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Matches 351 - 400 out of 9,007

Document Document Title
WO/2015/121144A1
The invention relates to a method for operating a gas turbine plant (2) having a compressor (12) and a turbine (20), and to an arrangement (42) for controlling a gas turbine plant (2) having a compressor (12)and a turbine (20), and to a ...  
WO/2015/121146A1
The invention relates to a method for operating a gas turbine system (2) in part load operation and to an arrangement (48) for controlling a gas turbine system (2) in part load operation, and to a gas turbine system (2) having a compress...  
WO/2015/123107A1
The subject matter of this specification can be embodied in, among other things, a fuel pressure regulator system for regulating pressure through a fuel delivery path that includes a fuel pressure regulator valve in the fuel delivery pat...  
WO/2015/121235A1
A method (100) of detecting a fault in a bleed air system (20) of an aircraft (10) having multiple engines (12) including transmitting a bleed air flow rate (102) from multiple engines, determining a difference (104) between the transmit...  
WO/2015/122051A1
A control device for a power generation system whereby power is generated by a first power source that operates by burning a fuel, wherein the control device identifies, on the basis of a pressure difference in a prior-stage mechanism th...  
WO/2015/083186A3
A method for detecting onset of oscillatory instability in a device is described. The method includes obtaining a symbolic time series of a time series signal corresponding to a dynamic state variable of the device. The method further in...  
WO/2015/119135A1
A gas turbine (100) supplies a combustor (103) with fuel and compressed air from a compressor (102) provided with an inlet guide vane (104) in a first part, and rotates a turbine (101) and drives a power generator (150) by means of combu...  
WO/2015/115625A1
 A gas turbine, a device for controlling the gas turbine, and a method for cooling the gas turbine, wherein the gas turbine has a cooling air supply channel (41) for supplying compressed air bled from a compressor (11) to a disc cavity...  
WO/2015/113801A1
The invention refers to a method for controlling part load operation of a gas turbine comprising a controller (27) wherein a load set point (LSP) of the controller (27) is greater or equal a minimum load set point (LSPmin).The minimum lo...  
WO/2015/112633A1
A gas turbine system (14) includes a fuel control system (264) configured to control a fuel flow to one or more combustors (160) and an oxidant control system (262) configured to control an oxidant flow to each combustor of the one or mo...  
WO/2015/110748A1
The invention concerns a turbomachine (1) characterised in that it comprises: - an exhaust housing (7), comprising a plurality of arms (10), the space separating the arms defining openings (13) in which there circulates a primary air flo...  
WO/2015/112317A1
A non-transitory, computer readable medium stores instructions executable by a processor of an electronic device. The instructions include instructions to determine that a transient event is occurring in an electrical grid coupled to an ...  
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 ...  
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...  
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 ...  
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/2015/106153A1
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...  
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...  
WO/2011/083166A3
The invention relates to a device for full-authority electronic regulation (1) of an aircraft engine (3) comprising a supply unit (15), a computation unit (5), a monitoring unit (7), and a radio communication module (19) which is connect...  
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...  
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...  
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...  
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.  
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...  
WO/2015/047468A3
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...  
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,...  
WO/2015/050601A3
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...  
WO/2013/115994A3
A gas turbine engine includes a variable inlet guide vane positioned forwardly of a low pressure compressor. The angle of the inlet guide vane is controlled at startup to increase airflow into the compressor. This is particularly useful ...  
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...  
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 produc...  
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 ...  
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...  
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...  
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...  
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 ...  
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...  
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...  
WO/2014/088671A8
A gas turbine engine variable bleed apparatus (48) includes a variable bleed valve door (50) disposed in a bleed inlet (47) in a transition duct (29), rotatable about two or more separate pivot points (160), operable to open and close an...  
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...  
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 ...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
WO/2015/023323A3
According to various embodiments, a fuel pump system 50 having a servo controlled pump bypass 67 is utilized. The servo controlled bypass around the fuel pump provides the capability for the fuel flow rate to be adjusted and controlled i...  
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...  

Matches 351 - 400 out of 9,007