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WO/2015/110320A1 |
The invention relates to a method for regulating a gas turbine (1). The fuel quantity supplied to the burners of the gas turbine (1) is regulated using a target value (Tsoll) for the corrected turbine outlet temperature (TATK). A stable ...
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WO/2015/110313A1 |
According to the invention, a method for controlling a gas turbine (1) reduces the gas turbine speed more rapidly in the case of a load disconnection in order to prevent emergency shutdown of the gas turbine. To this end, when it has bee...
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WO/2015/108340A1 |
The present invention relates to: a gas turbine having a rotor shaft, which is movable in the direction of a rotation shaft, for adjusting a turbine blade front end gap, and having a blade vane carrier, which is movable in the direction ...
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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/2015/106153A1 |
The present disclosure relates generally to system and method for detecting fuel shutoff valve failures in a system including multiple fuel shutoff valves connected in series. By commanding different fuel shutoff valves to close and dete...
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WO/2015/102882A1 |
A system includes a gas turbine comprising a compressor section, combustor section, and a turbine section. The system further includes a first fuel line and a second fuel line coupled to the gas turbine. The system also includes a feed c...
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WO/2015/100081A1 |
A control system and method for a gas turbine engine are provided. A controller (40) is responsive to at least one parameter to control an air-to-fuel ratio. The parameter may be a measured engine exhaust temperature from a temperature s...
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WO/2015/097861A1 |
A combustion system (1) comprises: a combustor (2) having a plurality of staging blocks and flashback sensors (40, 41,...) for sensing for flashbacks occurring at the staging blocks; and a combustion control device (10) for stopping fuel...
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WO/2015/092252A1 |
The invention relates to a method for automatically controlling an operating speed of a helicopter turboshaft engine, including a step (10) of receiving data (27, 28, 29) that represent the flight of the helicopter; a step (11) of select...
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WO/2015/091029A1 |
The invention relates to a method for regulating and/or controlling the manipulated variables (25) of a gas turbine in a combustion system, using three submodels according to the invention.
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WO/2015/088662A2 |
A method includes interpreting a compressor outlet pressure target value and a compressor outlet flow target value, determining a compressor target speed value in response to the compressor outlet pressure target value and the compressor...
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WO/2015/084747A1 |
A system includes a gas turbine engine configured to combust an oxidant and a fuel to generate an exhaust gas, a catalyst bed configured to treat a portion of the exhaust gas from the gas turbine engine to generate a treated exhaust gas,...
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WO/2015/078014A1 |
Disclosed is a measurement method for rotation of a guide vane (70) in a gas turbine, comprising: measuring a first rotational angle α1 of the guide vane (70) at the position where a first angle sensor is mounted; measuring a second rot...
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WO/2015/079508A1 |
Provided is a power generation system which adapts well to load fluctuations. A multi-shaft gas turbine power generation system provided with: a compressor (1) for compressing air to produce compressed air; a combustor (20) for producing...
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WO/2015/078013A1 |
Disclosed is a detection method of a sensor in a gas turbine, comprising: adopting a pressure sensor (88) to measure a pushing force (F) of a push rod (10); measuring a first rotational angle of a guide vane (70) at the position where a ...
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WO/2015/075346A1 |
The invention relates to a method for controlling a turbine engine (5) which includes a compressor (8), a combustion chamber (9), first and second turbines (10, 12), a first rotary shaft (11) rotatably secured to said compressor and to s...
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WO/2015/075389A1 |
The invention relates to a multi-point fuel injection device (1) for an aircraft engine (M), comprising an inlet line (10), at least two injection lines (11, 12), and a purge line (14), a fuel distributor member (2) connected to each lin...
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WO/2015/075360A1 |
A device (20) for supplying propellant to at least one propulsive rocket engine chamber (19) of a propulsive assembly (21) comprises a main propellant reservoir (1, 2), a main supply pipe (3, 4) extending between the main reservoir (1, 2...
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WO/2015/071079A1 |
The present invention relates to a combustor system (100) for a gas turbine engine. The combustor system (100) comprises a combustion chamber (101) into which a pilot fuel (102) and a main fuel (103) is injectable and flammable, wherein ...
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WO/2015/072635A1 |
Disclosed is a swirler assembly. The swirler assembly according to the present invention comprises: a casing; a support shaft placed in the interior of the casing; and a blade part formed on the outer peripheral surface of the support sh...
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WO/2015/067872A1 |
The invention relates to the field of technical trials and specifically to a technical trial method for assessing at least one device operation parameter (X) across a series of operation increments, each one of which corresponds to a sta...
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WO/2015/062966A1 |
The invention concerns a method of operating a gas turbine (100) in order to ensure that a gas turbine operates reliably and economically in natural gas supply mains with a power-to-gas feed. To that end, the hydrogen content of the fuel...
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WO/2015/063735A1 |
Control method and device for controlling a gas turbine plant (1) provided with at least a gas turbine (5), a combustion chamber (4) and a compressor (3); the method comprising the steps of: - setting a plurality of reference values for ...
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WO/2015/062948A1 |
The invention relates to a gas turbine (100) and suitable operating methods, wherein the gas turbine (100) comprises a compressor (1) for providing compressed air (2), a combustion chamber (4) provided with a burner (3), and an expansion...
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WO/2015/064428A1 |
This temperature control device is equipped with: a temperature difference calculation unit that calculates a temperature difference between the inlet and outlet of a booster compressor that outputs cooling air, obtained by cooling compr...
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WO/2015/062979A1 |
The invention relates to a gas turbine (10) and to a method for producing a gas turbine (10) with a housing (1) and a compressor (2), wherein the compressor (2) has a rotor (3) with multiple compressor discs (4a, 4b). The rotor (3) carri...
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WO/2015/054834A1 |
A fuel supply system includes a first fuel gas compressor coupled to a fuel gas compressor shaft and configured to pressurize a fuel for a gas turbine system. A clutch is coupled to the fuel gas compressor shaft and is configured to sele...
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WO/2015/053003A1 |
Provided is a fuel injection device for gas turbines that is capable of uniformizing, with a simple structure and at low cost, the concentration distribution of a fuel gas and water vapor in a combustion chamber, and that is capable of e...
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WO/2015/052458A1 |
A method (100) of diagnosing an auxiliary power unit (10) fault in an aircraft (50) having an auxiliary power unit and multiple sensors related to the auxiliary power unit, components thereof, and systems related thereto, including recei...
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WO/2015/052413A1 |
The invention relates to a method for optimising the specific consumption of a helicopter provided with two turboshafts (1, 2), each one comprising a gas generator (11, 21) provided with a combustion chamber (CC), each of said turboshaft...
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WO/2015/054079A1 |
Methods and apparatus for measuring liquid fuel flows within a conduit (104) are disclosed. An example flow sensor (101) may include a conduit (104) arranged to flow fuel therethrough along a flow axis (154), the conduit (104) defining a...
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WO/2015/050601A2 |
A fuel system for a gas turbine engine comprises an injector disposed to inject fuel and air into a combustor of the gas turbine engine. In a first embodiment, the fuel system further comprises an air separation module configured to supp...
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WO/2015/046133A1 |
A fuel system (1A) is provided with a centrifugal pump (2a) that pressurizes and discharges fuel (N) that is supplied to an aircraft engine (E). The fuel system (1A) is also provided with a transmission (2c) that: connects the engine (E)...
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WO/2015/045905A1 |
This fuel system (1A) is provided with: a constant volume pump (2i) and a centrifugal pump (2a) that pressurize and discharge a fuel (N) that is supplied to an aircraft engine (E); a calculation control means (4) that is configured so as...
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WO/2015/046177A1 |
A fuel system (1A) is provided with a constant volume pump (2c) that pressurizes and discharges fuel (N) that is supplied to an aircraft engine (E). The fuel system (1A) is additionally provided with a transmission (2d) that: connects th...
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WO/2015/047468A2 |
A control system for turbofan engine includes a first sensor measuring rotation of a first shaft at a first location and a fan shaft sensor measuring a speed of a fan shaft. A controller utilizes measurements of a first speed of the firs...
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WO/2015/048214A1 |
A gas turbine engine includes a fan, a turbine having a fan drive rotor, and a speed reduction device effecting a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of ...
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WO/2015/041346A1 |
A gas turbine (10) equipped with a compressor (11), a combustion chamber (12) and a turbine (13) is further equipped with: a pressurizing device (40) for taking in some of the compressed air compressed by the compressor (11), and pressur...
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WO/2015/042123A1 |
A system 100 for controlling a gas turbine based power plant 10 includes a plurality of sensors 34 configured to transmit signals 72 indicative of one or more operating parameters of the gas turbine 12, and a control system 20 in electro...
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WO/2015/040569A1 |
A method of controlling emissions of a gas turbine plant (1), including a compressor (7), a combustion chamber (9) and a gas turbine (10), includes detecting the oxygen concentration (S02) in the exhaust gases (QE) of the gas turbine (10...
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WO/2015/038247A1 |
A fluid pressure regulating system includes a turbomachine configured and adapted to pressurize fluid in a first mode and to depressurize fluid in a second mode. An energy exchange device is operatively connected to the turbomachine to p...
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WO/2015/036233A1 |
The invention relates to a gas turbine (1) comprising a compressor (2), a turbine unit (3), at least one combustion chamber (4) and a secondary air system (10), which secondary air system (10) has at least one cooling line (20) having a ...
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WO/2015/034513A1 |
An aircraft including a jet engine including a core having a compressor and combustion chamber, and a particulate sensor located within the core and a particulate detection method for an aircraft having a jet engine where the method incl...
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WO/2015/034133A1 |
The present invention provides a gas turbine combustion instability control device, which is combustion instability device for controlling the operation of a gas turbine by measuring the combustion dynamics of the gas turbine, and the de...
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WO/2015/033786A1 |
A fuel supply system for a gas turbine engine is provided with: a confluence passage (19) connected to a combustion nozzle (11); a first pump (P1) for discharging fuel into the confluence passage (19); a first electric motor (M1) for dri...
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WO/2015/033046A1 |
The invention concerns a fuel system (1) for a turbomachine comprising: - a control circuit (9a), - a main circuit (9b), - a flow rate regulator (2), suitable for regulating the flow of fuel in the control circuit (9a) and in the main ci...
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WO/2015/033769A1 |
This control device (50) is provided with: a temperature control unit (51) which controls the degree of opening of a fuel flow regulator valve (47) so as to maintain the inlet of a turbine (21) into which a fuel gas enters at a constant ...
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WO/2015/031318A1 |
A method includes receiving an indication of exhaust gas temperature (EGT) for a gas turbine engine, and determining, by at least one processor, based on the received indication of the EGT, a representation of a second derivative with re...
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WO/2015/025109A1 |
The invention relates to a system for injecting fuel into a combustion chamber of an engine, comprising at least two fuel circuits, one with a constant flow rate (1) and the other with an intermittent flow rate (2), members (4, 5) for do...
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WO/2015/026444A1 |
A turbine section including a high pressure turbine, an intermediate pressure turbine and a fan drive turbine, the fan drive turbine driving a gear reduction to in turn drive a fan, and effecting a reduction in the speed of the fan relat...
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