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4668results about "Rocket engine plants" patented technology
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Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine
InactiveUS20130219853A1Easy to operateReduce lossesContinuous combustion chamberGas turbine plantsCombustorTurbine
A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).
Owner:SIEMENS ENERGY INC
Nontoxic, noncorrosive phosphorus-based primer compositions and an ordnance element including the same
Owner:NORTHROP GRUMMAN SYST CORP
System, method and apparatus for lean combustion with plasma from an electrical arc
The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, (b) extends into the cylindrical vessel, and (c) can be moved along the longitudinal axis, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle creates a plasma that discharges through the hollow electrode nozzle.
Owner:FORET PLASMA LABS
System, method and apparatus for lean combustion with plasma from an electrical arc
The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, (b) extends into the cylindrical vessel, and (c) can be moved along the longitudinal axis, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle crate a plasma the discharges through the hollow electrode nozzle.
Owner:FORET PLASMA LABS
Variable Magnetic Coupling of Rotating Machinery
ActiveUS20080149445A1Reduce vibration transmissionMechanical actuated clutchesEngine fuctionsCouplingEngineering
A system for transferring torque between a pair of independently, concurrently rotating shafts of a turbofan engine includes a magnetic gearbox. The magnetic gearbox has a first ring structure, a second ring structure and an intermediate ring structure. Each ring structure has an annular aperture therethrough and a plurality of permanent magnets embedded therein. The intermediate ring structure is disposed between the first and the second ring structures. Each ring structure is coaxially concentric with, and independently rotatable with respect to the remaining ring structures. The first and second ring structures are each coupled to separate ones of the rotating engine shafts, and the intermediate ring is operable to transfer torque between the pair of shafts. Preferably, the intermediate ring structure is coupled to a rotating machine. The rotating machine has a controller, and is operable for adjusting a ratio of torque transferred between the pair of shafts.
Owner:GENERAL ELECTRIC CO
Hybrid Gas Turbine Propulsion System
ActiveUS20150013306A1Reduce fuel consumptionImprove responsivenessGas turbine type power plantsEfficient propulsion technologiesAir compressionDual-thrust
A hybrid aerodynamic thrust system as a prime mover for aircraft or other high-speed vehicles. An arrangement of dual thrust resources to alternately accommodate low and high airspeed regimes. Electromotive force is used in lieu of hot section power turbines to achieve engine air compression or alternately perform thrust work at low velocities.
Owner:SHELLEY RUDOLPH ALLEN
Aircraft propulsion system
InactiveUS20060254255A1Highly compatible with environmentSynchronous generatorsMagnetic circuitCombustion chamberLiquid hydrogen
To provide an aircraft propulsion system which can secure the optimum thrust and thrust vector for flight conditions, as well as the optimum sectional area for the engine, and which is highly compatible with the environment. An electrical generator is coupled to a turbofan engine, the electrical generator is driven by output power of the turbofan engine to output electric power, and an electromagnetic driving fan is driven by the electric power. On the other hand, after bringing each of coils in the electromagnetic driving fan to a superconductive state, liquid hydrogen is introduced to a heat exchanger, collects the energy of exhaust as heat, is then vaporized, and thereafter supplied to a combustor and to a fuel cell. Further, the electromagnetic driving fan is changed in its rotational phase by a rotating mechanism portion, is made movable in a width direction of a wing and a wing chord direction by a slide mechanism portion, and can be stored inside or outside the wing by a storage mechanism portion.
Owner:JAPAN AEROSPACE EXPLORATION AGENCY +1
Fluid mixer with an integral fluid capture ducts forming auxiliary secondary chutes at the discharge end of said ducts
ActiveUS7434384B2Improve performanceEfficient capturePower plant exhaust arrangementsPower plant constructionEngineeringMain lobe
A fluid mixer for mixing two fluid streams 40, 42 includes a set of main lobes 26 defining alternating primary and secondary main chutes 30, 32, one or more auxiliary lobes 28 intermediate two of the main lobes, and an auxiliary fluid capture duct 62. The auxiliary lobes are defined, at least in part, by the discharge end of the duct. In operation, the duct conveys secondary fluid to secondary chutes 36 defined by the lobes thereby improving the performance of the mixer despite the presence of an obstruction 18 that would otherwise impede thorough mixing of two fluid streams.
Owner:RTX CORP
Integrated bypass turbojet engines for air craft and other vehicles
InactiveUS6966174B2Reduce complexityReduce weightJet type power plantsEfficient propulsion technologiesRam air turbineTurbojet engine
Turbojet engines and aircraft configurations for advantageous use of the turbojet engines; the turbojet engines utilizing ram air turbine units that centrifugally compress air isothermally for use in various combustion configurations designed for stoichiometric combustion, wherein a stream of by-pass ram-air jets is mixed with combustion gas jets for discharge in a common discharge nozzle.
Owner:PAUL MARIUS A
Gas turbine engine assembly and methods of assembling same
InactiveUS20080098716A1Cosmonautic vehiclesCosmonautic propulsion system apparatusTurbineGas turbines
A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor directly to the low-pressure turbine such that the booster compressor rotates in the first direction.
Owner:GENERAL ELECTRIC CO
Gas turbine engine assembly and methods of assembling same
A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor directly to the low-pressure turbine such that the booster compressor rotates in the first direction.
Owner:GENERAL ELECTRIC CO
Apparatus for combusting a fuel at high pressure and high temperature, and associated system
ActiveUS8986002B2Reducing and eliminating needEliminate damage to and build-upContinuous combustion chamberGas turbine plantsWorking fluidCombustor
A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a porous perimetric transpiration member, at least partially surrounded by a pressure containment member. The combustion chamber has longitudinally spaced apart inlet and outlet portions. The fuel mixture is received by the inlet portion for combustion within the combustion chamber at a combustion temperature to form a combustion product. The combustion chamber directs the combustion product longitudinally toward the outlet portion. The transpiration member is configured to substantially uniformly direct a transpiration substance therethrough toward the combustion chamber, such that the transpiration substance is directed to flow helically about the perimeter and longitudinally between the inlet and outlet portions, for buffering interaction between the combustion product and the transpiration member. Associated systems are also provided.
Owner:8 RIVERS CAPTTAL LLC
Method for forming a channel on the surface of a metal substrate
InactiveUS6921014B2Avoid stickingMolten spray coatingFixed microstructural devicesCopperCooling channel
A method for forming a channel within a coated, metal-based substrate is described. In one technique, a channel-forming material is first deposited on the substrate, followed by the deposition of a bonding agent, such as a braze. One or more coatings can then be applied over the substrate. In one embodiment, the channel is formed when the channel-forming material is subsequently removed. In another embodiment, the channel is formed due to the lack of adhesion between particular channel-forming materials and the overlying bonding agent. Related articles are also described, e.g., gas turbine components which include protective coatings and a pattern of cooling channels.
Owner:GENERAL ELECTRIC CO
Methods of combining a series of more efficient aircraft engines into a unit, or modular units
InactiveUS20100251692A1More thermal capacityReduce environmental pollutionContinuous jet plantsRocket engine plantsRamjetFree-piston engine
The present invention generally relates to units of engines and more particularly to units containing a unique combined-cycle (combustion-detonation) “counter-rotation, anti-gyration, gyroscopic,” turbine fan-jet / free-piston engine configuration for induced air supercharging and boosting the performance of novel Ramjet engines or Ramjet engine configurations by improving internal air-stream dynamics. These dynamics are the result of co-operative air stream intermixing through convergent, supercharge-attenuated, inducted, compressed, tuned, pre-heated ambient air. Achieved through the varying of the geometric structural form and the utilization of unique engines and air induction and propulsion conformations, aided with supplemental air, fuel, oxygen and optiomal water and electrolyte charging.
Owner:KINDE SR RONALD AUGUST
Aircraft propulsion system
InactiveUS7555893B2Highly compatible with environmentMagnetic circuitAircraft power plant componentsSpacecraft propulsionFuel cells
Owner:JAPAN AEROSPACE EXPLORATION AGENCY +1
Split shroud exhaust nozzle
A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat of the nozzle. An outer shroud surrounds the inner shroud and cooperates with the centerbody to define the exit area of the nozzle. Both shrouds are independently translatable to provide independent control of the nozzle throat area and the nozzle expansion ratio.
Owner:GENERAL ELECTRIC CO
Flexible power and thermal architectures using a common machine
ActiveUS20070266695A1Reduce riskImprove cooling effectCosmonautic vehiclesDomestic cooling apparatusStarter generatorElectricity
A power and cooling management system configured to flexibly couple various adaptive modules to an integrated power and cooling unit to suit any aircraft platform is provided. The integrated power and cooling unit has a compressor, a power turbine, a cooling turbine and an integral starter generator mounted to the shaft of the power and cooling turbine. The integrated power and cooling unit may be pneumatically and / or pneumatically coupled to an adaptive module that comprises an additional compressor and an additional turbine or electrically coupled to a fuel cell which provides the main power after entering the full operation mode. When the engine includes an integral starter generator mounted thereto, the integral starter generator of the integrated power and cooling unit is operative to receive electric power from the engine mounted generator. Alternatively, a motor / generator may be mounted to the shaft of the additional turbine of the adaptive module.
Owner:NORTHROP GRUMMAN SYST CORP
System for premixing air and fuel in a fuel nozzle
InactiveUS20120192565A1Turbine/propulsion fuel supply systemsContinuous combustion chamberTurbineAutomotive engineering
According to various embodiments, a system includes a turbine fuel nozzle. The turbine fuel nozzle includes a first fuel passage extending to a downstream mixing region, a first air passage extending from an exterior of the turbine fuel nozzle to the downstream mixing region, and a second fuel passage extending into the first air passage upstream of the downstream mixing region.
Owner:GENERAL ELECTRIC CO
Hollow turbine
InactiveUS20050005592A1General water supply conservationSeawater treatmentFree rotationCentre of rotation
A versatile turbine suitable for both hydraulic and pneumatic applications. The turbine's blades are affixed to the inner surface of a cylindrical shell which is free to rotate about an outside supporting structure. Rotational energy is transferred from the outer surface of the rotating cylindrical shell, usually by means of a gear; however, there may be applications better suited for a pulley means of transfer. The vacant central axis of rotation can be closed, by incorporating taller blades to achieve a larger surface area, resulting in greater efficiency, or open, by means of shorter blades forming a hole with the distal edges of the blades, to allow for passing fish and or debris to safely exit. The preferred embodiment further includes a means for electricity generation, water purification, and hydrogen production.
Owner:FIELDER WILLIAM SHERIDAN
Component Deployment System
A method and apparatus for deploying a group of panels. An apparatus comprises a group of panels in a folded configuration against a side of a spacecraft, a group of flexible members connected to the group of panels, and an interface system associated with the group of panels and the group of flexible members. The interface system is configured to move the group of panels from the folded configuration to a deployed configuration when the group of flexible members is extended from the spacecraft.
Owner:THE BOEING CO
Turbofan arrangement
A bypass turbofan engine comprises a first propulsion system and a second propulsion system. The first propulsion system comprises a first fan rotor, a core engine, a first low pressure turbine and a first fan shaft drivingly connecting the first turbine and the first fan rotor. The second propulsion system comprises a second fan shaft drivingly connecting to a second fan rotor and the first propulsion system and arranged so that the first and second shafts are not coaxial with one another.
Owner:ROLLS ROYCE PLC
System, Method, and Program Product for Targeting and Optimal Driving Force Distribution in Energy Recovery Systems
ActiveUS20080015839A1Efficient designGuaranteed uptimeLevel controlTemperatue controlEnergy recoveryTrade offs
A system, methods, and user-friendly program product to calculate global energy utility targets and define optimal driving force distribution for a process or cluster of processes under all possible process changes and streams specific minimum temperature approach values, simultaneously, and without enumeration, are provided. The program product can utilize stream-specific minimum temperature approach values ΔTmini, where the superscript i represents the specific hot stream, as the optimization parameters instead of the single global ΔTmin currently used, in addition to identifying the optimal operating conditions. The program product can define optimal process conditions and an optimal driving force distribution in heat recovery systems, and can produce an optimal Pareto-curve that shows the rigorous trade off between energy cost and capital cost for any energy recovery system.
Owner:SAUDI ARABIAN OIL CO
Bifold door thrust reverser
A fan thrust reverser includes an outer louver door joined to an inner blocker door by a drive link in a bifold configuration. The louver door is stowed closed in the outer skin of a fan nacelle outside the blocker door stowed closed in the inner skin of the nacelle. An actuator deploys open the louver and blocker doors, with the louver door extending radially outwardly and the blocker door extending radially inwardly for reversing fan exhaust flow during thrust reverse operation.
Owner:AERONAUTICAL CONCEPT OF EXHAUST
Thermal management system for an aircraft
ActiveUS7260926B2Minimizes air-to-liquid heat exchangersEngine fuctionsTurbine/propulsion fuel deliveryThermal management systemProcess engineering
A fuel based thermal management system includes a fuel stabilization system which permits the fuel to exceed the traditional coking temperatures. High temperature components are arranged along the fuel flow path such that even at the higher operating temperatures the fuel operates as a heat sink to transfer heat from high temperature components to the fuel. An optimal high temperature ester-based oil permits an oil-loop to exceed current oil temperature limits and achieve a high temperature to permit efficient rejection of heat to the fuel late in the fuel flow path.
Owner:RTX CORP
Compact swirl augmented afterburners for gas turbine engines
InactiveUS6895756B2Efficient flame propagationBurn quicklyTurbine/propulsion fuel supply systemsContinuous combustion chamberCombustion instabilityCombustion chamber
An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel / oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length. Inherent with this swirl afterburner concept are design compactness, light weight, lower cost, smooth and efficient combustion, high thrust output, wide flammability limits, continuous operation at stoichiometric fuel / oxidizer mixture ratios, no combustion instabilities, and relatively low pressure losses.
Owner:THE BOEING CO +1
Shape changing structure
In one preferred embodiment, a structure is provided that includes a body having a first wall and a second wall. At least one appending component extends from an end of the body and includes a first skin and second skin. The structure additionally includes at least one actuator positioned within a cavity formed in the body first wall and the appending component second skin. The actuator includes at least one shape memory alloy (SMA) wire adapted to constrict when activated to move the first skin of the appending component from a first position to a second position.
Owner:THE BOEING CO
Fuel nozzle
A fuel distributor is disclosed comprising a body having a unitary construction, a fuel conduit located within the body, a fuel flow path located within the body that is oriented in a circumferential direction around an axis and in flow communication with the fuel conduit, and at least one orifice located in the body in flow communication with the fuel flow path such that a fuel entering the fuel conduit exits through the orifice.
Owner:GENERAL ELECTRIC CO
Aircraft propulsion systems
ActiveUS7752834B2Reduce weightGas turbine type power plantsEfficient propulsion technologiesTurbineAmbient air
Disclosed are propulsion systems 30 providing reduced fuel burn, weight and cost. A single gas generator core 38 drives multiple bladed propulsion elements 36 with a power train 48. The core 38 has a forward compressor 56 and a rearward turbine 40 and rotates about a longitudinal core axis 62. The bladed propulsion elements 36 rotate about bladed propulsion element axes 78 that are not coaxial with the core axis 62. The bladed propulsion elements 36 discharge an ambient air stream 50 rearward as a bypass stream 52 portion and a core stream 54 portion. The core stream 54 portion is directed to the compressor 56. The propulsion systems 30 mount inside a fuselage 22 of an airframe 20 or they are suspended beneath a wing 24 via pylons 32.
Owner:RTX CORP
Extremely strain tolerant thermal protection coating and related method and apparatus thereof
InactiveUS20050266163A1Effective applicationHigh strain toleranceLiquid surface applicatorsMolten spray coatingPorosityHigh rate
Method and Apparatus for efficiently applying coating systems to a surface that can survive the thermal gradient that is encountered in high temperature, high heat flux environments such as a rocket engine or like using vapor or cluster deposition process such as a directed vapor deposition (DVD) approach. Method and Apparatus provides electron or other energetic beam technique to evaporate and deposit compositionally and morphologically controlled bond coats at high rate while providing a highly strain tolerant thermal barrier coating that has an improved porosity morphology between columnar grains.
Owner:UNIV OF VIRGINIA ALUMNI PATENTS FOUND
Microvalve and microthruster for satellites and methods of making and using the same
InactiveUS6068010ASmall sizeLight weightCosmonautic vehiclesEngine manufactureElectromagnetic valveVALVE PORT
A microvalve and microthruster are provided. Both include a housing with an interior in which an armature can travel and abut a valve seat to provide an electromagnetic valve. The armature acts as a valve body that is maintained in a or normally closed position by a permanent magnet, and is opened by interaction with a selectively activatable electromagnet. A microthruster is provided by fashioning the valve discharge as a nozzle, preferably of a material that is permanently and selectively magnetizable, so that the nozzle functions as the permanent magnet and which magnetism can be adjusted to assure proper opening and closing of the valve portion. The valve body is guided without any sliding fit mechanism and is suitable for controlling gas or liquid fluid flows.
Owner:MAROTTA SCI CONTROLS
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