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WO/2024/100353A1 |
The invention relates to an aero-propulsion system (1) having a thrust density per blade (14) of the fan rotor (9) greater than or equal to 1.40 x 105 and less than or equal to 1.70 x 105 N/m2, wherein the thrust density per blade (14) i...
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WO/2024/100356A1 |
An aeronautical propulsion system (1) comprises a drive turbine (8), a fan rotor (9) and a reduction mechanism (19) coupling the shaft (11) of the drive turbine (8) and the shaft (20) of the fan rotor (9). A rotational speed of the drive...
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WO/2024/100354A1 |
The invention relates to an aero-propulsion system (1) having a thrust density per blade (14) of the fan rotor (9) greater than or equal to 5.0 × 104 and less than or equal to 10.0 × 104 N/m2, wherein the thrust density per blade (14) ...
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WO/2024/100355A1 |
An aeronautical propulsion system (1) has a mean internal radius of the high-pressure turbine (7) at least equal to formula (I), where: Rmoyen'int is the mean internal radius of the high-pressure turbine (7) in millimeters (mm); D is the...
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WO/2024/100986A1 |
This carbon dioxide recovery system comprises: an iron-making facility; a gas turbine which drives a turbine by means of a combustion gas generated by burning a first gas discharged from the iron-making facility; a heat exchanger for exc...
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WO/2024/095638A1 |
A gas turbine system 100 comprises: an ammonia supply source 1; a gas turbine 4 including a combustor 42 that is connected to the ammonia supply source 1 and that burns ammonia from the ammonia supply source 1; a water electrolysis devic...
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WO/2024/090092A1 |
This combustion system (100) is provided with: an ammonia supply source (1); a cracking device (3) which is connected to the ammonia supply source (1) and decomposes ammonia into hydrogen and nitrogen; a combustor (42) which is connected...
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WO/2024/088557A1 |
The present invention relates to a method for providing heat using a furnace arrangement (100) comprising a first furnace zone (110) a first heat transfer arrangement (130) arranged downstream of the first furnace zone (110), a second fu...
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WO/2024/084168A1 |
The invention relates to a device (B) for regulating a system (A) for supplying hydrogen to a turbine engine comprising a combustion chamber, the hydrogen supply system comprising, in particular arranged in series, at least: - a pressuri...
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WO/2024/083502A1 |
The invention relates to a fuel conditioning system (SC) configured to power an aircraft turbomachine (M) with fuel (Q) from a cryogenic tank (R), the conditioning system (SC) comprising: a fuel circuit (1); a distribution valve (5) conf...
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WO/2024/078930A1 |
A fuel conditioning system (SC) configured to supply an aircraft turbine engine with fuel (Q) coming from a cryogenic tank (R), the conditioning system (SC) comprising: a fuel circuit (1); a first heat module (31) mounted in an aircraft ...
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WO/2024/068198A1 |
A system (1) for producing ammonia comprises an ammonia reactor (44) which is designed to produce ammonia (NH3) from a synthesis gas, the synthesis gas comprising hydrogen (H2) and nitrogen (N2), and the system also comprises an electrol...
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WO/2024/073341A1 |
A stator vane is provided. The stator vane including an airfoil that has a nominal suction-side profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in Table I. The Cartesian coordina...
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WO/2024/072881A1 |
An apparatus includes an electric generator that includes a fluid inlet configured to receive hydrogen at a first pressure, a turbine wheel configured to expand the hydrogen and rotate in response to expansion of the hydrogen flowing int...
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WO/2024/061558A1 |
A gas turbine engine has a core flow path and an outer flow path, the outer flow path positioned at a greater radial displacement from a rotational axis of the engine than the core flow path. The gas turbine engine also has a cavity to p...
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WO/2024/059468A1 |
Liquid fuel systems and methods are provided. A liquid fuel system includes a mixing unit and a plurality of liquid fuel supply systems. Each liquid fuel supply system is fluidly coupled to the mixing unit. The liquid fuel system further...
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WO/2024/057775A1 |
An aircraft engine combustor equipped with a cylindrical member for demarcating an internal space which extends along an axis, and a fuel nozzle which is positioned in a manner such that at least a part thereof is positioned inside the i...
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WO/2024/054836A1 |
A dual-fuel turbine engine is a type of turbine engine that can operate using two different fuel sources, such as liquid fuel (e.g., diesel) and natural gas. For liquid fuels, the turbine engine includes a primary line to facilitate engi...
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WO/2024/052725A1 |
A method and disc that gasifies and pressurizes liquid propellants for use in rocket propulsion systems. The method involves the following steps: a) Increasing the tangential kinetic energy and pressure of liquid propellants by driving t...
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WO/2024/043268A1 |
This gas turbine is provided with a combustor which can switch a fuel to be combusted between an ammonia fuel and a hydrocarbon-based fuel. The combustor has: a cylindrical body which has a cylindrical shape and through which a combustio...
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WO/2024/044260A2 |
An oxy-fuel combustion gas generator combusts fuel with oxygen to produce high temperature steam and carbon dioxide. A lithium brine is introduced into the gas generator to cause at least a portion of the water within the lithium brine t...
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WO/2024/042343A1 |
A turbine engine is disclosed, which comprises a first electric machine coupled to a low pressure shaft of the turbine engine and a second electric machine coupled to a high pressure shaft of the turbine engine. The turbine engine includ...
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WO/2024/039365A1 |
A system includes a gas treatment system having first and second gas capture systems and a steam supply circuit. The first gas capture system is configured to capture a first portion of an undesirable gas from a combined cycle power plan...
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WO/2024/032933A1 |
A fuel gas booster-gas turbine integration for energy saving & optimized operability is disclosed. The fuel gas booster-gas turbine integration comprises an integrated system comprising a reciprocating compressor based fuel gas booster (...
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WO/2024/034367A1 |
This suction heating system is configured to heat outside air fed to a compressor of a gas turbine. The suction heating system is provided with a suction heating unit configured to heat outside air using a heat source different from that...
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WO/2024/033588A1 |
The invention relates to an aircraft turbine engine (10) having: - a compressor (14), - an annular combustion chamber (24), - a system (32) for diffusing and straightening an air stream exiting the compressor in order to supply the combu...
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WO/2024/034366A1 |
This intake air heating system is configured so as to heat external air flowing in an intake air flow path communicated with a compressor of a gas turbine, the intake air heating system comprising: a first heating unit that includes a re...
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WO/2024/023413A1 |
Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21...
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WO/2024/023445A1 |
Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbines (11, 2...
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WO/2024/018137A1 |
The invention relates to a hybrid propulsion system (2) comprising: a turbine engine (3) comprising a high-pressure spool (4) and a low-pressure spool (5), the low-pressure spool (5) comprising reduction gear (11), the reduction gear (11...
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WO/2024/020605A1 |
An energy generating system (10) includes: (i) a first conduit (14) for conveying air there along, which first conduit defines: a first conduit inlet for receiving air; and a first conduit outlet (14a) for discharging air; (ii) a turbine...
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WO/2024/018169A1 |
A process for providing heat energy to an ammonia cracking reactor. The invention comprising recovering an oxygen containing off-gas from a hydrogen fuelled gas turbine and supplying at least a portion of the off-gas to a fuel combustion...
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WO/2024/014349A1 |
A fuel supply apparatus comprising: a water electrolysis device; a dehumidifier that is provided in a hydrogen line through which hydrogen from the water electrolysis device flows, and includes an adsorbing material for adsorbing water c...
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WO/2024/015292A1 |
Systems and methods are provided for operating a combined cycle power plant while enhancing the CO2 content of the flue gas generated by the power plant. The CO2 content is enhanced by using a combination of exhaust gas recycle and oxyge...
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WO/2024/012715A1 |
An energy conversion plant is disclosed, having one or more driving units, for driving respective loads, such as an electric motor or a centrifugal compressor. The energy conversion plant comprises at least one heat exchange recuperator,...
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WO/2024/012909A1 |
A gear changing system for the driving of an apparatus by an accessory gearbox comprising: a train comprising a ring gear (5), a planetary gear (6) integral with an output shaft (4) and a planet carrier (7) integral with an input shaft (...
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WO/2024/009715A1 |
A gas turbine system (1), including a gas turbine engine (3) having a compressor (11), a combustor (13), and a turbine (15), and a fuel gas pressure adjustment device (5) that adjusts the pressure of the fuel gas (F) introduced into the ...
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WO/2024/008698A1 |
The invention relates to a system (1) for heating a fuel for supplying an aircraft turbine engine (M), the heating system (1) comprising a fuel circuit (2); at least one first heat exchanger (41) configured to be mounted in an inner duct...
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WO/2024/003083A1 |
The invention concerns an aircraft fuel heating arrangement comprising an exhaust cone for a gas turbine engine, the exhaust cone having an outer body defining an internal cone cavity, the internal cone cavity comprising one or more cond...
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WO/2024/003641A1 |
A propulsor fan and drive system having reduced noise emission is disclosed. The propulsor fan includes a blade fan having a plurality of blades. The blades may include a dual pin-root design to secure the blade fan to a hub and a shroud...
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WO/2024/006201A1 |
A combined cycle power plant (100) including a gas turbine engine (102) having a compressor inlet (106) and a turbine outlet (110) that is configured to discharge a first exhaust gas stream (120) therefrom. A heat recovery steam generato...
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WO/2024/001147A1 |
A ventilation control system of a rotor supercharged gas turbine, the ventilation control system comprising an air compressor (8), a rotor housing (23), a rotor (48) in the rotor housing, and a turbine (9), wherein the rotor housing is p...
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WO/2023/249660A1 |
An integrated hydrogen-electric engine includes, an air compressor system; a hydrogen fuel source; a fuel cell; an elongated shaft connected to the air compressor system or a propulsor; and a motor assembly disposed in electrical communi...
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WO/2023/247626A1 |
The invention relates to a device (5) for providing electrical energy by means of a hydrogen carrier medium, the device comprising: a dehydrogenation unit (9), which has a first dehydrogenation reactor (56), for releasing hydrogen gas fr...
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WO/2023/246980A1 |
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) having a core flow channel (10), wherein a compressor (12), a combustion chamber (13), a first turbine, in particular a high-pressure turbine ...
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WO/2023/249815A1 |
A thermal power plant comprising: at least ah expander system, an energy-supply fluid, an energy-receiving fluid, and a direct-contact heat and mass exchanger, said exchanger facilitating heat and mass transfer from said energy-supply fl...
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WO/2023/246979A1 |
A method (100) for operating an aircraft-engine turbomachine (1) having a compressor (3), through which a gas flow (6) passes in a flow direction, a combustion chamber (4), a turbine (5) and a heat exchanger (8) downstream of the turbine...
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WO/2023/249659A1 |
An integrated hydrogen-electric engine including an air compressor system, a hydrogen fuel source, a fuel cell, a heat exchanger, an elongated shaft, a motor assembly and a combustion chamber including a turbine downstream of the fuel ce...
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WO/2023/242081A1 |
The invention relates to an adapter (1; 1a) for a device for introducing a fuel necessary for operating a prime mover or a heater (20) into a receiving space (22) in the prime mover or heater (20) intended therefor. The adapter (1; 1a) i...
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WO/2023/240377A1 |
An aerospace low-noise engine, comprising a housing (1). The middle of the left side of the housing (1) is fixedly connected to a spiral shaft (2), and an inner wall of the spiral shaft (2) is fixedly connected to a noise reduction devic...
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