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Patent Searching and Data


Matches 451 - 500 out of 8,874

Document Document Title
WO/2014/147738A1
A gas turbine power generation system is characterized by comprising: a gas generator that has a compressor, a high-pressure turbine, and a combustor; a power turbine that has a low-pressure turbine and a power generator; a motor-generat...  
WO/2014/151673A1
A gas turbine engine includes an aerodynamic track fairing adjacent to a convergent- divergent nozzle, the aerodynamic track fairing including a localized curvature along an outside edge. The aerodynamic track fairing is configured to of...  
WO/2014/143218A1
One embodiment of the present disclosure is a unique gas turbine engine. Another embodiment of the present disclosure is a unique machine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for g...  
WO/2014/143219A1
A control for a turbine engine using electrical machines monitors engine health and allocates power extraction between the electrical machines.  
WO/2014/105232A3
A gas turbine engine inlet sensor fault detection and accommodation system comprises an engine model, an engine parameter comparison block, an inlet condition estimator, control laws, and a fault detection and accommodation system. The e...  
WO/2014/141830A1
Provided is a fuel spray nozzle provided with: a liquid fuel channel (15) which is a channel for liquid fuel; a liquid fuel injection hole (19) which is a hole for communicating the liquid fuel channel (15) and the inside of a combustion...  
WO/2014/143189A1
A turbine engine includes a compressor, and high and low pressure turbines. The configuration includes a mid-compression station which can be, in the case of a single compressor in the middle of that compressor, or at the exit of the fir...  
WO/2014/143187A1
A control for a multi-shaft turbine engine system using electrical machines seeks optimal system performance while accommodating hard and soft component limits. To accommodate the component limits, the control may generate a number of po...  
WO/2014/140460A1
A dosing device for an engine fuel supply circuit comprising a dosing valve (21), and a pressure control device keeping a constant pressure differential between the downstream and upstream of the dosing valve (21), in which the dosing va...  
WO/2014/135797A1
The invention concerns a fuel dosing device (10) for a fuel injector of an aircraft turbomachine, comprising an opening (24), a movable member (28) for sealing the opening, and elastic return means (60a, 60b), the member being capable of...  
WO/2014/138340A1
A fuel injector (50) for a gas turbine engine (10) may include a flow path for a fuel-air mixture extending longitudinally through the fuel injector, and a fuel gallery (62) extending circumferentially around the flow path. The fuel gall...  
WO/2014/138320A1
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a varia...  
WO/2014/137456A1
One example of a gas turbine engine may include a gas generator, a reheat combustor that is disposed downstream of the gas generator, and a power turbine that is disposed downstream of the reheat combustor and includes a plurality of noz...  
WO/2014/088671A3
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...  
WO/2014/105231A3
A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to estim...  
WO/2014/137505A1
A system (36) is provided that includes a memory (37) storing a turbomachinery degradation model configured to model degradation of a turbomachinery over time. The system also includes a controller (38) communicatively coupled to the mem...  
WO/2014/135942A1
A device for protecting aircraft equipment against contact by a foreign object including an interference arrangement disposed in an air inlet upstream from the aircraft equipment where the interference arrangement is configured to physic...  
WO/2014/113120A3
A gas turbine system includes a controller (118) configured to receive fuel composition information related to a fuel (70) used for combustion in a turbine combustor (160); receive oxidant composition information related to an oxidant (6...  
WO/2014/134134A1
An anti-surge mechanism has a duct for tapping compressed air and delivering that air into an exhaust flow. A selectively open valve allows the tapped air to flow into the exhaust flow through a plurality of holes. The holes are sized to...  
WO/2014/133601A1
One embodiment of the present disclosure is a unique method for operating a gas turbine engine during flight operation of the gas turbine engine in an aircraft. Another embodiment of the present disclosure is a unique gas turbine engine....  
WO/2014/133724A1
A variable vane actuator assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a plurality of vanes. A synchronization rings surrounds and is mechanically linked to dri...  
WO/2013/123008A8
A component for a gas turbine engine includes a gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an i...  
WO/2014/132932A1
Provided are a gas turbine system, a controller, and a gas turbine operation method, whereby the combustion gas temperature of a gas turbine can be controlled with higher precision. The gas turbine system has: a gas turbine having a comp...  
WO/2014/099077A3
A gas turbine engine includes a multiple of Nozzle Guide Vanes (NGVs) arranged asymmetrically and a multiple of NGVs clocked with respect to the multiple of fuel nozzles around a 360 degree circumference.  
WO/2014/133938A1
A stator vane for a gas turbine engine includes a first platform and a second platform radially spaced apart from one another. The first and second airfoils are circumferentially spaced from one another and interconnect the first and sec...  
WO/2014/130027A1
Contemplated configurations and methods are presented for effectively controlling the temperature in an oxy-fuel combustion system. Contemplated systems preferably introduce water independent of the fuel and oxygen into the combustion ch...  
WO/2014/129458A1
A gas turbine system equipped with a gas turbine (10) and a combustor control device (11). The gas turbine (10) is equipped with a combustor (12) having a pilot nozzle (13), first main nozzles (14), and second main nozzles (15). The comb...  
WO/2014/128112A1
The invention refers to a plant with a fuel system comprising a gas separation system (16), for separating at least a first fuel fraction (14) with high hydrocarbons, which has a higher concentration of high hydrocarbons than an incoming...  
WO/2014/129226A1
A method for controlling a lean fuel suction gas turbine engine (GT), which is equipped with a catalytic combustor (3) that burns a compressed gas compressed by a compressor (1) and supplies the burned gas to a turbine (5), and a heat ex...  
WO/2014/128124A1
The invention refers to a method for operating a gas turbine plant. According to the method a first fuel gas (5) with a first fuel reactivity and a second fuel gas (14) with a second fuel reactivity which is higher than the first fuel re...  
WO/2014/128039A1
The invention relates to a method for operating a gas turbine (10) below the nominal power thereof, comprising the following steps: determining a lower power threshold value (P1@TATK=const. ) of the gas turbine (10) as the power threshol...  
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...  
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...  
WO/2014/099071A3
A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to gener...  
WO/2014/099075A3
A combustor of a gas turbine engine includes a multiple of fuel nozzles arranged asymmetrically.  
WO/2014/105237A3
A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core engine section includes a primary nozzle inclu...  
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...  
WO/2014/099074A3
A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.  
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...  
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...  
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...  
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...  
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...  
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 ...  
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...  
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.  
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 ...  
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...  
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...  
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...  

Matches 451 - 500 out of 8,874