weight. All cells up to the leading and trailing edges will be included in the assembly process. Conduits to convey fuel, hydraulic fluid and electrical wiring will also be installed in designated cells. Finally, the completed wing will be cured in an autoclave under uniform pressure and temperature.

A method and apparatus for controllable distribution of power from a turbine of a gas turbine engine between two rotatable loads of the gas turbine engine, comprises transferring a shaft power of the turbine to the respective rotatable loads using differential gearing operatively coupled with the turbine and the rotatable loads, respectively; and controlling the power transfer using machines operatively coupled with the respective rotatable loads, operable as a generator or a motor for selectively taking power from one of the rotatable loads to drive the other of the rotatable loads, or the reverse.

An unmanned air vehicle is provided, which includes an airframe and a parallel hybrid-electric propulsion system mounted on the airframe. The parallel hybrid-electric propulsion system includes an internal combustion engine and an electric motor. A hybrid controller is configured to control both the internal combustion engine and the electric motor. A propeller is connected to a mechanical link. The mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller. An alternate unmanned air vehicle includes a second propeller driven by the electric motor. In this alternate unmanned air vehicle, the internal combustion engine is decoupled from the electric motor.

A segmented abradable ceramic coating system having superior abradability and erosion resistance is disclosed. The system includes a duct segment having a metallic substrate, a MCrAlY bond coat on the substrate and a segmented abradable ceramic coating on the bond coat. The segmented abradable ceramic coating includes a base coat foundation layer, a graded interlayer and an abradable top layer for an overall thickness of preferably about 50 mils (1.270 mm). The coating is characterized by a plurality of vertical microcracks. By precisely controlling the deposition parameters, composition of the layers and layer particle morphology, segmentation is achieved, as well as superior abradability and erosion resistance.

Particles have an ultrathin, conformal coating are made using atomic layer deposition methods. The base particles include ceramic and metallic materials. The coatings can also be ceramic or metal materials that can be deposited in a binary reaction sequence. The coated particles are useful as fillers for electronic packaging applications, for making ceramic or cermet parts, as supported catalysts, as well as other applications.

A method and apparatus for extracting CO2 from air comprising an anion exchange material formed in a matrix exposed to a flow of the air, and for delivering that extracted CO2 to controlled environments. The present invention contemplates the extraction of CO2 from air using conventional extraction methods or by using one of the extraction methods disclosed; e.g., humidity swing or electro dialysis. The present invention also provides delivery of the CO2 to greenhouses where increased levels of CO2 will improve conditions for growth. Alternatively, the CO2 is fed to an algae culture.

The invention provides methods of manufacturing biodiesel and other oil-based compounds using glycerol and combinations of glycerol and other feedstocks as an energy source in fermentation of oil-bearing microorganisms. Methods disclosed herein include processes for manufacturing high nutrition edible oils from non-food feedstock materials such as waste products from industrial waste transesterification processes. Also included are methods of increasing oil yields by temporally separating glycerol and other feedstocks during cultivation processes. Also provided herein are oil-bearing microbes containing exogenous oil production genes and methods of cultivating such microbes on glycerol and other feedstocks.

A system (200) for distributing electrical power, includes: a first high voltage AC power distributing unit (210a) including a first high voltage AC bus (214a-1, 214a-2), which is selectively connected to a first high voltage AC generator (224a), and a first start bus (212a); a second high voltage AC power distributing unit (210b) including a second high voltage AC bus (214b-1, 214b-2), which is selectively connected to a second high voltage AC generator (224b), and a second start bus (212b); a first high voltage DC power distributing unit (240a) including, a first high voltage DC bus (246a), and a second high voltage DC power distributing unit (240b) including a second high voltage DC bus (246b). The first high voltage AC bus (214a-1, 214a-2) is selectively connectable to the second high voltage AC bus (214b-1, 214b-2), such that the system (200) provides redundancy for high voltage power distribution.

A composite thermal barrier coating system includes a honeycomb metallic structure filled with high thermal expansion ceramic hollow spheres in a phosphate bonded matrix. The composite thermal barrier coating system may be manufactured to thicknesses in excess of current thermal barrier coating systems, thereby imparting greater thermal protection. Superior erosion resistance and abrasion properties are also achieved. The composite thermal barrier coating is useful on combustion turbine components such as ring seal segments, vane segment shrouds, transitions and combustors.

An advanced internal combustion-electric hybrid airplane, having at least double the flight range and flight duration than a conventional equivalent airplane, while using the same amount of any desirable fuel. This is achieved by using 2-3× smaller and ultra-lightweight engine for cruising, and ultra-lightweight electric motor powered by lithium batteries during take-off and climbing. The electric motor becomes a generator during cruising and descent, recharging said batteries. The airplane has also temporary silent electric stealth capability and added safety by the electric back-up power. Due to its high efficiency, the operational cost is substantially reduced. Additional features include highly advanced, minimum drag and weight airframe.

A process for producing a blended fuel from a paraffin rich component and a cyclic rich component, where each of the components are generated from a renewable feedstock, is presented. The paraffin rich component is generated from a first renewable feedstock comprising at least one component selected from the group consisting of glycerides, free fatty acids, biomass, lignocellulose, free sugars, and combinations thereof. The cyclic rich component is generated from a second renewable feedstock comprising at least one component selected from the group consisting of glycerides, free fatty acids, free fatty alkyl esters, biomass, lignocellulose, free sugars, and combinations thereof. The blended fuel may a gasoline boiling point range blended fuel, a diesel boiling point range blended fuel, an aviation boiling point range blended fuel, any combination thereof, or any mixture thereof.

Biofuels can be produced by: (i) providing a biomass containing celluloses, hemicelluloses, lignin, nitrogen compounds and sulfur compounds; (ii) contacting the biomass with a digestive solvent to form a pretreated biomass containing carbohydrates; (iii) contacting the pretreated biomass with hydrogen in the presence of a supported hydrogenolysis catalyst containing (a) sulfur, (b) Mo or W, and (c) Co and / or Ni incorporated into a suitable support to form a plurality of oxygenated intermediates, and (vi) processing at least a portion of the oxygenated intermediates to form a liquid fuel.

A variable geometry inlet guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning inlet flow to a turbine or compressor and an internal spar spaced from the airfoil shell by an air gap. A number of actuation mechanisms grounded to the spar and connected to the inner surface of the aerodynamic shell adjust the shape of the shell in response to varying operating conditions of the engine, imbalanced aerodynamic loading of the shell or vibration or other transient loads on the shell.

Provided is an accessory gearbox for a gas turbine engine that contributes minimally to engine weight and complexity. An accessory gearbox comprises a stationary frame that is circumferentially disposed about a central longitudinal axis of the engine. The frame includes a forward-directed axial face and a rearward-directed axial face for fastening the frame to the engine. A central bore accepts a rotational driving means and an outermost rim circumscribes the outer diameter of the frame. A compartment is located between the bore and the rim. At least one primary accessory is mounted to a face and proximate the compartment, remotely engaging the driving means and able to be driven concurrently therewith.

A vertical takeoff and landing (VTOL) aircraft is superior in maneuverability, safety, and mobility. The aircraft has turbofan engines with separate core engines having fan engines used commonly for cruising and lifting up. The thrust from the fan engines can be directed to all directions by supporting the fan engines of the turbofan engines with separate core engines with biaxial support so that the fan engines are rotatable in the direction of pitching and rolling. The fan engines are mounted on both sides of each of front and rear sings. With this construction, the VTOL aircraft can cruise and hover by tilting the fan engines about the two axes while using the fan engines commonly for cruising and hovering.