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WO/2014/200582A1 |
A method and apparatus of using cryogenic fuel (12) in an engine (101) for an aircraft (5) wherein the cryogenic fuel (12) is supplied to the engine for combustion.
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WO/2014/200830A1 |
A flow control device for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner surface and a radially outer surface and at least one stand-up pr...
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WO/2014/200597A2 |
Advanced gas turbines and associated components, systems and methods are disclosed herein. A gas turbine configured in accordance with a particular embodiment includes a rotor operably coupled to a shaft and a stator positioned adjacent ...
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WO/2014/196985A1 |
A turbofan engine having a thrust reverser having at least one movable control surface, movable to and from a reversing position where at least a portion of the bypass air flow is at least partially reversed, a thrust reverser actuation ...
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WO/2014/189568A2 |
An example section of a gas turbine engine includes a plurality of variable vanes circumferentially disposed about an engine axis, a first moveable annular ring disposed on an upstream side of the variable vanes, a second movable annular...
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WO/2014/189574A2 |
A method of controlling a variable vane assembly includes the steps of sensing a first angular deflection of a first array of variable vanes about a first vane axis, and a second angular deflection of a second array of variable vanes abo...
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WO/2014/188245A2 |
Provided is a turbine housing of a turbosupercharger provided in an exhaust passage of an internal combustion engine, in which the turbosupercharger has a turbine wheel provided in the exhaust passage, and an outlet of the turbine housin...
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WO/2014/189694A1 |
A turbomachine assembly (102) has a compressor section (202) including a first end (208) of a rotating member (206) and a first cover (218) configured to substantially enclose the first end therein. The compressor section includes a bypa...
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WO/2014/186146A1 |
A liquid gallery for a fuel injector of a gas turbine engine includes a gallery body, a liquid gallery scroll, a plurality of atomizer inlets, and a plurality of atomizer bosses. The liquid gallery scroll extends into the gallery body sp...
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WO/2014/186149A1 |
An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection port...
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WO/2014/186148A1 |
A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from th...
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WO/2014/182616A2 |
Embodiments are directed to selecting, by a computing device comprising a processor, the size of at least one prime mover associated with an aircraft to satisfy a baseline power requirement for operation of the aircraft during a steady s...
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WO/2014/182507A1 |
A swirler inlet valve plate for a fuel injector of a gas turbine engine includes a blocker ring and a pivot sleeve mechanically connected to the blocker ring. The blocker ring is formed from at least a portion of a toroid shape. The bloc...
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WO/2014/175404A1 |
This IGCC plant is provided with a coal gasification furnace which uses an oxidizing agent to gasify coal, a gas turbine which is driven by the combustion gas resulting from burning a fuel gas obtained by refining, in gas refining equipm...
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WO/2014/174208A1 |
The method according to the invention comprises, during a phase (EO) of starting up the turbomachine : — a step (E10) of open-loop generation of a control (WF_OL) of the flow of fuel based on at least one pre-established law; and — a...
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WO/2014/170058A1 |
The present invention relates to a method for providing negative control power for an electrical supply and/or transmission network by means of the operation of a gas turbine (1), comprising the following steps: a dynamo-electric machine...
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WO/2014/166671A1 |
A method for reducing the CO emissions of a gas turbine (1), having a compressor (6), having a turbine (10) and having an air preheater (22) positioned upstream of the compressor (6), is intended to permit technically simpler regulation ...
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WO/2014/161661A1 |
The invention relates to a method for operating an internal combustion engine in a combined heat and power generation system (1) and to a combined heat and power generation system (1) comprising an internal combustion engine of this type...
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WO/2014/165364A1 |
A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes ...
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WO/2014/158307A2 |
A filter algorithm for a dual channel electronic engine control system according to one disclosed non-limiting embodiment of the present disclosure includes a division function that divides a measured pressure rate of change of one of a ...
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WO/2014/158335A1 |
A system includes a controller configured to control an operational behavior of a turbine system. The controller includes a droop response system configured to detect one or more operational characteristics of the turbine system as an in...
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WO/2014/158238A1 |
Control systems and methods for an aircraft propulsion system are disclosed in which the propulsion control system (140) is integrated to intelligently control aircraft propulsion and minimize transient effects from the power demands of ...
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WO/2014/159504A1 |
A bleed valve assembly according to an exemplary aspect of the present disclosure includes, among other things, a bleed adaptor having an inlet portion, a fitting opposite the inlet portion, an adaptor body that extends between the inlet...
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WO/2014/158455A1 |
An exemplary variable vane actuation system includes, among other things, a vane arm with a vane stem contact surface and a radially outward facing surface. The vane stem contact surface is to contact a vane stem of a variable vane and t...
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WO/2014/150377A1 |
A system and method for implementing stage-by-stage counter rotation in a multi-stage axial compressor of a gas turbine engine. The system includes an electrical power generator and an electric motor (2). A turbine-driven shaft (3) conne...
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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...
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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...
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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...
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WO/2014/143219A1 |
A control for a turbine engine using electrical machines monitors engine health and allocates power extraction between the electrical machines.
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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....
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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