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WO/2016/120555A1 |
The invention relates to a turbine engine combustion module (10), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: at least two combustion chambers (12A, 12B) arranged about an a...
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WO/2016/076693A1 |
The invention relates to mechanical engineering. A discrete-action rotary jet engine of a power unit has at least two combustion chambers. Combustion chamber covers are provided with automatic shutting devices which open the covers when ...
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WO/2016/061654A1 |
A combustor with pressure gain, intermittent combustion and substantially continuous discharge flow for use in gas turbine engines in general, in ramjet engines in general and in gas turbine engines for aircraft propulsion in particular,...
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WO/2016/018171A1 |
The invention relates to methods for the detonation combustion of fuel mixtures and to apparatuses for carrying out same, and can be used in aircraft engines and vehicle engines, in stationary power plants, and in the chemical industry. ...
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WO/2016/018172A1 |
The invention relates to methods for detonation burning of fuel mixtures and to apparatuses for carrying out same, and can be used in aircraft engines and vehicle engines, in stationary power-generating plants, and in the chemical indust...
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WO/2015/177409A1 |
An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is ...
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WO/2015/159956A1 |
An engine (10) that jets out combustion gas as a driving force is provided. This engine (10) has: a combustion chamber (11); a fuel supply passage (13) for supplying a fuel-air mixture into the combustion chamber (11); an igniter (42) fo...
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WO/2015/149448A1 |
Provided is a method and system for a semi-closed timing constant volume thermodynamic cycle in a prime motor. The cycle thereof comprises 6 processes: a multi-stage compression interstage cooling process, a counter-flow heat exchange pr...
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WO/2015/104458A1 |
An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is ...
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WO/2015/063558A1 |
Endothermic rotary engine comprising a fixed part comprising a combustion chamber (21) provided with an intake conduit (22) for combusted gas and an exhaust conduit (30) selectively communicating with a cylindrical rotor (11) comprising ...
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WO/2014/178731A2 |
A rotor assembly for an engine, comprising: a rotor, supported on bearings for axial rotation, a rotor portion forming a compression passage extending outwards from the axis, gases entering the rotor through inlets at the axis and flowin...
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WO/2014/163731A1 |
An engine for propelling vehicles on land, in the air and on the water. The engine is able to extract energy from a same fuel twice, including extracting a first amount of energy with a gas turbine and a second amount of energy by burnin...
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WO/2014/114980A2 |
A detonation engine can detonate a mixture of fuel and oxidizer within a cylindrical detonation region to produce work. The detonation engine can have a first and a second inlet having ends fluidly connected from tanks to the detonation ...
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WO/2014/057227A1 |
The present invention concerns a heat engine for driving a drive shaft, comprising at least a gas generator and a turbine (6), the gas generator supplying the turbine with engine gas and the turbine driving the engine shaft in rotation. ...
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WO/2014/000072A1 |
The present invention relates to an engine operating in accordance with Carnot's thermodynamic cycle, which, in accordance with the general features thereof, has, as basic principle, the conversion of heat energy into motive force in a m...
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WO/2013/182301A1 |
The aim of the invention is to increase the injection speed of the injection valves in an internal combustion engine by using a single injection valve having a particular configuration for carrying out multiple fuel injections and combus...
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WO/2013/089593A1 |
The turbo-rotary engine comprises a ventilated or hermetic housing within which a rotor is mounted on a shaft. The rotor is provided with channels or is comprised of a series of pipes which are mounted around the shaft to form channel...
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WO/2013/086625A1 |
This invention relates to devices for discharging high pressure exhaust, and in particular to pulse detonation engines. More specifically, the invention describes a rotary pulse detonation engine having a rotary valve system. The rotary ...
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WO/2013/083271A1 |
The invention relates to a method for the thermal ignition of a pulsed- or cyclic-combustion engine, comprising at least a stage of taking in a premixed fresh gas (G2) at an injection inlet (Ci) of a combustion chamber (CC), a stage of b...
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WO/2013/040679A1 |
The present disclosure introduces a rotor assembly having a concentric arrangement comprising a rotating turbine portion, a cooling channel and an annular reinforcement wall. The concentric arrangement is configured to rotate around a co...
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WO/2013/035367A1 |
[Problem] To provide a working gas-generating device that supplies working gas to a power unit having working gas as the motive power source. [Solution] This working gas-generating device for supplying working gas to a device that has wo...
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WO/2012/145836A1 |
A method of controlling operation of a pressure gain combustor comprises: determining a fuel injector duty cycle and a combustion frequency that meets a target load set point and a target fill fraction of the combustor; determining a fue...
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WO/2012/134325A1 |
The present application provides a power augmentation system with dynamics damping for a gas turbine engine. The power augmentation system may include a transition piece of a combustor and a steam manifold positioned about the transition...
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WO/2012/113523A1 |
According to the invention, the jet engine (1) includes at least one vaporization duct (5) arranged on the outer wall (2a) of a combustion chamber of the jet engine (1) and extending over the entire length thereof between an ejection val...
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WO/2012/092285A1 |
One embodiment of the present invention is a unique pulse detonation combustion system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for p...
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WO/2012/067885A1 |
A pulse detonation combustor including a plurality of nozzles engaged with one another via mating surfaces to support a gas discharge annulus in a circumferential direction. The pulse detonation combustor also incluidng multiple pulse de...
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WO/2011/127635A1 |
Disclosed is a fully-steam-driven internal combustion engine added with a motor, which includes a mechanical power system, a combustion system and a gas supply system. The mechanical power system includes a turbine and a turbine shaft (2...
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WO/2011/011963A1 |
A full steam-driven internal combustion engine includes a mechanical power system, a combustion system and an air supply system. The mechanical power system includes a turbine (1) and a turbine shaft (2). The combustion system includes a...
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WO/2011/006484A2 |
The invention relates to a jet engine for driving a flying object, comprising an inlet (E) for air (10) to be compressed, a turbocompressor (4) for compressing the inflowing air (10), a combustion chamber (3) for combusting the fuel (T) ...
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WO/2010/136402A2 |
An internal combustion engine for converting energy released during the combustion of a fuel, in particular an H2-O2 mixture, into mechanical work, comprising at least one drive shaft 10, which is connected to at least one chamber compon...
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WO/2010/104415A1 |
The gas turbine engine comprises a rotor with combustion chambers and a turbine, which are arranged in a housing and are rigidly fastened to a shaft. The combustion chambers are arranged around the periphery of the rotor. The shaft of th...
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WO/2010/086091A1 |
The invention relates to a jet engine (1), in particular an aircraft jet engine, including at least one combustion chamber (3). The combustion chamber (3) is connected to at least one compressed gas intake (4) and to at least one burnt g...
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WO/2010/056520A1 |
An engine (100) contains a compressor stage (101), a pulse detonation combustion stage (105) and a turbine stage (103). The pulse detonation combustion stage contains at least one pulse detonation combustor (109) which has an inlet porti...
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WO/2010/022416A1 |
The invention relates to a combustion turbine (1) in which combustion is intermittent and which comprises at least one combustion chamber (3) that has intake valves (2) and an ignition device (18). The at least one combustion chamber (3)...
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WO/2010/024705A1 |
The invention relates to heat power engineering. The inventive power plant comprises a device (2) for producing a compressed gas mixture for a gas turbine which is connected to an electric generator (3). Said device (2) for producing a c...
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WO/2009/154511A1 |
The inventive prechamber rotary internal combustion engine is directed at solving the problem of the fragility of a gap seal between the rotor and stator of rotary internal combustion engines, the problem being solved by non-using any se...
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WO/2009/133304A2 |
According to the invention, the said engine (I), which comprises at least one flame tube (2) with a mobile transverse end wall (18), comprises an external envelope (3) around the said flame tube (2), which defines a peripheral annular sp...
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WO/2009/113114A1 |
A controlled sequence of explosions of calculated amounts of exploding materials inside an explosion chamber, efficiently transfers a quantity of motion between a massive hammer obstructing the explosion chamber and a lighter dancer plac...
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WO/2009/067872A1 |
A high-power completely-steam-driven type gas engine includes two systems, i.e. a combustion system and a mechanical power system, the mechanical power system includes a power turbine (2) and a gas turbine (3) fixed on a turbine shaft (1...
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WO/2009/019718A1 |
A rotary Jet Engine consisting of a rotor (1) axially mounted on a main-shaft (2), on the periphery of which rotor (1) are situated seal-able combustion chambers (4), equipped with inlet valve (26), ignition device (27) and a valve (25) ...
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WO/2009/010796A2 |
An engine comprising a first section having a first face and a second section having a second face, the first and second faces being opposed to one another and arranged for relative rotation, the first face comprising at least one chambe...
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WO/2008/102160A2 |
An auxillary power generation apparatus for powering an ancillary electrical load comprises an apparatus comprising a combustor arranged for disposal in an exhaust conduit of a reciprocating engine, a compressor arranged in fluid communi...
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WO/2008/088225A1 |
A rotating device for producing pressure from a process substance by expansion, which device includes a U-channel structure (120) rotatably arranged on an axis (121,122) including an expansion point (105) arranged at the periphery of the...
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WO/2008/065078A2 |
The invention relates to an energy conversion system which comprises at least one compressor (14) and a turbine (16) having a turbine shaft which turbine is connected to the compressor by means of compressed gas. The aim of the invention...
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WO/2008/057826A2 |
A rotary engine includes a rotor having one or more combustion chambers connected to an exhaust passageway extending radially outward from the chamber to an exhaust port adjacent a peripheral edge of the rotor. The exhaust gas is expelle...
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WO/2008/037075A1 |
A rotary internal combustion engine, includes a housing, a rotating plate assembly and a stationary plate assembly. The rotating plate assembly has a plurality of vanes disposed between an inflow passage and an outflow passage. The stati...
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WO/2008/029432A2 |
Two identical impact turbines with intermittent combustion are arranged in parallel in a common.housing. Air is compressed by intake fans due to centrifugal compression, fuel is injected and ignition is assured with spark plugs. Exhauste...
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WO/2007/099768A1 |
[PROBLEMS] To provide a detonator in which the distance required from ignition to detonation can be shortened by shortening the time required from ignition to detonation, and to provide a pulse combustor equipped with that detonator and ...
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WO/2007/086729A1 |
A pneumatic operating driving device, comprising at least one rotor (1) being connected to a rotatable supported shaft (3) and being brought into rotation by means of air. Near the circumference of said rotor (1), at least one cylinder (...
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WO/2007/086728A1 |
A combustion engine comprising a mainly cylindrical housing (5) provided with means for supplying an air- fuel mixture to a number of combustion chambers (3) , provided on the outside of said housing, with a shaft (2) rotating in said ho...
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