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Matches 201 - 250 out of 9,002

Document Document Title
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/2017/052795A3
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/2017/095569A1
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/2017/052795A2
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/2016/055715A3
The invention relates to a stator (40) of an aircraft turbine engine, comprising an annular row of stationary vanes (44) and an annular row of arms (48), characterised in that the trailing edges (42) of the stationary vanes are located s...  
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; ...  
WO/2016/203979A1
This compressed air energy storage power generation device 2 is provided with: an expansion-side heat medium temperature sensor 40 for measuring the temperature of a heat medium supplied to an expansion-side heat exchanger 16; an expansi...  
WO/2016/192890A1
The invention relates to an operating method for a gas turbine (1) by partial-load operation, comprising the following steps: setting of a power setpoint value (LS) for a predefined temperature value (T0); determining the two operating c...  
WO/2016/186512A1
A system and a method for recovering waste heat from an industrial process in pre heating combustion air and fuel is provided. The present invention attains the above-described objective by a plurality of heat exchangers extracting heat ...  
WO/2016/185119A1
The invention relates to an intermediate casing hub of an aircraft turbojet engine, which includes: an outer shroud (14) intended for defining a secondary flow space of a stream of secondary gas on the inside and an inter-flow area on th...  
WO/2016/181069A1
The invention relates to a butterfly valve (24) for bleeding a compressor for an aircraft turbine engine, the valve including a valve body (32), a butterfly (36), and a device (42) for controlling the angular position of the butterfly, t...  
WO/2016/177538A1
The invention relates to a method for computer-supported processing of a digitally saved series of measurement data. In the method according to the invention, a first function, which approximates the progression of the data points of the...  
WO/2016/176174A1
The invention relates generally to an electrical power and storage system and more specifically to ways and methods of using a thermal storage medium as a heat source to heat compressed air from a power augmentation system for use in a g...  
WO/2016/175753A1
A fuel delivery system (10) for a gas turbine engine (12) that employs a technique for purging fuel delivery tubes (82). The fuel delivery system includes a multifunction valve (64) that has a flow through position (66) and a bi-directio...  
WO/2016/172083A1
A fuel metering valve includes a valve body housing a valve element in an interior chamber between an inlet port and an outlet port, an actuator coupled to move the valve element relative to the valve body, and a controller configured to...  
WO/2016/172244A1
A fuel metering valve includes a valve body housing a valve element in an interior chamber between an inlet port and an outlet port, an actuator coupled to move the valve element relative to the valve body, and a controller configured to...  
WO/2016/167925A1
A method of operating a multi-engine, rotary wing aircraft in a single engine, in-flight mode, the method includes stopping a first engine while operating a second engine; closing variable inlet guide vanes on the first engine; and turni...  
WO/2016/162139A1
The invention relates to a device (100) for detecting the rotational angle of the position of a plurality of adjustable guide vanes (11) of a gas turbine (10), comprising at least three rotational angle sensors (1, 2, 3) at different loc...  
WO/2016/163907A1
The present patent application provides a monitoring system for use with a mechanical device, especially a gas turbine, comprising a number of sensors configured to measure physical data from the mechanical device, a data acquisition ...  
WO/2016/156739A1
The invention relates to a hub (2) of an intermediate casing (1) for a dual-flow turbine engine, said hub (2) comprising: a discharge flow duct (18) extending between an inner shroud (3) and an outer shroud (5) of the hub (2), the discha...  

Matches 201 - 250 out of 9,002