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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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 (...
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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 ...
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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 (...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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 ...
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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 ...
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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...
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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;...
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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...
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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...
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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...
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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) ...
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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...
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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...
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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...
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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...
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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; ...
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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...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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WO/2016/156740A1 |
The invention relates to a flow limiter which comprises a body (1) comprising a fluid intake (2) and a fluid outlet (3), in which body a pipe (5) for circulating the fluid is provided, comprising a series of chambers having different cro...
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WO/2016/151849A1 |
A turbine rotor blade according to an embodiment of the present invention comprises: a hub part that is connected to one end of a rotating shaft; a plurality of main blades that are provided on a peripheral surface of the hub part so as ...
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