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153results about "Continuous jet plants" patented technology
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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
Rotary ramjet turbo-generator
ActiveUS20070056290A1MiniaturizationHigh thermal efficiencyEngine manufactureEfficient propulsion technologiesBrayton cycleElectricity
A Brayton-cycle rotary ramjet engine (10) operated within the confines of a helically elongated pass-through duct formed between a preferably stationary radially outward surface (14) and an outer rotating flow channel (36). The flow channel (36) is contoured between its inlet (34) and outlet (38) to include a supersonic diffuser (40), a combustor (42) and an expansion nozzle (44). Gaseous fuel, or liquid fuel atomized by a fuel slinger (58) within a housing (46), or solid fuel in the form of fine particulates, is inter-mixed with an oxidizer prior to being directed to the flow channel inlets (34). The air and fuel are combusted in the flow channels (36) and exhausted through the rear of the housing (46). A generator (22) can be coupled to a power shaft (18) to convert net shaft power into electricity. Preferably, the rotor (24) and stator (12) are fabricated from a ceramic or other high-temperature material so that combustor exit temperatures (T3) can be operated at highly efficient levels.
Owner:RGT UNIV OF MICHIGAN
Gas turbine engine lockout reduction
ActiveUS8776530B2Shorten the overall cycleShorten the timeLeakage preventionGas turbine plantsCombustorTurbine
A method is provided of reducing lockout time of a gas turbine engine which includes: an inlet, a compressor, a combustor, a turbine, and an exhaust duct, where the compressor and the turbine are carried on a turbomachinery rotor and each include an array of blades mounted for rotation inside a casing of the engine. The method includes: operating the engine at a first power output; shutting down operation of the engine without substantially reducing the power output beforehand, wherein thermomechanical changes occur in the engine subsequent to shutdown that tend to reduce a radial clearance between at least one of the blades and the casing; and subsequent to shutting down the engine, (1) heating the casing and / or (2) pumping an airflow of ambient air into the inlet and through the casing, past the rotor, and out the exhaust duct, so as to reverse at least partially the thermomechanical changes.
Owner:GENERAL ELECTRIC CO
Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance
InactiveUS6907724B2Shorten the lengthFast atomizationContinuous combustion chamberJet type power plantsRamjetFlame propagation
A combined-cycle engine having at least one core engine and at least one ramjet engine. The ramjet 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 an inner central recirculation zone, both of which 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, which accelerate flame propagation throughout the core flowfield. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L / D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits, high combustion efficiency and high specific thrust performance.
Owner:UNITED TECH CORP +1
Single-stage hypersonic vehicle featuring advanced swirl combustion
InactiveUS20080283677A1Reduce complexityShorten the lengthAircraft navigation controlPower plant exhaust arrangementsRamjetLow speed
A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet / rocket engine depending requirements. Benefits of the swirl generator design include its ability to rapidly and efficiently atomize, vaporize, mix and burn the fuel and oxidizer for the low speed propulsion system, significantly reduce length, weight, cooling requirements and complexity for both propulsion systems, while maintaining high propulsion performance and reducing propulsion and launch costs.
Owner:UNITED TECH CORP
Low shock strength inlet
ActiveUS20090107557A1Power plant exhaust arrangementsAircraft power plant componentsNacelleUltimate tensile strength
Embodiments of the invention relate to a supersonic inlet having a cowl lip configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.
Owner:GULFSTREAM AEROSPACE CORP
Single-stage hypersonic vehicle featuring advanced swirl combustion
InactiveUS7762077B2Reduce complexityShorten the lengthPower plant exhaust arrangementsEfficient propulsion technologiesRamjetLow speed
A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet / rocket engine depending requirements. Benefits of the swirl generator design include its ability to rapidly and efficiently atomize, vaporize, mix and burn the fuel and oxidizer for the low speed propulsion system, significantly reduce length, weight, cooling requirements and complexity for both propulsion systems, while maintaining high propulsion performance and reducing propulsion and launch costs.
Owner:UNITED TECH CORP
Isentropic compression inlet for supersonic aircraft
ActiveUS20080271787A1Improve performanceInherent shock stabilityCosmonautic vehiclesEngine manufactureEngineeringAirplane
Embodiments of the invention relate to a supersonic inlet employing relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Using supersonic inlets in accordance with the invention also demonstrated reductions in peak sonic boom overpressure while maintaining performance.
Owner:GULFSTREAM AEROSPACE CORP
Propulsion from combustion of solid propellant pellet-projectiles
InactiveUS7194852B1High volume loadAbility to throttleGas turbine plantsContinuous jet plantsRamjetCombustion chamber
Owner:KRISHNAN VINU B
Pulse detonation engine and valve
InactiveUS20050183413A1Accurate timingIncrease air densityPulsating combustionTurbine/propulsion fuel heatingCombustion chamberCombustor
Pressure and density of a gaseous mixture are increased in the process of introducing the gaseous mixture into the combustor of an air-breathing pulse detonation engine employing atmospheric oxygen as an oxidizer. The exit valve 20 able to be opened and closed is provided at the outlet of the combustor 15, an air cooler 12 is provided in the exit of the intake, and density is increased by exchange of heat of the air received at the intake with a coolant in the air cooler 12. Furthermore, by closing the exit valve 20 provided in the outlet of the combustor during the process of loading the gaseous mixture, transition to the detonation process is possible without expansion of the high-pressure high density air obtained by ram-compression at the intake.
Owner:JAPAN AEROSPACE EXPLORATION AGENCY
Rotary ramjet engine
An engine for providing rotary power about an output shaft with a high power-to-weight ratio includes a plurality of flow guiding blades mounted on the inner surface of an annular thruster base. The flow guiding blades cooperate with the peripheral surface of a rotor for forming a plurality of ramjet-like thrusters. The configuration of the flow guiding blades allows for optimization of the number of thrusters. The centrifugal forces generated by the rotating components is compensated by an annular reinforcement wall made with high strength materials allowing for downsizing of the rotor and associated components.
Owner:SCOPRA SCI & GENIE SEC
Top cycle power generation with high radiant and emissivity exhaust
The present invention generally relates to power generation methods and secondary processes requiring high radiant and emissivity homogeneous combustion to maximize production output. In one embodiment, the present invention relates to a top cycle power generator with combustion exhaust modified to have radiant flux in excess of 500 kW per square meter and emissivity greater than 0.90, and supercritical CO2 power generating cycle to maximize exergy efficiency.
Owner:GURIN MICHAEL
Propulsion from combustion of solid propellant pellet-projectiles
InactiveUS6968676B1High volume loadAbility to throttleGas turbine plantsContinuous jet plantsCombustion chamberAuxiliary power unit
Propulsion from combustion of solid propellant pellet-projectiles for providing a useful propulsion that has the advantages of both solid and liquid propulsion engines, and also can make use of either solid chemical propellants or fissionable nuclear material as the fuel. Preferred methods and systems can include a storage chamber for storing solid propellant pellets, a feeding system having a pellet feeding channel and a pellet feeding mechanism connected to the storage chamber and to a gun assembly, which is positioned along a longitudinal axis to eject the pellets at a certain velocity. A triggering system positioned between gun assembly and thrust chamber can initiate the propellant pellet-projectile, and a thrust chamber having a combustion chamber for combustion of propellant pellet-projectile with an exhaust nozzle. Additionally, an auxiliary power system can be used to power the components and various electrical and electronic systems that may be present in the invention for controlling the engine components. The gun assembly may include an ejector mechanism for ejecting the propellant pellets through at least one barrel. The triggering system can produce a medium creating an ambience for the initiation of propellant pellet-projectiles. Methods and systems can be used for space and rocket crafts, turbojets and ramjets.
Owner:KRISHNAN VINU B
Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance
InactiveUS20050081508A1Rapid fuel atomizationVaporization fastContinuous combustion chamberJet type power plantsRamjetFlame propagation
A combined-cycle engine having at least one core engine and at least one ramjet engine. The ramjet 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 an inner central recirculation zone, both of which 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, which accelerate flame propagation throughout the core flowfield. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L / D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits, high combustion efficiency and high specific thrust performance.
Owner:UNITED TECH CORP +1
Multi-mode pulsed detonation propulsion system
InactiveUS6857261B2Improve performanceReduce weightCosmonautic vehiclesCosmonautic propulsion system apparatusAviationDetonation
A multi-mode propulsion system for potential application to hypersonic and aerospace planes. The system can employ various propulsion modes at various points in time, with the propulsion system employed at a given point in time being selected according to the velocity of the inlet airflow. In one embodiment, the propulsion system of the present invention has an ejector-augmented pulsed detonation rocket propulsion mode, a pulsed normal detonation wave engine mode, a steady oblique detonation wave engine mode, and a pure pulsed detonation rocket mode.
Owner:BOARD OF RGT THE UNIV OF TEXAS SYST
Core burning for scramjet engines
InactiveUS20080092519A1Reducing combustor heat loadReduces combustor heat loadCosmonautic vehiclesCosmonautic propulsion system apparatusRamjetCombustion chamber
A pilot for a scramjet provides a flame front whose arrival at the wall of the scramjet combustor is delayed thereby reducing combustor heat load. By combining in-stream injection of fuel with an interior pilot and a lean (fuel-poor) outer annulus, the bulk of combustion is confined to the scramjet combustor center. This concept, referred to as “core-burning,” further reduces combustor heat load. One such pilot is for a two dimensional scramjet effective to propel a vehicle. This pilot includes a plurality of spaced apart struts separated by ducts and a strut pilot contained within each strut. A second such pilot is for an axisymmetric scramjet engine has, in sequence and in fluid communication, an air intake, an open bore scramjet isolator and a scramjet combustor. This centerbody pilot pod includes a pilot isolator disposed between the air intake and a pilot diffuser, the pilot diffuser disposed between the pilot isolator and a pilot with the pilot disposed between the pilot diffuser and a pilot combustor. The pilot pod is in axis symmetry around a central axis of the scramjet isolator and supported by a plurality of struts extending from an inner wall of the open bore to an outer surface of the centerbody pilot pod.
Owner:AEROJET ROCKETDYNE INC
System for directing air flow to a plurality of plena
A system for directing air flow to separate plena of a compartment that is defined at least by a compartment wall includes a NACA scoop, and a Pitot scoop. The NACA scoop is formed in the compartment wall, and includes two side walls, a bottom wall, and an entrance lip that is defined by the compartment wall and is spaced apart from the bottom wall to form a NACA scoop air inlet. The Pitot scoop is longitudinally aligned with the NACA scoop, includes a Pitot scoop air inlet, a Pitot scoop air outlet, and a Pitot scoop flow passage.
Owner:HONEYWELL INT INC
Microjet creation and control of shock waves
InactiveUS20090288711A1Increase flow rateCosmonautic vehiclesCombustion enginesShock waveEngine efficiency
A method of using one or more microjets to create and / or control oblique shock waves. The introduction of microjet flow into a supersonic stream creates an oblique shock wave. This wave can be strengthened—by increasing microjet flow rate or the use of many microjets in an array—in order to form an oblique shock. Such an oblique shock can be used to decelerate flow in a jet aircraft engine inlet in a controlled fashion, thus increasing pressure recovery and engine efficiency while reducing flow instability. Adjusting the pressure ratio across the microjet actually alters the angle of the oblique shock. Thus, the use of microjets allows decelerating shock waves in an inlet engine to be properly positioned and controlled. Microjet arrays can also be used to ameliorate shock waves created by external aircraft surfaces, such as sensor pods and weapons. Microjets placed forward of any external protuberance can convert a single substantial shock wave into a series of much milder waves which will not produce unwanted external effects, such as strong sonic booms.
Owner:FLORIDA STATE UNIV RES FOUND INC
Rotary ramjet turbo-generator
ActiveUS7685824B2MiniaturizationHigh thermal efficiencyEngine manufactureEfficient propulsion technologiesBrayton cycleElectricity
A Brayton-cycle rotary ramjet engine (10) operated within the confines of a helically elongated pass-through duct formed between a preferably stationary radially outward surface (14) and an outer rotating flow channel (36). The flow channel (36) is contoured between its inlet (34) and outlet (38) to include a supersonic diffuser (40), a combustor (42) and an expansion nozzle (44). Gaseous fuel, or liquid fuel atomized by a fuel slinger (58) within a housing (46), or solid fuel in the form of fine particulates, is inter-mixed with an oxidizer prior to being directed to the flow channel inlets (34). The air and fuel are combusted in the flow channels (36) and exhausted through the rear of the housing (46). A generator (22) can be coupled to a power shaft (18) to convert net shaft power into electricity. Preferably, the rotor (24) and stator (12) are fabricated from a ceramic or other high-temperature material so that combustor exit temperatures (T3) can be operated at highly efficient levels.
Owner:RGT UNIV OF MICHIGAN
Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance
InactiveUS6968695B2Flame stabilizationEasy to operateContinuous combustion chamberEfficient propulsion technologiesRamjetFlame propagation
A ramjet powered device 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 an inner central recirculation zone, both of which 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 and stabilizes flame propagation and accelerates combustion throughout the entire combustor. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L / D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits and high combustion efficiency and thrust performance.
Owner:THE BOEING CO
Hypersonic inlet systems and methods
ActiveUS8292217B2Adequate pressure recoverySufficient operabilityGeometric CADGas turbine plantsLeading edgeEngineering
Hypersonic inlet systems and methods are disclosed. In one embodiment, an inlet for an airbreathing propulsion system includes an inboard surface at least partially shaped to conform to a plurality of streamline-traces of a design flowfield approaching an aperture, an outboard surface spaced apart from the inboard surface, an upper surface extending between the inboard and outboard surfaces, and a lower surface extending between the inboard and outboard surfaces, wherein leading edges of the inboard, outboard, upper, and lower surfaces cooperatively define the aperture.
Owner:ORBITAL ATK INC +1
Pulse detonation system
In one embodiment, a pulse detonation system includes a pulse detonation tube including a base tube and a thermally protective layer disposed adjacent to an inner surface of the base tube. The thermally protective layer is configured to limit temperature fluctuations at the inner surface of the base tube to less than approximately 20 degrees Celsius during operation of the pulse detonation system, and the thermally protective layer does not comprise a ceramic coating.
Owner:GENERAL ELECTRIC CO
Rocket based combined cycle propulsion unit having external rocket thrusters
The present disclosure generally pertains to rocket based combined cycle (RBCC) propulsion units. In one exemplary embodiment, at least one rocket thruster is integrated with a jet engine but is external to the flow path of the jet engine, forming an altitude compensating plug nozzle. Since the rocket thruster is external to such flow path, the rocket flow from the rocket thruster interacts with the jet flow from the jet engine aft of the nozzle of the jet engine. Such interaction occurs without a significant performance penalty in the operation of the jet engine. In fact, it is possible that the interaction of the rocket flow with the jet flow may actually improve the efficiency of the jet engine under some conditions. Moreover, having the rocket thrusters positioned external to the flow path of the jet engine helps to avoid many of the problems plaguing conventional RBCC propulsion units.
Owner:UNIVERSITY OF ALABAMA
Ejector based engines
An injector-based engine, as exemplified in the injector ramjet (1), is an engine with an inlet (2), mixer (4), diffuser (5), combustor (6) and outlet ) conventionally reinforced ramjet element propulsion duct, allowing operation in the zero to hypersonic range. At the upstream end of the mixer (4), an injector assembly (50) is mounted in the fluid flow channel to form an injector (3). The injector assembly (50) has one or more injector rings with alternately offset injector exhaust nozzles (53) or slots to direct fluid towards the engine inner wall (14) or the engine longitudinal axis (9), respectively. ), thereby improving fluid mixing for shorter mixing zones. The supply of fluid to the injector exhaust nozzle (53) can be accomplished by flow pumps and other elements.
Owner:太空通道有限公司
Multi-height ramp injector scramjet combustor
InactiveUS20080060361A1Optimize fuel distributionEfficient propulsion technologiesContinuous jet plantsCombustion chamberScramjet engine
A multi-height ramp injection system, for use in a supersonic propulsion system, comprises a plurality of multi-height ramp injectors for variably introducing a fuel into an airflow in a combustor. In one embodiment of the invention, the multi-height ramp injectors comprise a plurality of tall injectors for fueling an inner portion of the airflow, and a plurality of short injectors for fueling an outer portion of the airflow.
Owner:ROCKETDYNE
Dual-mode combustor
InactiveUS8484980B1Reduce the Mach numberContinuous combustion chamberPower plant arrangements/mountingRamjetCombustion chamber
A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.
Owner:NASA
Valve actuator and throttle valve assembly employing the same
InactiveUS20090261279A1Impede fluid flowOperating means/releasing devices for valvesServomotor componentsValve actuatorEngineering
Embodiments of a valve actuator are provided for adjusting the position of a main valve element in relation to the pressure of a fluid supplied by a supply duct. The valve actuator includes a housing, a control pressure valve disposed in the housing, and a piston slidably disposed in the housing and mechanically coupled to the main valve element. The housing has a control pressure chamber therein, which is configured to be fluidly coupled to the supply duct. The control pressure valve is configured to substantially impede fluid flow into the control pressure chamber until the fluid pressure within the supply duct surpasses a minimum actuation pressure. The piston normally resides in a first position and is configured to move toward a second position as the pressure within the control pressure chamber increases.
Owner:HONEYWELL INT INC
Thrust generator for a propulsion system
InactiveCN101327844AImprove propulsion efficiencyJet type power plantsEfficient propulsion technologiesGas generatorExhaust gas
A thrust generator for thrust system is provided. The thrust generator includes an air inlet configured to introduce air within the thrust generator and a plenum configured to receive exhaust gas from a gas generator and to provide the exhaust gas over a Coanda profile, wherein the Coanda profile is configured to facilitate attachment of the exhaust gas to the profile to form a boundary layer and to entrain incoming air from the air inlet to generate thrust.
Owner:GENERAL ELECTRIC CO
Cooling structure for outer surface of a gas turbine case
A gas turbine case is provided including an outer case surface, and a channel portion formed as a recessed area extending radially inwardly into the outer case surface. The channel portion extends about a circumference of the case. An outer flow jacket is attached to the outer case surface and extends over the channel portion to define an enclosed cooling passage along the outer case surface. At least one inlet passage and at least one outlet passage are provided in fluid communication with the enclosed cooling passage to convey air to and from the cooling passage.
Owner:SIEMENS ENERGY INC
Combined engine for single-stage spacecraft
InactiveUS20050016157A1Increase widthEasy to changeCosmonautic propulsion system apparatusSpace shuttlesAir compressionCombustion chamber
A novel combined engine for a single-stage spacecraft is provided that combines a air-breathing engine utilizing oxygen in the atmosphere as oxidizer and rocket engines for obtaining thrust outside the atmosphere and that does not require a portion whose shape is variable in accordance with the flight speed. Rocket engines 15 are provided on struts 12 that form air introduction channels 10 in the air intake section 4. The rocket jets 18 from the rocket engines 15 control the flow of the airflows 16 introduced into the combustion chamber 20 in accordance with the flight speed. When the spacecraft 1 is stationary or in subsonic flight, the rocket jets 18 promote air intake into the combustion chamber 20 by lowering of static pressure due to expansion (ejector effect). In the subsonic flight condition, it performs the role of air compression, mixing with incoming air, fuel injection and ignition and during supersonic / ultra-supersonic flight it performs the role of a variable diffuser.
Owner:JAPAN AEROSPACE EXPLORATION AGENCY
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