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Patent Searching and Data


Matches 801 - 850 out of 8,883

Document Document Title
WO/2010/039403A1
A method for limiting blade pitch is provided. The method includes providing a brake assembly that is actuatable to limit blade pitch, providing a limit stop assembly including a stop wheel and a traveler movable relative to the stop whe...  
WO/2010/037949A1
The invention relates to a system for controlling at least two variable geometry apparatuses in a turbine engine, said system comprising an actuator (24) for actuating the two apparatuses (22, 110, 210), wherein one apparatus comprises a...  
WO/2010/038528A1
Disclosed is a fuel control method for a gas turbine, in which a combustor is constituted by dividing fuel-feeding main nozzles into at least two groups. The fuel is fed (at S1) from the main nozzles of all groups at an ignition time of...  
WO/2010/037751A1
The invention relates to a system for controlling at least two sets of variable geometry equipment (10, 110) of a gas turbine engine comprising at least one first body and a second body, the first set of equipment (10) being a stage of v...  
WO/2010/038290A1
A gas turbine device capable of producing a mixed gas in which three or more types of gases are uniformly mixed. A gas turbine device is structured to burn a fuel gas supplied from a fuel gas supply device (8) together with compressed ai...  
WO/2010/036291A2
A satellite propulsion system has both a chemical monopropellant thruster providing high thrust for rapid maneuvering and an electrospray thruster providing high specific impulse. Both thrusters operate off of a single ionic liquid prope...  
WO/2010/035539A1
Provided is gas turbine control method and controller whereby a design performance and an operating state based on ideal fuel flow rate and air flow rate assumed at the time of designing can be maintained by preventing an operation devia...  
WO/2008/048391A3
A system and method for operating an integrated gasification combined cycle (IGCC) gas turbine system that utilizes the fuel stream (210) as a means of controlling the operation of the IGCC to achieve a target output and efficiency. The ...  
WO/2010/006151A3
A method of transmitting power among a plurality of shafts in a turbine engine is disclosed herein as well as a turbine engine for practicing the method. The turbine engine includes a compressor section having a low pressure portion and ...  
WO/2010/029271A1
The invention relates to a turbine 1 including at least one combustion chamber 2 and a scavenging device, the combustion chamber capable of being supplied with liquid fuel through a first circuit 5 comprising a non-return valve 9, the sc...  
WO/2010/020595A2
The invention relates to a gas turbine (12) which can be safely operated at a nominal rotation speed with a reduced margin in relation to the surge limit of the compressor, and to a method for the operation of this gas turbine. The gas t...  
WO/2010/018338A2
The present invention relates to a fuel flow metering valve (22). The invention is characterized in that it comprises a plurality of openings (24a…24h) and a plurality of control pins (26a…26h) capable of closing said openings, each ...  
WO/2010/016159A1
A gas turbine which has a simplified system and can be operated simply, produced at low cost, maintained and inspected at low cost, and can be operated in turn-down conditions. The gas turbine (1) has a compression section (2); a combust...  
WO/2010/008641A2
A rotary injector (95, 222) comprising one or more radially-extending arms (93) provides for injecting fuel (12, 12.1, 12.4) into a combustion chamber (16). The combustion chamber (16) receives air (14) from locations upstream and downst...  
WO/2010/005120A1
With an operation-controlling device for a gas turbine (1) that is driven mainly with ammonia as fuel, the proportion of petroleum fuel in the fuel supplied to the gas turbine is increased, compared to during normal operation, in operati...  
WO/2010/006151A2
A method of transmitting power among a plurality of shafts in a turbine engine is disclosed herein as well as a turbine engine for practicing the method. The turbine engine includes a compressor section having a low pressure portion and ...  
WO/2009/138598A3
Method and device for implementing the thrust reversers of an aircraft. According to the invention, the following successive steps are carried out automatically: • deployment (E3) of the previously armed thrust reversers of the aircraf...  
WO/2009/052794A3
The present invention relates to a fuel-metering unit (1) for an aircraft engine, said fuel-metering unit being arranged for conveying and metering fuel between a fuel tank (2) and a combustion chamber (3) of the aircraft engine, and als...  
WO/2009/156299A2
An estimation unit is disclosed that estimates on a real-time basis the maximum power generation capacity of a single cycle or combined cycle gas turbine power plant. According to the invention, first, the actual power output and the max...  
WO/2009/151073A1
Provided is a lean fuel sucking gas turbine system comprising a compressor (1) for compressing a mixed gas (G1) having a fuel and air mixed to a concentration of an inflammable limit or lower, thereby producing a compressed gas (G2), a f...  
WO/2009/036970A3
The invention relates to a hydraulic drive (10, 20) for an airplane (F), comprising: a transmission (13), a first hydraulic pump (11; 21) and a second hydraulic pump (12; 22), wherein the transmission (13) is installed in a transmission ...  
WO/2009/144415A2
The invention relates to a turbomachine, including an intermediate casing (12) at the end of which is attached an outer casing (44) of a high pressure compressor (10), and an air collecting means (54, 68), for collecting downstream air i...  
WO/2009/142026A1
Disclosed is a combustion device comprised of a combustion tube which forms the combustion chamber in the interior, a main burner which is positioned at the top of the combustion tube and has a premixture path which injects an air-fuel p...  
WO/2009/142973A2
A system (10) for providing variable pitch to a rotor blade (16) of an aircraft engine includes a rotatable hub (34); at least one blade mounted on the rotatable hub; a gear mechanism operably connected to the rotatable hub; a timing rin...  
WO/2009/138598A2
Method and device for implementing the thrust reversers of an aircraft. According to the invention, the following successive steps are carried out automatically: • deployment (E3) of the previously armed thrust reversers of the aircraf...  
WO/2009/082281A9
The invention concerns a gas turbine engine (1, 100, 500, 600, 700) comprising in serial flow relationship: a first compressor (22, 122, 722) provided with at least one row of compressor blades (27, 127a, 127b, 127c, 127d, 727) distribut...  
WO/2009/133852A1
Provided is an apparatus for the control of a gas turbine in a uniaxial combined-cycle plant, which keeps the output of a gas turbine constant while neither needing a complicated work at the site nor being influenced by the output fluctu...  
WO/2009/112779A3
Heat exchanger system (14) through which a liquid is intended to flow, comprising a heat exchanger (4) with a liquid inlet (4a) and a liquid outlet (4b), a bypass valve (6) with a liquid inlet and a liquid outlet, and a self-cleaning fil...  
WO/2009/101267A3
Device and method for monitoring a high‑pressure pump (14) in a turbomachine fuel supply circuit by detecting the opening of a pressurizing and shut‑off valve (24) mounted on the outlet side of a fuel flow regulating valve (18), by m...  
WO/2009/123770A2
High thrust at sea level and high Isp at high altitudes with low ambient pressure are obtained in a vehicle with an engine of fixed geometry including an exit of non-changing cross section, by incorporating a series of propellant injecto...  
WO/2009/117442A2
The present invention is directed to an energy storage system comprised of a heat block having a relatively high specific energy capacity. The heat block can be used, for example, with a regenerative braking system for gas turbine powere...  
WO/2009/112779A2
Heat exchanger system (14) through which a liquid is intended to flow, comprising a heat exchanger (4) with a liquid inlet (4a) and a liquid outlet (4b), a bypass valve (6) with a liquid inlet and a liquid outlet, and a self-cleaning fil...  
WO/2009/109446A1
Method for operating a gas turbine in a power plant in which boundary limits on the operating concept are adjusted by a power plant operator during operation for optimization of power plant operation relative to efficiency, lifetime cons...  
WO/2009/107818A1
A gas turbine control method for preventing then operation from deviating from the operating state at the ideal fuel and air flow-rates expected when the gas turbine is designed and maintaining an efficient operating state. A gas turbine...  
WO/2009/107805A1
Provided is a plant state monitoring method which monitors an operation state of a plant by using the Mahalanobis distance based on the plant state amount. The method creates a first unit space as a set of data used to be a reference whe...  
WO/2009/101267A2
Device and method for monitoring a high‑pressure pump (14) in a turbomachine fuel supply circuit by detecting the opening of a pressurizing and shut‑off valve (24) mounted on the outlet side of a fuel flow regulating valve (18), by m...  
WO/2009/095632A1
A variable geometry turbine comprises a turbine wheel (5) supported in a housing for rotation about a turbine axis with an annular inlet passageway (9) defined between a radial face of a nozzle ring (11) and a facing wall of the housing ...  
WO/2009/092872A2
The invention relates to a monitoring system (22) characterized in that it comprises – detectors (30) for detecting the state of a turbojet thrust reverser, – a monitoring computer (24), - a device (26) for controlling the reverser m...  
WO/2009/083691A1
The subject of the invention is an aircraft propulsion assembly comprising a nacelle (50) in which there is a power plant (52), the said nacelle comprising an interior wall delimiting a duct (54) with an air inlet (56) at the front, the ...  
WO/2009/084250A1
A control device for controlling a compressor driven by both a gas turbine and a motor has a temperature detection section for detecting the temperature of combustion gas from the gas turbine, and also has a control section for generatin...  
WO/2009/083986A2
The invention relates to a system and a method for generating energy by the use of natural gas-operated energy-generating plant, capable of meeting different energy demand needs.  
WO/2009/082281A1
The invention concerns a gas turbine engine (1, 100, 500, 600, 700) comprising in serial flow relationship: a first compressor (22, 122, 722) provided with at least one row of compressor blades (27, 127a, 127b, 127c, 127d, 727) distribut...  
WO/2009/004143A3
According to the invention, the hot flow nozzle includes a single skin (14s) conformed for promoting the cold flow (10) circulation when the aircraft including said turboshaft engine is in a cruise flight mode.  
WO/2009/040112A3
The invention refers to a power supplying device or system for aeronautics, having a hydrocarbon supply (400) for supplying an engine (400) with hydrocarbon fuel and a hydrogen supply (100) having a fuel reformer (120) for producing hydr...  
WO/2009/075335A1
A gas turbine controlling method aims to reduce the output fluctuation of a gas turbine for a nozzle changing period. For the nozzle changing period to change a first nozzle group used till then into a second nozzle group to be used, tha...  
WO/2009/075721A2
A gas turbine combustion system (10) for a turbine engine (12) is disclosed. The gas turbine combustion system (10) may include a plurality of combustor baskets (14) positioned circumferentially about a longitudinal axis of the turbine e...  
WO/2009/015868A3
Disclosed is a method for determining emission values of a gas turbine, comprising the following steps: a test run is performed on the gas turbine; operational parameters (T0, T4, T4*, NGG, power) of the gas turbine are determined during...  
WO/2009/060889A1
An operation controller and an operation control method of a gas turbine capable of lowering a turbine inlet temperature and satisfying request response for an axial output. In such a case where an output of a power generator (150) is in...  
WO/2009/052794A2
The present invention relates to a fuel-metering unit (1) for an aircraft engine, said fuel-metering unit being arranged for conveying and metering fuel between a fuel tank (2) and a combustion chamber (3) of the aircraft engine, and als...  
WO/2006/107828A3
The invention relates to the discovery that employing a toroidal intersecting vane machine (TIVM) within the internal combustion engine provides substantial improvements in controlling pressure, air pressure and air flow into an engine, ...  

Matches 801 - 850 out of 8,883