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Matches 1 - 50 out of 8,103

Document Document Title
WO/2017/137404A1
The invention relates to a method for operating a heat engine, which permits a reliable operation of the heat engine, in particular under variable boundary conditions, wherein the method comprises the following steps: supplying gas conta...  
WO/2017/129518A1
A method for operating start-up of a compressor train is disclosed. The train comprises a driver machine (30) and at least a centrifugal compressor (1) drivingly coupled to the driver machine. The centrifugal compressor (1) in turn compr...  
WO/2017/129917A1
The invention relates to an assymetrical electronic control system (100) for a gas turbine (50), which is designed to control a set of functions associated with logic input data (60) or data from sensors and associated with output data (...  
WO/2017/126383A1
A gas turbine cooling system (50) is provided with a cooling air line (51) for guiding compressed air compressed in an air compressor (10) to high-temperature components, a cooler (63) for cooling the compressed air in the cooling air li...  
WO/2017/126180A1
In the present invention, a first controller of a turbine generates a first lift command that instructs a valve opening degree on the basis of a governor command that indicates a valve opening degree of a flow rate control valve. The fir...  
WO/2017/125663A1
The invention relates to an aircraft turbomachine fan module (1) comprising: a fan (2), a low pressure compressor (3), inlet guide vanes (18) located upstream of the low pressure compressor and downstream of the fan (2), and a device for...  
WO/2017/123686A1
A gas turbine system includes a gas turbine engine, an exhaust processing system disposed downstream of and fluidly coupled to the gas turbine engine, and an air delivery system that may supply treated air to the gas turbine engine and t...  
WO/2017/108250A1
The invention relates to a control device and a method for operating a gas turbine. The method comprises the following steps: determining the creep rate of at least one component of the gas turbine for a predetermined time interval, eval...  
WO/2017/110448A1
A gas turbine cooling system (50) is provided with: a cooling air line (51) which guides air compressed by an air compressor (10) to a high-temperature component of a gas turbine (1); a cooler (64) which cools the compressed air; a flow ...  
WO/2017/108253A1
The invention relates to a power plant (1), comprising a compressor (2) for compressing combustion air (3), a combustion device (4), in which compressed combustion air (3) and a fuel (5) burn with each other, and a turbine (6), in which ...  
WO/2017/109374A1
The invention relates to a turbomachine comprising an inter-flow compartment (110) extending radially between first and second intermediate walls, gas bypass ducts (102) passing through the second intermediate wall and communicating with...  
WO/2017/105204A1
The present invention relates to a device having a rotary mechanism, which provides fuel propulsion and has a monolithic structure designed to reduce leakage, maintain unvarying fuel flow and pressure, and improve the efficiency of turbi...  
WO/2017/105182A1
The invention relates to a rotary fuel delivery system with a monolithic structure, for aircraft turbines, which comprises: a pump body in which all of the components are assembled to establish and control the pressure and the displaceme...  
WO/2017/104094A1
A compressor rotor comprising a structure for bleeding air, which flows through a compression passage in an axial flow compressor, into an internal passage on the inner peripheral side of the compression passage is provided with rotor bl...  
WO/2017/098782A1
This fuel cell system is provided with: a fuel cell; an electric compressor that supplies a cathode gas to the fuel cell; a cathode exhaust gas passage through which flows a cathode exhaust gas discharged from the fuel cell; a turbine pr...  
WO/2017/098147A1
The invention relates to an assembly comprising a compressor (38) for a turbine engine (1), and a discharge system (50) comprising: a supply duct (8), one end (3) of which is connected to the compressor (38), the duct (8) being configure...  
WO/2017/096144A1
The present invention discloses a novel modular system and methods of operating an increased air supply to a gas turbine engine such that the upon supplying a source of external air to the system, a bias is added to the exhaust temperatu...  
WO/2017/095569A1
A turbomachine complex includes at least one motor-generator, at least one power source coupled to the at least one motor-generator, and at least one load dissipative device coupled to the at least one motor-generator. The turbomachine c...  
WO/2017/090446A1
This method includes: carrying out refurbishment to reduce the amount of cooling air supplied to a turbine, and to replace at least some components provided in the turbine with components corresponding to the amount of cooling air suppli...  
WO/2017/090709A1
A gas turbine (1) is provided with a compressor (10), a turbine (30), a bleed line (61), and a component introducing line (66). The bleed line (61) extracts, as bleed air, compressed air from an intermediate compression stage (19a) of th...  
WO/2017/077850A1
This structure for bleeding a chamber (11) that receives compressed gas from a compressor of a gas turbine engine (GE) and supplies the compressed gas to a combustor is provided with: a turbine casing (25) which covers the outer peripher...  
WO/2017/078821A2
An exhaust cooling arrangement includes a first duct having a first inlet and a first outlet, a fairing positioned radially outwardly of the first duct defining an annular space between the fairing and the first duct, and a second duct h...  
WO/2017/077921A1
A gas turbine startup method and device wherein a low-pressure bleed passage (41), a medium-pressure bleed passage (42), and a high-pressure bleed passage (43) for supplying compressed air bled from a low-pressure bleed chamber (25a), a ...  
WO/2017/074227A1
The invention relates to aircraft gas turbine engines, and specifically to methods for controlling the draft of a gas turbine engine during a fire in an engine nacelle at aircraft takeoff. Controlling the sending of a "Decision Speed" si...  
WO/2017/074225A1
The invention relates to systems for automatically protecting gas turbine engines from uncontrolled acceleration of a turbine in the event of said turbine becoming decoupled from the compressor shaft. An initial slip value Sнaч and a c...  
WO/2017/073195A1
A gas turbine combined cycle (GTCC) power generation plant (100) equipped with a control unit which performs a load reduction following operation with respect to a fuel adjustment valve (Vd), a main steam valve (V1), and a bypass valve (...  
WO/2017/068911A1
Provided is a power supply system provided with an energy storage device and a power generation device in which fuel and renewable energy are used for a regional system linked to an external power system, wherein the power supply system ...  
WO/2017/065285A1
Provided is an engine (10) having a gas turbine unit and multiple combustion units (80) for supplying combustion gas (51) to the gas turbine unit. Each of the combustion units (80) includes: a combustion chamber (11); a first mechanism (...  
WO/2017/060228A1
A valve assembly for use to regulate a flow of steam in a flowpath of a turbine. The valve assembly can be configured with a body 200 that circumscribes a rotor. The body is disposed upstream of the rotor blades. In one implementation, t...  
WO/2017/054971A1
The invention is related to a compressor arrangement (100) and a gas turbine engine comprising such a compressor arrangement (100). The compressor arrangement (100) comprises a main compressor section (10), which again comprises boundary...  
WO/2017/052795A3
Embodiments of the invention provide a system or a method for combusting reactants including a fuel and an oxidizer into combustion products in a combustor. A combustor can be configured to contain a flow of the reactants and the combust...  
WO/2017/052795A2
Embodiments of the invention provide a system or a method for combusting reactants including a fuel and an oxidizer into combustion products in a combustor. A combustor can be configured to contain a flow of the reactants and the combust...  
WO/2017/051766A1
A gas turbine control device and method, a gas turbine control program, and a gas turbine, comprising: a first degree-of-opening setting unit (101) that sets a first inlet guide vane (IGV) degree-of-opening command value (S1) for inlet g...  
WO/2017/048611A1
A number of variations may include a product comprising: a vane lever comprising a first end; a second end; a top surface; and a bottom surface; and an opening defined by an inner surface which extends through the top surface and the bot...  
WO/2017/042122A1
A compressed air energy storage system (1) is described, comprising a compressor (3) fluidly coupled to a compressed air reservoir (9) and an expansion train (10) comprising at least a first turbine (7). The system (1) further comprises ...  
WO/2017/038371A1
This gas turbine is provided with an exhaust diffuser (5) in which is formed an exhaust passage (Pe) for channeling exhaust gas from a turbine, and a cooling device (6) for cooling a structure in the exhaust diffuser (5) that faces the e...  
WO/2017/033541A1
According to the present invention, an IGV opening command value is corrected to calculate an actual opening equivalent value which indicates an approximate value of an actual opening. A temperature estimation value, for a case where a m...  
WO/2017/029689A1
The turbine (21) is equipped with: a casing (30); a turbine rotor (90) which is disposed inside the casing (30) so as to penetrate therethrough; rotor vanes (100) which are implanted along the circumference of the turbine rotor (90); an ...  
WO/2017/029437A1
The present invention is a system, method and computer program for operating a land- or marine-based multi-spool gas turbine system for generating electrical power to supply a load, wherein the system comprises a multi-spool gas turbine ...  
WO/2017/022397A1
A gas turbine fuel flow rate setting device (100) is provided with a flow rate ratio computing unit (160) and a flow rate computing unit (180). The flow rate ratio computing unit (160) accepts a parameter (CLCSO) correlated to the gas tu...  
WO/2017/018154A1
A water feeding system (50) is provided with: a first water feeding line (51) through which first feed water flows; a second water feeding line (52) through which second feed water having a lower pressure than the first feed water flows;...  
WO/2017/017378A1
The invention concerns an anti-icing system for a turbine engine blade (A1) extending between an outer housing (CE) and an inner housing (CI) delimiting a flow path (VN), characterised in that it comprises means for injecting a jet of ai...  
WO/2017/013360A1
The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two...  
WO/2017/015343A1
A system and related method for providing a highly reactive fuel to a combustor of a gas turbine are disclosed herein. The system includes a fuel supply system that is in fluid communication with a fuel supply. The fuel supply system inc...  
WO/2017/013356A1
The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (4), a hub (5), hollow arms (63) connecting said collar (4) to said hub (5), and an opening piece (3) which is located on the collar (4) ...  
WO/2017/013347A1
The invention relates to a fuel metering device (12-1) comprising a mobile element (22) comprising at least one fuel passage section (32) opening upstream toward a fuel supply duct and opening downstream toward a usage duct via a meterin...  
WO/2016/209825A1
The subject matter of this specification can be embodied in, among other things, a fluid flow trim apparatus includes an outer housing defining a cavity having an interior surface and an end wall having an orifice therethrough, a valve b...  
WO/2016/208998A1
A method for controlling a gas turbine combustor, according to one embodiment for achieving the objective of the present invention, may comprise: a detection step of obtaining combustion oscillation values through first detection units p...  
WO/2016/203157A1
The invention relates to a hub (2) of an intermediate casing (1) for a bypass turbomachine comprising: - a bleed stream duct (18), - a bleed valve, comprising a mobile door at the inlet orifice to the bleed stream duct (18), - a set of b...  
WO/2016/203980A1
This compressed air energy storage power generation device 2 is provided with: motors 26a, 26b which are driven by fluctuating input power; a compressor 4 which is mechanically connected to the motors 26a, 26b, and which compresses air; ...  

Matches 1 - 50 out of 8,103