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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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 ...
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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...
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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.
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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...
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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...
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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...
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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...
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WO/2009/043487A1 |
The invention relates to a multi-stage supercharging group (10, 10', 10') for an internal combustion engine for charging the internal combustion engine with a fluid, particularly an exhaust gas, comprising at least one high-pressure turb...
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WO/2009/040112A2 |
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...
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WO/2009/033944A1 |
The invention relates to a method for the computer-aided control and/or regulation of a technical system. The method involves the use of a cooperative learning method and artificial neural networks. In this context, feed-forward networks...
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WO/2009/030856A2 |
The invention relates to a device for motorized aircraft comprising at least one avionic component (300) positioned in the said aircraft, at least one engine interface (310) positioned in the said aircraft and at least one engine control...
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WO/2009/031552A1 |
In a heating apparatus for heating the air to be sucked into a gas turbine by a heat exchanger, the temperature fluctuation of the heated air is suppressed even in the period, for which a steam source to be fed to the heat exchanger is c...
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WO/2009/018532A1 |
A plasma generator for delaying the onset of rotation stall by tip gap flow control in, for example, an axial flow compressor is disclosed. The tip gap flow control system includes a housing surrounding a rotor of blades and having an in...
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WO/2009/015868A2 |
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...
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WO/2009/016665A1 |
A gas turbine plant control device has control means for selectively controlling an exhaust gas temperature (TS) of the turbine (11) on the basis of at least two distinct reference values (TSRIFV0, TSRIFVI, TSRIFV2... TSRIFVn) related to...
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WO/2009/013136A1 |
The invention relates to a method for operating a combustion device (10) which comprises at least one combustion chamber (11) with a plurality of burners (B1,..,Bn) which act in parallel and which generate in each case one flame (F1,..,F...
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WO/2009/004143A2 |
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.
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WO/2008/152964A1 |
It is possible to reduce the manufacturing cost and the running cost. A plurality of combustion devices are arranged in an annular shape in a combustion device casing. A casing (22) containing a combustion oscillation detection device (2...
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WO/2008/149731A1 |
A gasifying agent supply passage (A) from an axial flow compressor (21) for increasing the pressure of the gasifying agent to a gasification furnace (2) is branched, and a gasifying agent bypass passage (D) provided with an escape pressu...
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WO/2008/147260A1 |
The invention relates to a device for moving a plurality of hatches (202), spaced at intervals from one another in a circumferential direction of a gas turbine engine, between a first position and a second position, wherein each of the h...
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WO/2008/142020A1 |
The invention relates to a gas turbo set (2) comprising a first and a second turbine (4, 6) in addition to a combustion chamber (8) connected therebetween and operating by auto-ignition. The turbines (4, 6) and the combustion chamber (8)...
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WO/2008/139536A1 |
A natural gas liquefaction plant that while effecting cost reduction, can realize over-load driving of gas turbine power generator and attains stabilization of plant power source and accordingly stabilization of plant operation; and a me...
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WO/2008/139535A1 |
A natural gas liquefaction plant comprises a liquefier (11) for liquefying a natural gas (111) by exchanging heat with refrigerants (135, 145, 155); refrigerant compressors (13, 14, 15) for compressing the refrigerants (134, 144, 154) su...
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WO/2008/138797A2 |
A method for pressure dynamics reduction within a gas turbine engine with a number of combustion chambers (1), where a pilot fuel spilt is defined for each combustion chamber, is provided, comprising the steps of measuring the pressure v...
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WO/2008/134853A1 |
A method of operating a gas turbine engine (10) having a rotatable turbine shaft (14) with an electric machine (24) mounted to the shaft (14). The method includes providing supplemental acceleration and/or deceleration of the turbine sha...
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WO/2008/134856A1 |
A method of starting a turbine engine (10) at a first engine speed value (S1) which is lower than a second engine speed value (S2) designed for a normal engine starting operation, comprises varying a fuel flow (FF1) into a combustor (28)...
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WO/2008/134097A2 |
A system and method implements machine performance, most preferably for gas ' turbine engines. The system and method implement a control law (118) that ' receives sensed operational parameter feedback signals (124). For each sensed engin...
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WO/2008/128326A1 |
A method for detecting a surge condition during operation of a gas turbine engine includes detecting a change of pressure differential between fuel flows in a fuel system (28) of the engine during engine operation.
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WO/2008/128325A1 |
A method and apparatus for measuring a start fuel flow to a pilot nozzle (34) of a fuel system (28) of a gas turbine engine using pressure differential between fuel passages leading to fuel nozzles (34, 37).
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WO/2008/126399A1 |
A plant controller of a combined cycle power plant type power-station having a plurality of power generation shafts for coupling a turbine and a generator and outputting electric power generated from the generator by the turbine output a...
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WO/2008/108058A1 |
A gas turbine power generation system, which can suppress an increase in the number of revolutions of a gas turbine easily upon occurrence of a sudden drop in gas turbine load, comprises a gas turbine (2), a generator (7) connected, in o...
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WO/2008/105907A2 |
A control system 10 and method of controlling a propeller aircraft engine 20 during takeoff limits the amount of engine power developed at the very beginning of the takeoff in order to maximize thrust and minimize rollout distances. The ...
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WO/2008/098891A1 |
The invention relates to a power plant system (10), comprising a turbine branch (11) made of a gas turbine (12) and a generator (18), which is directly driven by the gas turbine (12) and generates an alternating current have an operating...
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WO/2008/098894A1 |
The invention relates to a power plant (40) comprising a turbine train composed of a gas turbine (12) and a generator (28), directly driven by the gas turbine (12) and generating alternating current of a first operating frequency, the ou...
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WO/2008/098911A1 |
The invention relates to a method for operating a power plant (10) comprising a turbine train (11) composed of a gas turbine (12) and a generator (18), directly driven by the gas turbine (12) and generating alternating current of an oper...
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WO/2008/097269A2 |
A method includes controlling an aircraft during descent, and controlling the engine pressure ratio of a jet engine so that the engine has a substantially equal pressure at the exhaust, and at the front of the engine during the descent.
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WO/2008/092252A1 |
A fuel control system (22) having a combustive energy value evaluator (38) determining a combustive energy value of the fuel, and a controller (26) calculating a desired flow rate based at least on the combustive energy value and control...
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WO/2008/091503A2 |
A combustion turbine power generation system includes a combustion turbine assembly (10) including a main compressor (12) constructed and arranged to receive ambient inlet air, a main expansion turbine (14) operatively associated with th...
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WO/2008/091415A2 |
An indirect-fired biomass-fueled gas turbine system with a combustor for combustion of biomass particles to produce a combustion gas, a heat exchanger providing a heat exchange relationship between combustion gas from the combustor and c...
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WO/2008/087126A1 |
Method of Controlling a Fuel Split Method of controlling a fuel split of a pilot fuel flow and a main fuel flow in a gas turbine combustor in case of load reductions characterised in that the rate of change of fuel demand is monitored (1...
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