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Patent Searching and Data


Matches 301 - 350 out of 8,861

Document Document Title
WO/2015/140200A1
Method of starting a gas turbine, comprising the steps of providing an apparatus (1) for regulating the flow of fuel in a gas turbine, the apparatus (1) comprising a main line (4) connecting a fuel source (2) to a nozzle array (N); an au...  
WO/2015/141561A1
A combustor (10) is provided with: a nozzle (25) having formed therein an air jet section (51) that causes air to be jetted from a nozzle section (25s); a cylindrical member (26) that covers the nozzle (25) from the outer peripheral side...  
WO/2015/142318A1
A system for monitoring air flow into a compressor section of a turbine engine includes a chamber upstream from an inlet of the compressor section and a plurality of filter packages. The filter packages are in fluid communication with at...  
WO/2015/130356A2
A fuel system for a gas turbine engine includes a fuel conditioner. The fuel conditioner has an ice debris separator, a fuel pump, a heat exchanger, and an air oil cooler. The ice debris separator has a fuel inlet and a fuel outlet. The ...  
WO/2015/129498A1
 A fuel control device is provided with: a combustion temperature estimated value calculator for using atmospheric conditions, an opening degree command value of a valve for controlling the amount of air mixed and combusted with fuel, ...  
WO/2015/128193A1
The invention relates to a method for operating a stationary gas turbine (1) at partial load, comprising at least one compressor (11), at least one expansion turbine (14) and a combustion chamber (12) provided with at least one burner (1...  
WO/2015/124909A1
A fuel supply system for a gas turbine having at least one combustor (10), comprising at least one first heat exchanger (200A), receiving a fuel from a fuel source at a first temperature through a first fuel line (4) and provide the fuel...  
WO/2015/123820A1
A fuel supply line system (200) used for a gas turbine (200), comprising: fuel gas control valves (22, 24) used for controlling delivery to said gas turbine; a first line used for connecting the fuel gas source (10) to said control valve...  
WO/2013/126279A8
System and method for tuning the operation of a turbine and optimizing the mechanical life of a heat recovery steam generator. Provided therewith is a turbine controller, sensor means for sensing operational parameters, control means for...  
WO/2015/124359A1
The invention relates to a method for operating a gas turbine installation (10) with a measured compressor inlet temperature (Ti-actual) and a virtually constant turbine inlet temperature (TiTiso). To provide safe operation of the gas tu...  
WO2015060956A3
A method of controlling an airfoil component temperature distribution includes the steps of detecting an airfoil component temperature, comparing the detected airfoil component temperature to a desired airfoil component temperature profi...  
WO/2015/121035A1
The invention relates to a method for operating a compressor train (10) having at least one compressor (12) and at least one cooling device (14) for cooling at least one flow medium (16) to a predefinable compressor temperature (Tcom), i...  
WO/2015/101450A3
The invention relates to an ascertainment method (20) for determining a final angle (E) of vanes that are adjustable between an initial angle and the final angle (E) and are part of a row of leading vanes (12) which are arranged upstream...  
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...  

Matches 301 - 350 out of 8,861