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Matches 651 - 700 out of 8,874

Document Document Title
WO/2013/084763A1
A lean fuel sucking gas turbine is provided with: a compressor (1) which compresses working gas (G1) with varying fuel concentration at a combustible concentration limit or lower to generate compressed gas (G2); a catalytic combustor (2)...  
WO/2013/079294A1
The invention relates to a method for operating a fixed gas turbine (10) with a low-calorific and/or medium-calorific fuel, preferably synthetic gas, wherein the gas turbine has a secondary air system with at least two cooling air stages...  
WO/2013/080894A1
A valve control device (50) controls the degree of opening of a pressure adjustment valve (44), and is provided in a gas turbine (12), which is equipped with: a combustor (22) that generates combustion gas by burning a fuel; a turbine (2...  
WO/2013/077861A1
A system and method for anomaly detection is provided. The system (100) and method (200) include utilizing one or more processors, such as in a server, for receiving (108) operational and dynamics data (104) from sensors associated with ...  
WO/2013/077583A1
The present invention relates to an apparatus for displaying the state of a multi-control system of a power plant, and to a method for same which can easily and rapidly find out the state of a multiplexing system by displaying the state ...  
WO/2013/068671A1
The invention relates to a composite panel (30) including at least one inner skin (3) and one outer skin (2) and having at least one opening (5) for receiving a sampling scoop, which forms a channel and the sampling opening of which is i...  
WO/2013/069123A1
A control device for a gas turbine power-generating plant provided with: a compressor (1) for pressurizing the combustion air; an air intake spraying device (3) that sprays sprayed water droplets supplied via a spray flow adjustment valv...  
WO/2013/061301A1
A gas turbine plant for electric energy production provided with: - a gas turbine (12);• - a combustion chamber (11) supplied with fuel; - a detecting module (7) configured to detect at the exhaust of the gas turbine (12) at least a fi...  
WO/2013/061928A1
This liquefied gas treatment system is provided with: a compression means (2) which compresses outside air; a pressurized combustion means (6) which comprises a furnace (3) into which the compressed outside air is led as jacket air and c...  
WO/2013/058253A1
The objective of the present invention is to provide a method for controlling a gas-turbine power plant, a gas-turbine power plant, a method for controlling an oven for gasification of a carbon-containing fuel, and an oven for gasificati...  
WO/2013/058209A1
The present invention relates to a lean fuel intake gas turbine which is capable of stable operation avoiding an accidental fire at a catalytic combustor and an explosion in a compressor even when there is a change in fuel concentration....  
WO/2008/123904A3
Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine (10) having a compressor section (14), a combustor section (16) and a turbine section (18). ...  
WO/2013/042049A1
A method for detecting malfunctions in a combustion chamber of a gas turbine plant includes providing dynamic pressure signals (P1I, P2,...., PN), each indicative of a dynamic pressure at the outlet of a respective burner of a combustion...  
WO/2012/040195A3
A method of power production using a high pressure / low pressure ratio Brayton Power cycle with predominantly N2 mixed with CO2 and H2O combustion products as the working fluid is provided. The high pressure can be in the range 80 bar t...  
WO/2013/038085A2
Method for monitoring the volumetric efficiency of a high-pressure pump of a turbomachine hydraulic regulation system comprising a high-pressure volumetric pump delivering a flow rate Q, dependent on an engine speed N of the turbomachine...  
WO/2013/034420A1
An asset condition monitoring system having a plurality of sensors for taking readings of operational variables of the asset and a feedback controller. The feedback controller is arranged to receive data indicative of the operational var...  
WO/2013/034839A1
Method of synchronising the engines of an aircraft. Method of synchronising the engines of an aircraft, according to at least one activation logic (10, 10') defining a deactivated state (20), an armed state (22) and at least one activate...  
WO/2011/144567A3
The invention relates to a device for supplying cooling air for an engine, in particular an aircraft engine, gas turbine, or the like, having static and rotating components and having cooling air channels formed in same. In order to impr...  
WO/2013/028562A1
A split control unit in a distributed flow unit includes a flow inlet configured to receive a fuel flow, a first manifold having flow lines to supply fuel to one or more primary nozzles, and a second manifold having flow lines to supply ...  
WO/2013/025818A1
An improved system for providing fuel uses a centrifugal pump arrangement that provides dual pressure. The dual pressure pump assembly includes a centrifugal pump for supplying pressurized fluid to an associated downstream use, and an au...  
WO/2013/011222A1
The invention relates to a system for bleeding air on an aircraft, comprising: at least one air bleed valve (5, 5', 5") that can bleed a flow (F) of air on the aircraft, a first temperature information module (10), a second temperature i...  
WO/2012/177372A1
A fuel injector (26) for a turbine engine (100) may include a body member (36) disposed about a longitudinal axis (42), and a barrel member (34) located radially outwardly from the body member. The fuel injector may also include an annul...  
WO/2012/173651A1
An aircraft engine fuel system 900 is disclosed having a gas turbine engine 101, a turbocharger 910, a compressor bleed air system 930 for providing compressor air (A) from the gas turbine engine 101 to the turbocharger 910, and a fuel d...  
WO/2012/163667A1
The invention relates to an adiabatic compressed air storage power plant (01) having at least one compressed air reservoir (02), at least one continuous flow machine (08, 09, 10) connected at least on demand to the compressed air reservo...  
WO/2012/164224A1
Assembly consisting of an intermediate case (7) of a bypass turbojet engine and of an inter‑jet case (10) extending upstream of said intermediate case to separate the primary air jet of the turbojet engine from its bypass air jet, said...  
WO/2012/107467A3
The invention relates to a method for controlling a gas turbine, wherein measurement signal values (Mn1, Mn2) are measured at different times (n1, n2), namely at at least a first time (n1) and a second time (n2), wherein the first time (...  
WO/2012/141252A1
A gaseous-fuel analyzer for determining properties of a gaseous fuel, the analyzer comprising: a gas chromatograph which measures the calorific value and specific gravity of the gaseous fuel and the concentration of a specific component ...  
WO/2012/140373A1
The invention relates to a fuel circuit (10) for a turbine engine, comprising: a low-pressure pump (12), a high-pressure pump (14), and a low-pressure duct (22) connecting the low-pressure pump (12) to the high-pressure pump (14); a high...  
WO/2012/138672A1
A bleed valve that expels a gas from a compressed region includes a valve section and a muffler section coupled to and located downstream from the valve section. The valve section includes a centerbody and a housing. The centerbody suppo...  
WO/2012/132062A1
Disclosed is a method for operating a gas compressor which compresses a gas fuel, a supply condition of which fluctuates, and is provided with a suction flow rate adjustment mechanism, wherein the limit pressure ratio that defines the op...  
WO/2012/123264A1
A stroke transmitter (1) is presented. The stroke transmitter (1) includes a conduit (7) for providing a passage to a fluid, an actuating unit (2) for increasing pressure in an hydraulic fluid, a valve unit (4) configured to operate depe...  
WO/2012/125895A1
An aircraft engine includes a precooler disposed within a nacelle. The precooler defines an ambient air passage and a bleed air passage. Air passes through the precooler from an ambient air inlet to an ambient air outlet. Bleed air passe...  
WO/2012/121900A1
A turbine system for a multistage turbocharger and a method for utilizing the same are disclosed. The turbine system includes a high pressure turbine having an inlet for receiving a flow of fluid, and an outlet for passing the flow on ex...  
WO/2012/120220A1
The invention relates to a method for eliminating rotating stall in the compressor of a turbomachine, characterized in that said method comprises the following steps: - a step (103) of automatically detecting a surge in the turbomachine;...  
WO/2012/114025A1
The invention relates to a turbomachine (10) provided with a combustion chamber (330), a fuel injection device (340) for injecting fuel into the combustion chamber (330), and supply means (360) for supplying the fuel injection device (34...  
WO/2012/114832A1
A gas turbine provided with an air bleeder tube (1) that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharges the bled air into a cylindrical exhaust duct (20), wherein the air bleede...  
WO/2012/114024A1
The invention relates to a turbomachine (10) provided with a combustion chamber (330), a fuel injection device (340) for injecting fuel into the combustion chamber (330), and a power transmission shaft (220). The invention is characteris...  
WO/2012/107467A2
The invention relates to a method for controlling a gas turbine, wherein measurement signal values (Mn1, Mn2) are measured at different times (n1, n2), namely at at least a first time (n1) and a second time (n2), wherein the first time (...  
WO/2012/064363A3
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/2012/105053A1
Provided is a control device for a gas turbine power generation plant, the control device comprising: a compressor (1) pressurizing combustion air; an intake air sprayer (3) spraying a droplet of spray water supplied through a spray flow...  
WO/2012/059671A3
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/2012/093235A1
The invention relates to a fuel circuit (10) of an aeronautical turbine engine, comprising a main fuel line (12) intended to supply fuel to a combustion chamber (24) of the turbine engine and including a positive-displacement pump (20), ...  
WO/2012/056142A3
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/2012/092277A1
One embodiment of the present invention is a unique variable camber vane system for a gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and ...  
WO/2012/084453A1
The present invention relates to a method of detecting a predetermined condition in a gas turbine (10) and to a failure detection system for a gas turbine (10). The invention analyses instantaneous temperature readings from different loc...  
WO/2012/072614A1
The invention relates to a method for operating a gas turbine (40), a device (60) for regulating the starting and/or the operation of a gas turbine (40) and a power plant (42). In order to permit reliable operation of the gas turbine (40...  
WO/2012/073886A1
Hunting in the output of a power generator can be suppressed when the load range is lower than a rated load such as during a trial operation or immediately after adding a load. A gas turbine control device is provided, which is used in p...  
WO/2012/072352A1
The invention relates to a method for limiting over-revving of a gas turbine (12) in the case of load shedding having the steps: operation of the gas turbine (12) by burning fuel (F) in a combustion chamber (22) of the gas turbine (12) a...  
WO/2012/069745A1
The invention relates to a method for monitoring a filter (3) of the fuel-supply system (1) of an aircraft engine, including: a step of detecting clogging of the filter, and a step of sending an indication message, characterised in that ...  
WO/2012/027154A3
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...  

Matches 651 - 700 out of 8,874