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WO/2014/126236A1 |
The present invention is equipped with; a waste heat recovery device (100) that uses heat from exhaust gas (EG) exhausted from a gas turbine (10) to generate steam; and a purified water generation device (200) that uses the energy of the...
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WO/2014/126565A1 |
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity, a cor...
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WO/2014/126190A1 |
A fuel gas calorie estimation device equipped with: a fuel gas flow volume acquisition unit that acquires the flow volume of a fuel gas flowing into the combustor of a gas turbine; a state quantity acquisition unit that acquires the stat...
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WO/2014/118457A1 |
Turbo machine combustion assembly (1) comprising a combustion chamber (10), at least one starting injector (17), a plurality of main injectors (18) distributed at constant angular intervals around the circumference of the combustion cham...
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WO/2014/116326A2 |
A method of establishing a boundary for a material improvement process on a workpiece is disclosed. The method may include identifying a maximum allowable damage depth on the workpiece; identifying a maximum constant thickness line on th...
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WO/2014/114656A1 |
Described herein are methods of operating a gas turbine engine (12) for reduced ammonia slip. An exemplary method (100) includes operating (102) the engine over a range of power output levels; controlling (104) a mass flow of NOx produce...
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WO/2014/115105A1 |
A gas turbine plant (1) for electric energy production is equipped with; a gas turbine (5); a compressor (3); a combustion chamber (4); a plurality of heat-sensitive elements (34) configured to detect a plurality of temperature values (T...
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WO/2014/113662A1 |
A method for controlling a hybrid machine is disclosed. The hybrid machine may be equipped with a turbine engine (102), a generator (120) connected in series with the turbine engine (102), an electrical energy storage device (130), and a...
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WO/2014/113105A2 |
A fuel nozzle for a combustor of a gas turbine engine, includes a swirler tip along an axis; and a helical adapter along the axis and within the swirler tip. A method of directing a fuel gas and a liquid through a fuel nozzle and into a ...
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WO/2014/112484A1 |
This fuel system is provided with: a fuel pump (3) which comprises a constant volume pump and which has a discharge flow rate which changes in response to a variation in the rotational speed of the drive shaft of the fuel pump; a boost p...
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WO/2014/109788A1 |
A gas turbine engine has a turbine section, and a housing enclosing the turbine section, with a mount structure secured to the housing for mounting and including internal flow passages for delivering air to remote locations.
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WO/2014/109786A1 |
In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor ...
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WO/2014/105325A1 |
A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pum...
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WO/2014/105328A1 |
A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels, including a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tan...
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WO/2014/105331A1 |
A turbine engine assembly (101) and dual fuel aircraft system having a cryogenic fuel system (500), having a cryogenic fuel reservoir (502), a vaporizer heat exchanger (504), a liquid supply line (506) operably coupling the fuel reservoi...
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WO/2014/099530A1 |
A variable vane includes a variable vane body that has an airfoil portion. The variable vane body is formed of a first material. A trunnion is attached at one end of the variable vane body. The trunnion includes a pivot formed of a secon...
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WO/2014/098962A1 |
A method of configuring a plurality of gas turbine engines includes the steps of configuring each of the engines with respective ones of a plurality of propulsors. Each propulsor includes a propulsor turbine and one of a fan and a propel...
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WO/2014/099221A1 |
The speed of a high-pressure turbine of a gas turbine engine may be determined using known centrifugal pump affinity relationships for a fuel pressure apparatus, fuel pressure apparatus input and output pressures, and gear ratios for a m...
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WO/2014/096620A1 |
Turbomachine fuel circuit, this circuit comprising: - a fuel return valve (FRV) connected to the main fuel circuit (102) and to a tank (110), the valve (FRV) being able to adopt a first and a second open position, which are different fro...
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WO/2014/095237A1 |
The invention relates to a method for operating a gas turbine (10) which, upstream of the inlet of the compressor (12), has a device for cooling the air that can be drawn in by the compressor (12). To prevent step changes in the output g...
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WO/2014/100667A1 |
A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.
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WO/2014/093279A1 |
A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor ...
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WO/2014/086541A1 |
Gas turbine fuel supply method and arrangement It is described a method of controlling a supply of a fuel to a combustor of a gas turbine comprising a compressor upstream of the combustor, the method comprising: supplying the fuel (105) ...
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WO/2014/088671A2 |
A gas turbine engine variable bleed apparatus (48) includes a variable bleed valve door (50) disposed in a bleed inlet (47) in a transition duct (29), rotatable about two or more separate pivot points (160), operable to open and close an...
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WO/2014/086540A1 |
It is described a method of controlling a supply of a fuel (105) to a combustor (101) of a gas turbine comprising a compressor upstream of the combustor, the method comprising: supplying the fuel (105) to the combustor (101); obtaining a...
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WO/2014/085292A1 |
A system for diagnosing a rotating airfoil has an image capture device and a light emitting device. A control is programmed to actuate at least one of the image capture device and the light at a particular time to capture an image of a r...
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WO/2014/080758A1 |
The present invention resolves trouble caused by a difference in the temperature of different types of fuel gas. A power generation system (10) for using exhaust fuel gas (L3) emitted from an SOFC (13) as the fuel for the combustor of a ...
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WO/2013/025818A9 |
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...
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WO/2014/076400A1 |
The invention concerns an aircraft turbomachine computer comprising a parallelepiped metal housing (10) containing an electronic circuit incorporating a control channel and a monitoring channel. The housing (10) of the invention comprise...
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WO/2014/078221A1 |
A gas turbine engine has a compressor, a fan for delivering air into the compressor and into a bypass duct, a combustion section and a turbine section. A control for the gas turbine engine is programmed to change a fueling level and posi...
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WO/2014/072619A1 |
The invention relates to a method and to a device for determining, in real time, the flow rate of air collected from an aircraft engine (39) by a system (1) for collecting air from the engine, comprising: acquisition means (33) for acqui...
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WO/2014/073059A1 |
The purpose of the present invention is to provide gas turbine power generation equipment capable of suppressing missteps when an instantaneous voltage drop or other grid accident has occurred, in a local grid having naturally fluctuatin...
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WO/2014/074371A1 |
A system for providing fuel to a combustor assembly in a gas turbine engine includes a main fuel valve assembly a plurality of multi-stage combustor valve assemblies. Each multi-stage combustor valve assembly is provided for delivering f...
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WO/2014/071089A1 |
In one embodiment, a system includes at least one sensor configured to communicate a signal representative of a gas turbine operations. The system further includes a controller communicatively coupled to the sensor. The system additional...
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WO/2014/070630A1 |
A synchronization ring for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a synchronization ring for a variable vane assembly. A plurality of rollers are attached to the sync...
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WO/2014/066276A2 |
Electrical power systems, including generating capacity of a gas turbine, where additional electrical power is generated utilizing a separately fueled system during periods of peak electrical power demand.
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WO/2014/066210A1 |
A variable bleed valve (49) includes a variable bleed valve door (50) disposed in a bleed inlet (47) in transition duct (29) and rotatable about an axis (160) at or near a forward end (53) of door (50). Valve (49) is operable to open and...
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WO/2014/058710A1 |
A gas turbine engine has a fan which includes a plurality of fan blades that are rotatable about an axis, and a compressor section, where the combustor section includes a first compressor and a second compressor aft of the first compress...
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WO/2014/059000A1 |
An engine monitor includes a first tuned modeling unit, a second tuned modeling unit and a monitoring unit. The first tuned modeling unit models dynamics of a first engine by processing first control data with a first engine model to pro...
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WO/2014/053421A1 |
The turboexpander and driven turbomachine system comprises: a turboexpander (13) configured for expanding a first fluid and comprising an expander stage with one ex- pander impeller; a first set of moveable inlet guide vanes (23) at the ...
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WO/2014/053752A1 |
The invention relates to a method for monitoring a thrust fault of a turbofan during a modification of the thrust setting (NCONS) of said turbofan, said method comprising a step of processing the thrust setting (NCONS) by means of a filt...
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WO/2014/055104A1 |
A gas turbine engine design process includes the steps of determining the location of a hot streak downstream of a combustor nozzle, and determining whether it would be most beneficial to have the hot streak initially impact a pressure s...
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WO/2014/055124A1 |
A disclosed control system and method of controlling a gas turbine engine utilizes a thrust rating schedule generated from airframe selected requirements. The system utilizes a generic logic structure for ratings combined with simple sel...
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WO/2014/055751A1 |
An air bleed system for a gas turbine engine includes an annular bleed case with a manifold therein. The annular bleed case has a forward section and an aft section and ligaments connecting the two sections. The forward section, the aft ...
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WO/2014/052269A1 |
An example method of allocating power within a gas turbine engine includes driving an off-take power delivery assembly using a first amount of power from a spool, the first amount of power corresponding to an off-take power requirement o...
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WO/2014/051678A1 |
A gas turbine engine has a fan nacelle and a core nacelle arranged to provide a bypass flow path. A compressor section is provided within the core nacelle. A heat exchanger is arranged within a duct. The heat exchanger is configured to r...
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WO/2014/049260A1 |
The present invention relates to a method for differentiating control failures in a system for controlling an actuator (14) determining the position of a member for modifying the state of a gas-turbine engine, the system including a sing...
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WO/2014/052043A1 |
An example variable vane scheduling method includes adjusting variable vanes from a position based on a first schedule to a position based on a different, second schedule in response to a control feature. An example method of controlling...
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WO/2014/050163A1 |
This gas turbine cooling system (30) is equipped with: a cooler (31) that produces cooling air by cooling compressed air extracted from an air compressor (11); a cooling air compressor (34) that supplies the cooling air to a combustion t...
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WO/2014/046842A1 |
A nacelle assembly includes a thrust reverser moveable between a stowed position and a deployed position, a variable area fan nozzle, a motor to move the variable area fan nozzle, a drive shaft including a first portion coupled to the mo...
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