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Matches 1 - 50 out of 368

Document Document Title
WO/2017/048455A1
A turbine engine combustion system is disclosed including a fuel nozzle assembly having three independently controlled stages of water injection. A first stage includes water mixed with a gaseous fuel upon inlet to the nozzle, where the ...  
WO/2017/045014A1
An internal combustion engine wherein a thermo potential heat flow in combustion is maximized by providing a feedback of an optimized amount of thermo potential heat flow that is modulated in the exhaust media, into the air intake, and a...  
WO/2016/200460A2
A pulse combustor system for operating pulse combustors in anti-phase. The pulse combustor system includes two pulse combustors connected at their combustion chambers by a connecting tube. Each of the pulse combustors has a fundamental o...  
WO/2016/198792A1
The invention mainly relates to a turbine engine combustion chamber module (4) comprising at least one constant-volume combustion chamber (7). Said module is characterized in that it also comprises, upstream of said at least one constant...  
WO/2016/181307A1
The invention relates to a turbine, in particular a combustion gas turbine, which drives a high-speed generator for generating electricity, said turbine having a high efficiency. The turbine has at least one combustion chamber (6), which...  
WO/2016/145931A1
An internal combustion engine comprises a compressor, a combustion chamber (8), pipelines, a spray pipe (9), an oiler (23), a driving device, a first safety device, a second safety device, an electric ignition device (22), a rack, a firs...  
WO/2016/132055A1
The invention relates to a constant-volume combustion system (3) for a turbine engine. Said system includes: - a plurality of combustion chambers (11-14) regularly distributed around a longitudinal axis (AX); - a toroidal manifold (7) in...  
WO/2016/131149A1
A compound engine assembly having an engine core including at least one internal combustion engine in driving engagement with an engine shaft, a compressor having an outlet in fluid communication with an inlet of the engine core and incl...  
WO/2016/120551A1
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: a plurality of combustion chambers (12) distributed angularly i...  
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...  
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 ...  
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,...  
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. ...  
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...  
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 ...  
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...  
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...  
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 ...  
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 ...  
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...  
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...  
WO/2014/114980A3
A detonation engine (100) can detonate a mixture of fuel and oxidizer within a cylindrical detonation region (205) to produce work. The detonation engine has a first and a second inlet (135, 140) having ends fluidly connected from tanks ...  
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 ...  
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. ...  
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...  
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...  
WO/2013/184042A3
The multistage turbine comprises a housing, within which a working wheel with a bladed impeller is installed on a shaft. At the input opening end of the inter-blade channels, the impeller is adjacent to a distributor, with a gap therebet...  
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...  
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 ...  
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...  
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...  
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...  
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...  
WO/2012/142485A3
One embodiment of the present invention is a gas turbine engine. Another embodiment is a unique combustion system. Another embodiment is a unique engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and com...  
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...  
WO/2012/116285A3
A wave apparatus (21) comprising a wave rotor(61) further comprising a plurality of channels (95) each being elongated from an internal end (97) to an external end (99), each of the channels (95) having a constricted width dimension clos...  
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...  
WO/2012/097997A3
The invention relates to a gas turbine exhaust cone comprising an outer wall (29) that has a plurality of cavities, a honeycomb structure layer (30) that is arranged on and extends along the inner face of the outer wall (29), an inner wa...  
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...  
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...  
WO/2011/152912A3
A supersonic combustor as a component of a rocket nozzle offers improved utilization of available chemical energy that may be released from combustion gasses flowing through the rocket nozzle. A subsonic combustor compresses and sub-soni...  
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...  
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...  
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) ...  
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...  
WO/2010/136402A3
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...  
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...  
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...  
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...  
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)...  

Matches 1 - 50 out of 368