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WO/2024/106091A1 |
A shroud according to the present disclosure comprises a shroud main body, and a shroud edge portion which is provided around the shroud main body and which surrounds the shroud main body, wherein the shroud edge portion internally inclu...
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WO/2024/105332A1 |
The invention relates to a thrust reverser for an aircraft propulsion assembly, the reverser comprising a fixed structure (31) and a movable structure (29) comprising a movable reverser cowl (33) having a radially inner wall (52), the mo...
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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/2024/101149A1 |
This support device comprises: at least one first strut that has a first proximal end to be connected to a first wall and a first distal end, and extends from the first proximal end to the first distal end toward a second wall; at least ...
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WO/2024/101004A1 |
Provided is a cylindrical body capable of avoiding an increase in weight while improving cooling efficiency. This cylindrical body (1) comprises a plurality of annular members (100), wherein: the annular members (100) each have an outer ...
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WO/2024/100987A1 |
This heat utilization system comprises: a heat recovery device that carries out heat exchange between a heating fluid and water, thereby generating first steam, and second steam that is at a lower pressure than the first steam, from the ...
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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/2024/100332A1 |
The invention relates to a motor vehicle comprising a turbogenerator system which comprises: multiaxial turbochargers comprising compressors (C1, C2) and turbines (T1, T2); a cooler (I); a recuperator (R); two combustion chambers (CC1, C...
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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/2024/095848A1 |
This control device controls a gas turbine combustor capable of burning fuel gas and air mixed together inside a combustion chamber with a burner. The burner is provided with a first fuel gas injection hole, a second fuel gas injection h...
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WO/2024/097111A2 |
A turbine vane assembly for a gas turbine engine is disclosed herein. The turbine vane assembly includes a turbine vane including a leading edge, a pressure edge, a suction edge, and a trailing edge, a core defined by the turbine vane, a...
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WO/2024/096879A1 |
A gas turbine engine including a turbomachine. The turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine including an inlet duct defining an engine inlet,...
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WO/2024/095847A1 |
This gas turbine combustor can combust a fuel gas and air, which have been mixed in a combustion chamber, using a burner. The burner comprises a first fuel gas spraying hole, a second fuel gas spraying hole, and a first air spraying hole...
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WO/2024/091835A1 |
A combined cycle power plant (CCPP) is provided. The CCPP includes a gas turbine that has a compressor section, a combustion section, and a turbine section. The CCPP further includes a heat recovery steam generator (HRSG) that has a firs...
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WO/2024/087272A1 |
A gas turbine starting system, comprising an engine, a hydraulic starting system (200), a gas turbine (300), and a load module (400), the engine, the hydraulic starting system (200), the gas turbine (300) and the load module (400) being ...
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WO/2024/090524A1 |
This hybrid rotor drive system comprises: a gas turbine engine which includes a compressor, a combustor, a turbine, and a first output shaft mechanically connecting the compressor to the turbine; an electric motor including a second outp...
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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/2024/091836A1 |
A combined cycle power plant (CCPP) includes a heat recovery steam generator (HRSG) that includes a first economizer and a condensate supply line. The HRSG receives a flow of exhaust gas from the turbine section. The CCPP further include...
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WO/2024/088516A1 |
Air turborocket apparatus (10) including an air intake (11), a compressor (12), a turbine (13), a gas generator system, a coupling system (19), a combustion chamber (14), and a nozzle (15). The air intake is designed to receive atmospher...
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WO/2024/084150A1 |
The present invention relates to an aircraft turbomachine (10) with a recuperation cycle, comprising: - a heat exchanger (6) comprising a first circuit (62) with an inlet (622) connected to an outlet (444) of a flow path (44) of a turbin...
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WO/2024/084160A1 |
The invention relates to a turbojet engine comprising: a combustion chamber and a jet pipe; a main circuit (11) including a main centrifugal pump (14) and a main positive displacement pump (16) supplying fuel to the injectors (18) of the...
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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/2024/086485A1 |
A fire detection system for a gas turbine system including fire risk zones is provided. The system includes a pipe intake port proximate to each of the fire risk zones within a gas turbine system enclosure, and a manifold in fluid commun...
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WO/2024/083722A1 |
An aircraft engine seal apparatus has an inflatable seal with a front wall (3, 803, 1103) a rear wall (9, 840) and a side wall (4, 804) forming a rim for pressing and sealing against an internal surface of an engine intake. There is at l...
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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/2024/082078A1 |
A thermal management system and a valve thereof. The valve comprises a valve seat (12) and a valve core (14) rotatably arranged in the valve seat (12), wherein a plurality of inner valve ports and a plurality of outer valve ports are arr...
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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/2024/080334A1 |
A blade ring assembly according to the present disclosure comprises a turbine blade ring extending in a circumferential direction about an axis, stationary blades disposed on the inner-circumferential side of the turbine blade ring, and ...
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WO/2024/075569A1 |
This intermediate shaft cover comprises: a cylindrical inner cover covering an intermediate rotor shaft; an annular outer cover which covers an outer peripheral side of a diffuser space and which is connected to a gas turbine casing; and...
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WO/2024/075568A1 |
A lower half inner casing has a lower half inner casing body forming a semi-circular arc, and an inner casing accessory part provided to the lower half inner casing body. The inner casing accessory part has a protrusion which protrudes r...
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WO/2024/074448A1 |
The invention relates to an injector (3) for a de-icing device for an air intake of an aircraft turbojet nacelle, the injector (3) comprising a peripheral member (30) internally defining a passage duct (6), the peripheral member (30) com...
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WO/2024/074224A1 |
A hydraulic or pneumatic actuator (100, 200) for a valve, in particular a trip valve which may be used to cut-off the fluid supplied to an expander when a fault occurs, e.g. when pressure drops under a predetermined pressure value. The i...
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WO/2024/074256A1 |
The invention relates to a suspension system (2) for a manhole (6), in particular for a manhole (6) of a gas turbine (4), comprising: a first fastening portion (10) and a second fastening portion (11) for arrangement of connecting pieces...
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WO/2024/069086A1 |
The invention relates to a turbine engine comprising: - a first module comprising a speed reducer (3) having an input shaft (12), - a second module comprising a low-pressure compressor which is connected to the first module, - a third mo...
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WO/2024/066426A1 |
An oil and gas dual-effect seal structure for a gas turbine, comprising: a turbine rotor, a fixed sleeve, a supporting ring, a seal ring, a sleeve, an adjusting ring, a bearing, a locking gasket and a nut. The turbine rotor is sleeved wi...
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WO/2024/061740A1 |
The invention relates to a turbine engine comprising: a first splitting edge capable of separating an incoming air stream into a radially internal air stream and a secondary air stream; a second splitting edge capable of separating the r...
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WO/2024/061737A1 |
The invention relates to a turbomachine comprising: a first splitting edge capable of separating an incoming air flow into a radially internal air flow and a secondary air flow; a second splitting edge capable of separating the radially ...
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WO/2024/064620A1 |
Disclosed is a method enabling operation of a combustion system with at least two serially arranged combustion zones on fuels generally yielding varying flame speeds. First, the operating parameters of the gas turbine engine are determin...
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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/2024/059350A1 |
An igniter for a gas turbine engine has a shell; an insulator secured within said shell; a center electrode secured within said insulator and electrically isolated from said shell by said insulator, said center electrode having a firing ...
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WO/2024/057776A1 |
A heat-exchanging partition wall for air cooling a high-temperature component of an aircraft engine is provided with a wall that defines a cooling flow path through which cooling air flows along a first direction between the wall and a c...
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WO/2024/056975A1 |
The invention relates to a device for guiding a shaft of an aircraft turbine engine, the device comprising: - a rolling bearing (10, 11); - an annular bearing support (22); and - an oil film compression damping system (19) comprising: - ...
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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/2024/054295A1 |
A flow system (10) includes a flow source device (12) configured to receive fluid from a first flow line (14) and output fluid on a second flow line (16). An output (18) is in fluid communication with the flow source device on the second...
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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/2024/054490A1 |
A turboexpander (102) comprises a rotor shaft (108) and a permanent magnetic generator and includes a process gas inlet on a downstream side of a flow control valve (126) to receive process gas into the turboexpander; the rotor shaft (10...
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WO/2024/053326A1 |
The present invention provides a cooling fluid guide for a gas turbine, the cooling fluid guide comprising: a fixed part to be fixed either to piping for supplying a cooling fluid to a cooling fluid supply hole in a turbine casing or to ...
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