18717results about "Efficient propulsion technologies" patented technology

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.

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.

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.

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.

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 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.

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.

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.

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.

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.