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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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WO/2024/053577A1 |
This heat engine system comprises: a heat engine that is driven by gas fuel and generates exhaust gas; a waste heat recovery boiler that has a fuel heating line for generating the gas fuel by heating liquid fuel through heat exchange wit...
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WO/2024/046222A1 |
Disclosed in the present invention are a flow dividing ring and an aero engine containing same, and an aircraft. The flow dividing ring is internally provided with an annular cavity, and the flow dividing ring is connected to an air inta...
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