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WO/2022/111273A1 |
A liquid air-based power generation system, and a method. The power generation system comprises a liquid air treatment unit (100), a gas turbine power generation unit (200), and a steam turbine power generation unit (300). In a period of...
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WO/2022/113483A1 |
This seal device comprises: a movable seal ring arranged so as to be deformable in the radial direction, in a state of facing an outer peripheral surface of a rotor of a steam turbine capable of rotating around the axis; a first elastic ...
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WO/2022/112713A1 |
The invention relates to an actuating device (12) of a fuel pump (20) for an aircraft engine (18), the actuating device (12) comprising a motor (24), a generator (26) and an electrical connection member (27), the motor (24) being an asyn...
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WO/2022/112536A1 |
An engine comprises an air inlet configured to receive air; a first heat exchanger arrangement arranged downstream of the air inlet, having a first heat exchanger inlet configured to receive at least a portion of the air received by the ...
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WO/2022/105206A1 |
A multi-thrust-plate gas turbine capable of balancing an axial force, the gas turbine comprising a rotating shaft (1), and a gas compressor (2), a front radial bearing (61), a plurality of thrust plates (11), a thrust bearing (62), a rea...
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WO/2022/105215A1 |
A motor-embedded bearing type micro gas turbine, comprising a rotor system, a motor casing (810), a gas turbine casing (820) and a combustion chamber (830); the rotor system comprises a rotating shaft (100); a thrust bearing (200), a fir...
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WO/2022/104988A1 |
The present invention provides a cabin for a turbine engine, comprising a main cabin for accommodating the turbine engine and an air intake cabin arranged on one side of the main cabin. The air intake cabin comprises: an air intake cabin...
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WO/2022/105213A1 |
A multi-rotor micro gas turbine comprising an air inlet channel (4), a compressor (1), a combustion chamber (5), a turbine (2), a rotating shaft (3), a free turbine (18), a motor (19), an exhaust passage (7), a free casing (17), a free r...
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WO/2022/105212A1 |
A gas-blown miniature gas turbine, comprises a gas compressor (1), a turbine (2), a rotating shaft (3), a gas inlet channel (4), and a combustion chamber (5). The gas compressor (1) and the turbine (2) are sleeved on the front end and ta...
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WO/2022/109512A1 |
The present disclosure presents improved combustion turbine engine systems and related methods. One such system includes a turbine system comprising a high pressure compressor, a high pressure turbine, a combustor, and a recuperator. The...
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WO/2022/107734A1 |
A rotation unit constituent member (1), which is a constituent member of a gas turbine (GT) engine, is provided with: a rotation unit constituent member body (15) that is made of metal; and a hard particle layer (17) that includes a larg...
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WO/2022/105214A1 |
A dual-shaft power generation gas turbine, comprising a first rotor system and a second rotor system. The first rotor system comprises a first rotating shaft (100), a first motor (200), a compressor (300), a first turbine (400) and a com...
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WO/2022/106237A1 |
Disclosed is a main shaft (1) for an aircraft turbine engine drive line (A) extending longitudinally from front to rear along an axis (X) and comprising a rear portion (10) configured for receiving a front portion (20) of a rear shaft (2...
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WO/2022/103585A1 |
A compact heat exchanger (170) is disclosed for re-circulating bleed air from a combustor into an inlet (110) and/or exhaust (150) of a gas turbine engine (100). In an embodiment, the heat exchanger (170) may comprise a plurality of airf...
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WO/2022/100891A1 |
The invention relates to an aircraft comprising a display screen (7) and at least one turbomachine (2), each turbomachine (2) comprising a motor (10), the aircraft (1) comprising the following elements associated with each turbomachine (...
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WO/2022/101608A1 |
System comprising a gas turbine engine fuel injection apparatus (11) arranged to deliver to a combustion chamber (9) of a gas turbine engine a first injection fluid comprising a first fuel and a second injection fluid comprising a second...
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WO/2022/101756A1 |
This invention is specifically intended to generate electricity based upon management of power plants with frozen cooled dry gas system driven by kinetic energy. This is done according to a different engineering system for common power p...
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WO/2022/100150A1 |
A high-rotation-speed oil-gas separator for a turbine engine, the oil-gas separator comprising a hollow rotating shaft (77), wherein the upper portion of the rotating shaft (77) is provided with an oil input cavity assembly; the upper mi...
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WO/2022/100169A1 |
Disclosed is a creep-resistant, long-service-life, nickel-based deformation superalloy, comprising: C: 0.04-0.08%; Cr: 18.50-21.50%; Co: 9.00-11.00%; Mo: 8.00-9.00%; Al: 2.00-3.00%; Ti: 1.10-1.49%; Nb: 0.81-2.00%; B: 0.003-0.009%; Sc: 0....
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WO/2022/101570A1 |
The invention relates to a turbomachine (10) comprising a propeller (12), a propeller shaft (13) carrying the propeller (12), a rotating electric machine (19), having at least a first configuration in which it is mechanically coupled to ...
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WO/2022/100089A1 |
A multi-fuel combined cooling, heating and power system, comprising a multi-fuel micro gas turbine (1); the multi-fuel micro gas turbine (1) comprises a heat regenerator (101) and a combustion chamber (105); hollow evaporation pipes (14)...
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WO/2022/101166A1 |
A guiding array (200; 600) for a flow duct system (100; 200; 300; 500) includes a series of internested annular guide vanes (202), leading edges (230) or other common parts of the guide vanes being arranged to be positioned different dis...
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WO/2022/100087A1 |
A micro gas turbine combined circulation system, comprising a micro gas turbine (1); said combined circulation system further comprises at least one of a fuel cell system (2), a steam power generation system and a solar receiver; the mic...
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WO/2022/101586A1 |
A turbomachine (10), in particular for a rotary-wing aircraft, having a gas generator (13) provided with a rotary shaft (18), a reversible first electric machine (11), a free turbine (12) driven in rotation by a flow of gas generated by ...
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WO/2022/096359A1 |
Disclosed is an air intake (1) for an aircraft propulsion assembly (8) extending along a longitudinal axis (X) and comprising a turbine engine (7) that comprises a primary flow path (4) and a secondary flow path (5) for respectively guid...
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WO/2022/096814A1 |
Disclosed is an aircraft turbomachine (10) having a longitudinal axis (A) and comprising: a high-pressure body, termed HP body, a low-pressure body, termed LP body, a fan (48), and a reduction gear (36) having an epicyclic gear train; th...
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WO/2022/096813A1 |
A set of shafts (34, 72) for an aircraft turbomachine, this set comprising: a first shaft (72) having external splines (76) oriented parallel to an axis of rotation (A) of the shaft, a second shaft (34) having internal splines (74) compl...
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WO/2022/091273A1 |
This aircraft compressed air supply system comprises: a bleeding air passage through which bleeding air from a gas turbine engine flows; an auxiliary compressor having a compressor inlet and a compressor outlet fluidly connected to the b...
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WO/2022/090661A1 |
Disclosed is a turbogenerator (10), in particular for an electrically-driven rotary wing aircraft, comprising a gas generator (13) provided with a first shaft (18), at least one reversible electrical machine (11), and a free turbine (12)...
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WO/2022/090207A1 |
Device (50) for filtering air intended to supply an air system of an air-transport vehicle, rail vehicle or motor vehicle, characterized in that it comprises a porous three-dimensional structure (52) comprising at least one portion inten...
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WO/2022/094205A1 |
A dual drive hybrid electric power plant to power an aircraft comprises a propulsion assembly, an internal combustion engine having an output shaft configured to drive the propulsion assembly, and an electric motor configured to drive th...
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WO/2022/091274A1 |
This compressed air supply system is provided with: a bleed passage; an auxiliary compressor unit having a compressor inlet which is fluidly connected to the bleed passage, and a compressor outlet; a supply passage which is fluidly conne...
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WO/2022/090654A1 |
The invention relates to a device (30) for pressurizing a turbomachine downstream enclosure (20), said device (30) being fed by means of a pressurizing air flow and comprising: a first shaft portion (9a), a second shaft portion (9b) coup...
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WO/2022/090650A1 |
Disclosed is a turbomachine comprising a gas generator (13) provided with a first shaft (18), at least one reversible electrical machine (11), a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow gener...
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WO/2022/094124A1 |
CO2 separation systems and methods
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WO/2022/093415A1 |
A gas turbine propulsion system includes a shroud that defines a fluid flow path. A gas turbine engine in the fluid flow path includes a compressor, a combustor downstream from the compressor, and a turbine downstream from the combustor....
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WO/2022/091275A1 |
The present invention comprises: a core engine having a core casing that covers a low-pressure rotation part and a high-pressure rotation part and forms a flow path of air passing through the low-pressure rotation part and the high-press...
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WO/2022/090660A1 |
The invention relates to a method for repairing a part (1) for an aircraft turbine engine, the part (1) comprising a lower panel (3), an upper panel (2) and a core (4) having a honeycomb structure arranged between the lower panel (3) and...
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WO/2022/084611A1 |
The invention relates to a turbofan engine (1) comprising a primary duct and a secondary duct surrounding the primary duct, a row of guide vanes (10) extending in the secondary duct, downstream of a fan (2), at least one servo extending ...
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WO/2022/084629A1 |
The invention relates to a method for manufacturing an air inlet lip, which comprises: - placing a blank opposite a three-dimensional forming surface of a die of a hydroforming tool, the three-dimensional surface comprising an outer annu...
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WO/2022/084630A1 |
The invention relates to a method for manufacturing an air inlet lip, comprising: - supplying a sheet of sheet metal, - cutting the sheet of sheet metal to form a ring, - mechanically machining one or more regions of reduced thickness in...
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WO/2022/084628A1 |
A method for manufacturing annular sectors of an air intake lip (70, 71), comprising: the placement of a blank with a shape exhibiting symmetry of revolution with regard to a three-dimensional forming surface of a die of a hydroforming t...
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WO/2022/079523A1 |
An adjustable injector system (100) for adjusting a radial distribution of a mixed fuel (117) includes an adjustable injector (110) configured to receive first and second non-carbon fuels (112, 114) and configured to adjust the radial di...
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WO/2022/079378A1 |
The present invention relates to an aeronautical propulsion system (1) comprising a reduction mechanism (12) that couples a drive shaft (10) and a fan shaft (13), and an inlet channel (3) comprising an inner shroud (16) having a predeter...
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WO/2022/079371A1 |
The present invention relates to a fuel supply circuit (1) comprising a supply duct (20) in which a first flow (F1) is able to circulate, at least one supply pump (3, 5) for circulating the fuel from a tank (2) to a metering unit (6), an...
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WO/2022/079435A1 |
An aircraft (101) comprising: one or more main engines (104a, 104b); a first fuel in a first fuel tank (111a) configured to be fed towards at least one of the one or more main engines through a first fuel line; and a second fuel differen...
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WO/2022/081569A1 |
An electrically decoupled jet engine. The electrically decoupled jet engine includes a combustion chamber which creates a toroidal flow of air and a rotational electric motor which drives a fuel supply into the combustion chamber. The to...
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WO/2022/073892A1 |
Disclosed is a supersonic speed attenuator (2) for an air inlet (5) of an aircraft power plant (8), comprising a conical external wall (20) with a tapered end (21) upstream and an internal dividing wall (22) that delimits, with the conic...
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WO/2022/073890A1 |
A system (1) for cooling a compartment (4) for equipment (41) in a nacelle (2) comprising a member (10) for drawing a cooling flow (Fr) and a device (11) for admitting the cooling flow (Fr) into the compartment (4), comprising: a regulat...
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WO/2022/073891A1 |
Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake comprising a movable upstream...
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