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Matches 701 - 750 out of 8,882

Document Document Title
WO/2012/064363A2
The power plant combusts a hydrocarbon fuel with oxygen to produce high temperature high pressure products of combustion. These products of combustion are routed through an expander to generate power. The products of combustion are subst...  
WO/2012/045029A8
A dual fuel engine control system 900 is disclosed including a first fuel control system 700 for controlling the flow of a first fuel 11 to an aircraft gas turbine engine 101 and a second fuel control system 800 for controlling the flow ...  
WO/2012/059671A2
The invention seeks to reduce the specific fuel consumption Cs of a twin engine helicopter without compromising on the safety conditions regarding the minimum amount of power to be supplied for any kind of mission. To achieve this, the i...  
WO/2012/056144A1
Method of controlling a turbomachine comprising; - a step of measuring a first temperature (T25) by a first temperature sensor, - a step of measuring a second temperature (T3) by a second temperature sensor, - a step of estimating a thir...  
WO/2012/056142A2
According to the invention the control of a fuel metering device (3) for turbomachine as a function of a mass flow rate setpoint (Wf32) comprises the selection, as a function of at least one validity criterion, of a mass flow rate from a...  
WO/2012/057282A1
The present invention includes: a gas-turbine fuel nozzle (1) having a plurality of fuel supply passages (3a) through which fuel is supplied, a plurality of fuel/scavenging-fluid supply passages (3b) through which fuel or a scavenging fl...  
WO/2012/045939A1
The invention relates to a thruster for a space launcher, comprising: an engine (200) supplied with propellant from at least two propellant tanks (131, 132); measuring means (50) capable of measuring, by means of dewatering, the quantity...  
WO/2012/045028A1
A dual fuel propulsion system 100 is disclosed including a gas turbine engine 101 capable of generating a propulsive thrust using a cryogenic liquid fuel 1 12. A method of operating an aircraft engine 101 is disclosed using a selected pr...  
WO/2012/042628A1
The purpose is to improve the output and the power generation efficiency utilizing hot water produced with a solar heat or a thermal energy of a combustion exhaust gas. This gas turbine power generation device (100) comprises: a compress...  
WO/2012/045029A1
A dual fuel engine control system 900 is disclosed including a first fuel control system 700 for controlling the flow of a first fuel 11 to an aircraft gas turbine engine 101 and a second fuel control system 800 for controlling the flow ...  
WO/2012/028804A1
The invention relates to a method for detecting the ingress of water or hail into a turbine engine, said turbine engine including at least one compressor (4), a combustion chamber (1), and a turbine (2). The method includes the following...  
WO/2012/007638A3
The present invention relates to an actuator (10) comprising at least one stage of turbo compressor (1a, 1b), with an outlet for conveying gas compressed in said at least one stage of turbo compressor (1a, 1b) to at least one cooler (3a,...  
WO/2012/027154A2
A dual-pump fluid distribution system that includes a first pump having an inlet and an outlet, and configured to supply a first flow of fluid, and a second pump having an inlet and an outlet, and configured to supply a second flow of fl...  
WO/2012/025689A1
The invention specifically relates to optimizing fuel-injection control. To this end, the driving speeds of apparatuses are adjusted by controlling the speed of the turbine TL according to the power. According to the invention, the metho...  
WO/2012/023302A1
The purposes of the invention are to reduce the consumption of high-calorie gases such as a coke oven gas (COG) during the running of a gas turbine, and prevent the gas turbine from being shut down due to clogging of a pilot line or a tr...  
WO/2012/007341A1
The invention relates to a gas turbine (10) and to a method for operating such a gas turbine (10), by means of which method the partial load operating mode of the gas turbine (10) can be increased while low (CO) emissions are maintained,...  
WO/2012/004496A2
The invention relates to an ignition procedure for a turbine engine combustion chamber (10) supplied with fuel by injectors (26) and comprising means (28) for igniting the fuel injected into the chamber (10). This procedure comprises: an...  
WO/2012/004506A1
According to the invention, the detection method includes the following steps: detecting (E40) an abnormal acceleration of the turbine engine or of a operating line of the compressor that is characteristic of a fault in the turbine engin...  
WO/2011/154528A1
The invention relates to a method (30) for starting or stopping a gas turbine (1) including a combustion chamber (6) supplied, according to one or more feed controls, with a gas fuel that can comprise one or more given different gases, e...  
WO/2011/152840A1
A method is provided for increasing an emissions compliant load range (50) for a combined-cycle system (10). The method includes bypassing an air flow from a compressor (14) to a HRSG (20), to form a mixture of bypassed air and exhaust g...  
WO/2011/141302A1
The present invention relates to a limit stop device (9) for limiting an adjustment path (7) of a mobile component (10) relative to a stationary component (11), having a sleeve body (21) that can be inserted into an opening (24) formed i...  
WO/2011/139567A1
Methods for controlling a gas turbine engine are provided, where a compressor inlet temperature, ambient temperature, and relative humidity are measured. Utilizing these measurements, it is first determined whether an evaporation cooler ...  
WO/2011/137110A1
Tuning processes implemented by an auto- tune controller (150) are provided for measuring and adjusting the combustion dynamics and the emission composition of a gas turbine (GT) engine via a tuning process. Initially, the tuning process...  
WO/2011/137107A1
A tuning process is provided for monitoring fuel properties of a fuel being consumed by a gas turbine (GT) engine (110), and for dynamically tuning the GT engine as a function of changes to the monitored fuel properties. Initially, readi...  
WO/2011/132524A1
In order to provide a method and system for anomaly detection/diagnosis that can detect anomalies quickly and with high sensitivity in a installation such as a plant, in the present disclosures, sets of maintenance record information com...  
WO/2011/097121A3
A turbine engine assembly for a generator including a turbine engine having a compressor section (12), a combustor section (30) and a turbine section (14). An air bleed line is in communication with the combustor section for receiving co...  
WO/2011/132426A1
A fuel distributor provided in a fuel supply device for a gas turbine engine has a moving body that moves in response to the fuel pressure in a fuel inlet, opens only a pilot port when the fuel pressure in the fuel inlet is lower than a ...  
WO/2011/128573A1
The setpoint signal (C1) represents a delivery of fuel to be supplied by a slide-valve type (in-line) metering device (2) to a fuel injection system (4) for injecting fuel into a combustion chamber of a turbomachine, the position of the ...  
WO/2011/129287A1
Disclosed is a gas turbine control device which can maintain stable combustion and good exhaust gas characteristics even if the catalyst is degraded. The disclosed gas turbine control device (6) is provided with a combustion device (2) w...  
WO/2011/127635A1
Disclosed is a fully-steam-driven internal combustion engine added with a motor, which includes a mechanical power system, a combustion system and a gas supply system. The mechanical power system includes a turbine and a turbine shaft (2...  
WO/2011/128744A1
Disclosed is a device for preserving fluid systems, for example of a fuel system and an oil system of a turbine engine, with at least one drive for driving at least one fuel pump and at least one oil pump, wherein a valve arrangement is ...  
WO/2011/064143A3
Gas turbine, software and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine. The method includes determining a turbine exhaust pressure at an exhaust of the turbin...  
WO/2011/118372A1
Provided is a lean-fuel intake gas turbine which has no pressure loss in the exhaust gas line that may lead to a drop in engine output and can be reduced in size of the gas turbine. The lean-fuel intake gas turbine includes a compressor ...  
WO/2011/109008A1
An oxy-combustor is provided to combust oxygen with gaseous low heating value fuel. A compressor upstream of the combustor compresses the fuel. The combustor produces a drive gas including steam and carbon dioxide as well as other non-co...  
WO/2011/098193A1
It is described a method of determining an exit temperature of a gas exiting a combustor (24) of a gas turbine (10), the method comprising: determining a mass flow and a temperature of fuel being delivered to the combustor; determining a...  
WO/2011/097121A2
A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell a...  
WO/2011/096197A1
A fuel supply device for a gas turbine engine is provided with a fuel distributor (66) for distributing fuel, which is delivered from a collective fuel path (63), to a pilot fuel path (64) and a main fuel path (65). The fuel distributor ...  
WO/2011/093850A1
A system and method for converting otherwise wasted energy produced in the form of heated gases as a byproduct of an industrial process into electrical energy. At least some waste gases are diverted from a typical exhaust structure throu...  
WO/2011/056193A3
A method of controlling engine performance is provided that includes obtaining at least one optical wavelength-dependent measurement from at least one combustion event in at least one combustion chamber. The method further includes analy...  
WO/2011/031983A3
A method for improving interpenetration, mixing, and combustion between a fuel and oxidizer reactant mixture and combustion product gases in engines having a combustor includes the step of providing an engine having a combustor in which ...  
WO/2011/083166A2
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/2011/080547A1
A method and system for optimizing load scheduling for a power plant having one or more power generator units is provided. The method and corresponding system involves detecting an event indicative of a need for adapting one or more cons...  
WO/2011/064142A1
Gas turbine, computer readable medium, and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and a turbine. The method includes determining a turbine pressure ratio, calculating a primar...  
WO/2011/064343A1
Gas turbine and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine. The method includes calculating an exhaust temperature reference curve of the turbine as a funct...  
WO/2011/064140A1
A Gas turbine, computer software and a method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine are disclosed. The method includes a step of determining an exhaust pressu...  
WO/2011/064509A1
The invention relates to checking the measurement of the flow of fuel supplying an aeroplane engine, by means of a mass flowmeter. According to the invention, the method assesses whether at least the following conditions are met: the sig...  
WO/2011/065477A1
Disclosed is a gas supply device (4) provided with a first passage (11) which connects a heat-treating furnace (2) to a power generation device (3), a pressure control valve (21) which is disposed in the first passage (11) and which cont...  
WO/2011/042636A9
The invention relates to a system for controlling the angular position of stator blades including a means (20) for calculating a set angular position of the blades (VSVCAL) according to one of the speeds (N1, N2) and a module (1) for cor...  
WO/2010/072524A3
The invention relates to a method for stabilizing the network frequency (f) of an electrical power network (NT) wherein an at least two-shaft gas turbine (GT) has a power turbine (PT) and a gas generator (GG), wherein the power turbine (...  
WO/2010/077522A3
A fuel oxidizer system (100) is operated in a first operating mode. In the first operating mode, a mixture that includes fuel from a fuel source (20) is compressed in a compressor (6) of the fuel oxidizer system (100); the fuel of the co...  

Matches 701 - 750 out of 8,882