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WO/2019/243710A1 |
The invention concerns an assembly (22) comprising a fan drive reducing gear (20) of an aircraft turbine engine, and a lubrication system (24) comprising: - a housing (26) enclosing the reducing gear (20); - means (36) for spraying lubri...
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WO/2019/243074A1 |
The invention relates to a device (100) for desulfurizing natural gas, comprising a desulfurization system (102) for sour gas (101), which together with the desulfurized natural gas (103) forms a hydrogen sulfide-containing acid gas (104...
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WO/2019/242888A1 |
The gas turbine engine comprises a gas generator (66), comprised of a compressor section (11), and a power turbine section (65). The power turbine section (65) comprises a power turbine rotor (81) supported by a power turbine shaft (93),...
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WO/2019/239112A1 |
A combustion engine (10) comprises a radial compressor (16) in flow communication via a flow passage (22) with a compressor-combustor array (20) radially outward of the radial compressor (16), both rotatable around a central axis (12). T...
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WO/2019/223985A1 |
The invention relates to a power plant (1) comprising a compressor (2), a combustion chamber (3) and a turbine (4), further comprising a compressor air line (5), which connects the compressor (2) to the combustion chamber (3), a first he...
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WO/2019/222271A1 |
Embodiments described herein are directed to regulating pressure and/or fluid flow within a system. In one scenario, a system for regulating pressure includes a controller, a pneumatic pressure regulator with a dome that adjusts pressure...
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WO/2019/222702A1 |
A propulsion system includes a source of compressed fluid, at least one thruster in fluid communication with the source, at least one turbine in fluid communication with the source and coupled to a propeller, and an apparatus for selecti...
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WO/2019/207276A1 |
A combined heat and power system comprises a shaft (4), a compressor (6) coupled to the shaft to compress intake gas to form compressed gas; a recuperator (10) to heat the compressed gas to form heated compressed gas; a combustor (12) to...
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WO/2019/200975A1 |
A heavy-duty gas turbine, comprising a compressor (1), a variable-speed synchronous motor (2), a static excitation device (3), a variable-frequency power supply (4), a combustion chamber (5), a gas turbine (6), and a generator (7). The t...
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WO/2019/190802A1 |
This disclosure provides a cross key anti rotation spacer for use in a gas turbine engine (100). A compressor disk assembly (220) can have a cross key ring (240) having a plurality of keys (241), teeth, or castellations, alternating with...
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WO/2019/187782A1 |
A fuel gas cooling system and a gas turbine plant are provided with: a gas cooler (39) which performs cooling by causing cooling water (CW) to come into contact with compressed fuel gas (FC) serving as a fuel gas; a cooling water dischar...
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WO/2019/181877A1 |
This combustor (22) is provided with: a fuel supply section (35) defining on a radially inner side of an axis line (A) an inner periphery side space (34a) into which inert gas (E) is introduced and which supplies the inert gas (E) to a c...
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WO/2019/180253A1 |
An electronic control system (35) for a turbopropeller (2) having a gas turbine engine (20) and a propeller assembly (3) coupled to the gas turbine engine (20), the control system (35) having: a propeller control stage (35a), implementin...
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WO/2019/166040A1 |
Disclosed is a method for reducing contrails during operation of an aircraft (100, 100') having a heat engine (10). The method comprises: bringing about condensation of the moisture contained in the exhaust gas (A) of the heat engine by ...
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WO/2019/163664A1 |
The invention comprises: a first buffer tank (87) that accumulates, at a prescribed pressure, pressurized gas to be supplied to a powder supply hopper (80); a second buffer tank (88); a lower portion pressure regulation nitrogen system (...
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WO/2019/163955A1 |
A control device (100) for a two-shaft gas turbine power generation facility is provided with: a basic output calculation unit (110) which determines a basic output command value (Pb) corresponding to a required output (Pd); a component ...
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WO/2019/152879A2 |
A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine positioned within the housing and positioned so as to be contacted by the fluid expelled from the jet. The fluid causes the turbine to...
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WO/2019/135996A1 |
Disclosed is a novel device that converts some of the power in ocean waves into electrical power or other means of performing useful work. One or more tubes are arranged so that when the device is in position in a body of water, the tube...
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WO/2018/205889A9 |
In a combustor (10) for a gas turbine, a head end turning scoop (12) is provided associated with at least one premix nozzle (22,24), each scoop (12) being U-shaped and having a first leg (58), a second leg (60), and a curved base portion...
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WO/2019/104614A1 |
Disclosed is an oxidant-mutifuel burner capable of being used for solid fuel and gas fuel, the burner including: a flameproof unit (10), a metal member (20), a fuel-oxidant supply system (11) including a fuel burner and several fuel-oxid...
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WO/2019/104375A1 |
The present invention in one aspect is directed to an autonomous vehicle energy replenishment system (10) comprising: 1. a source of renewable ammonia (14); 2. an electricity generating module (16) operatively coupled to and fuelled by a...
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WO/2019/104417A1 |
A gas turbine engine, with a conical screw integrated compression system, that utilizes at least one conical screw as an intermediary fluid transport device to facilitate the multi-staging of non-axial compressors, such as centrifugal an...
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WO/2019/102156A1 |
The autonomous device (100) for providing electricity comprises: a storage tank (105) for liquefied natural gas (hereinafter "GNL") comprising a GNL supply inlet (110), a means (115) for the combustion of GNL provided by the storage tank...
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WO/2019/098836A1 |
When the temperature of ambient air is relatively low, thermal output and thermal efficiency of a micro gas turbine (1) decrease. In order to compensate for the loss of thermal efficiency, the micro gas turbine (1) is equipped with a val...
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WO/2019/088107A1 |
Provided are a combustor and a combustion method with which it is possible to inhibit generation of nitrogen oxides. A combustor (10) provided with: a first wall (13A) forming a combustion chamber (12); a fuel injection nozzle (11) which...
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WO/2019/084208A1 |
A bottoming cycle power system includes an expander disposed on a crankshaft. The expander being operable to receive a flow of exhaust gas from a combustion process and to rotate the crankshaft as the exhaust gas passes through. An absor...
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WO/2019/063635A1 |
The invention concerns a turbine exhaust casing (TEC) for a gas turbine engine in which portions of the inner surface of the casing against which exhaust gas flows are provided with recesses extending into the surfaces. The recesses are ...
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WO/2019/059888A1 |
An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives...
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WO/2019/057512A1 |
A gas turbine engine system is equipped with a tempering system for a selective catalyst reduction system. The subject tempering system for a selective catalyst reduction system comprises a tempering compartment equipped with a plurality...
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WO/2019/045997A1 |
A disc turbine engine with a multi disc engine where each disc engine includes a turbine blade, a low-pressure compressor blade, a high-pressure compressor blade, and a bearing. Each disc engine runs freely and individually, counter-rota...
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WO/2019/043556A1 |
The present disclosure provides systems and methods for power production. In particular, the systems and methods utilize the addition of heat to an expanded turbine exhaust stream in order to increase the available quantity of heat for r...
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WO/2019/037816A1 |
The invention relates to a jet engine, which has a stationary housing, in which housing a primary flow is formed, in which inflowing air is burned in at least one combustion chamber, and in which housing a secondary flow is formed, in wh...
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WO/2019/035774A1 |
A chamber rotary combustion engine constituted by a static and a moving part, wherein the static part is formed by an engine block with a cylindrical annulus case (1), a casing (2) with openings (2a), wherein the bearings (3) for mountin...
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WO/2019/015925A1 |
The invention relates to a method for improving the performance of a gas turbine (1), in which a hub (6) annually surrounding a rotor (2) is machined when the rotor (2) is in the non-stacked state and hot shield elements that are arrange...
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WO/2019/006352A1 |
Effluent water is combined with carbon dioxide sourced from a carbon dioxide- containing emission stream to produce a reaction solution. The pH of the reaction solution is controlled to induce precipitation of a carbonate salt from the r...
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WO/2018/236838A2 |
The disclosed embodiments concern methods, apparatus, and systems for providing differential diagnosis of autoimmune diseases including, Systemic Lupus Erythematosus (SLE) and Rheumatoid Arthritis (RA). The disclosed embodiments provide ...
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WO/2018/236449A1 |
The present invention is a centrifuge to be used for removing ice particles from the air fed to a gas turbine system. In an embodiment, the centrifuge is comprised of three ducts defining an air-path which comprises of two bends greater ...
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WO/2018/234684A1 |
This arrangement comprises two turboshaft engines (10, 20) interwoven so as to exchange thermal energy by heat exchangers (16, 26) which improve their efficiency, without greatly increasing head losses since the pipes (19, 29) imposed to...
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WO/2018/225923A1 |
A combined power generation apparatus, according to the present invention, comprises: an engine (110); a first flow line (120); a power turbine (113); a turbo charger (115); a second flow line (125); a third flow line (126); a compressor...
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WO/2018/225922A1 |
A combined power generation apparatus, according to the present invention, comprises: an engine (110); a first flow line (121); a turbo charger (130); a second flow line (122); a third flow line (123); a compressor (211); a first medium ...
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WO/2018/222734A1 |
Thermal energy storage systems and methods are provided including a bed, a blend of aggregates packed in the bed, and a high-density heat transfer fluid flowing through the blend of aggregates. The blend of aggregates includes rock mater...
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WO/2018/222192A1 |
An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, wh...
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WO/2018/219254A1 |
A heat pipe engine, comprising a housing (1), a shaft sleeve (4) disposed in the middle of the housing and fixedly connected with the housing, a spindle (5) disposed in the shaft sleeve through a bearing, and a combustion chamber (6) dis...
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WO/2018/203941A2 |
A turbocharged gas turbine engine with an electric generator to provide electrical power for an aircraft (e.g., UAV) with multiple propulsor fans each driven by an electric motor, where the engine includes a low spool that drives a main ...
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WO/2018/198932A1 |
A shaft 13 for turbo chargers comprises a low-strength section 25 set to a breaking strength at which same breaks when a preset prescribed load is applied, said section being in an area between a compressor-side bearing 15 and a compress...
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WO/2018/197856A1 |
The present invention is related to a multiple-inlet turbine casing (16) for a turbine rotor (60) which comprises a first fluid supply channel (70) configured to direct a first working fluid onto the turbine rotor (60) and a second fluid...
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WO/2018/187731A1 |
Re-lithiation methods and systems are disclosed. Example re-lithiation methods include separating lithium depleted active cathode material from a cathode and introducing lithium containing materials. Also disclosed are re-lithiation elec...
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WO/2018/186925A2 |
The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine...
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WO/2018/180773A1 |
Provided is a combustion device equipped with: an ammonia supply unit (6) that, by supplying primary reduction ammonia as a nitrogen oxide reducing agent to within a combustor (2) and mixing secondary reduction ammonia with combustion ex...
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WO/2018/181063A1 |
This combustion device (C) causes the combustion of fuel ammonia and combustion air within a combustion chamber (N), and is equipped with a combustor liner (3a) which forms the combustion chamber, a burner (3c) which is attached to one e...
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