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WO/2021/245340A1 |
Disclosed is an injection mould (100) for manufacturing a revolving part (10) made of composite material, comprising a mandrel (110) supporting a fibrous preform (20) and comprising an annular wall (111), and a plurality of angular count...
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WO/2021/241042A1 |
Provided are a journal bearing and a rotating machine, the journal bearing comprising: a housing that has an annular shape and is disposed around the periphery of a rotary shaft; a plurality of bearing pads that are disposed between the ...
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WO/2021/240107A1 |
The present invention relates to a cryogenic fuel supply system (9) for the combustion chamber (5) of an aircraft turbine engine, which comprises: - a tank for storing said cryogenic fuel in a liquid state (90), - a mixing chamber (91) w...
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WO/2021/240095A1 |
The invention relates to a turbomachine comprising a fan, a first casing with longitudinal axis X in which a motor shaft is rotated around the longitudinal axis X, a second casing (23) surrounding and coaxial with the first casing, and a...
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WO/2021/240111A1 |
An installation (2) for heating a cryogenic fuel supplying the combustion chamber (15) of an aircraft turbomachine (1) comprises: • - a reservoir (20) for storing said cryogenic fuel in the liquid state, • - a closed circuit (3) for ...
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WO/2021/240114A2 |
The present invention relates to an installation (2) for supplying cryogenic fuel to the combustion chamber (16) of a turbomachine (1) of an aircraft. This installation is noteworthy in that it comprises: - a mixing chamber (21) receivin...
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WO/2021/240094A1 |
The invention relates to a turbomachine comprising a fan (2), an engine shaft (14) caused to rotate about a longitudinal axis X in a first casing, a second casing surrounding and coaxial with the first casing, and a drive shaft (25) conn...
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WO/2021/240106A1 |
Device (2) for regulating the pressure inside an on-board tank (3) for the storage of a cryogenic fuel intended to supply the combustion chamber (10) of an aircraft turbine engine (1), this device comprising: • - said tank (3), • - a...
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WO/2021/234257A1 |
On board the aircraft (2), the following steps are implemented in the following order: - measuring a first density value, a first dielectric constant value and a first temperature value of the fuel at a first time, - measuring a second d...
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WO/2021/234258A1 |
The aircraft comprises: - at least one engine (4), - at least one fuel tank (6), - a chamber (22) which is located in the tank and which comprises at least one sensor (24, 26, 28) for measuring a characteristic of the fuel, - a system (8...
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WO/2021/230790A1 |
The disclosure relates to an air filtering apparatus (1) configured to provide intake air to an engine, said apparatus comprising: a filter chamber (2) comprising an air inlet opening (3), and an air outlet opening (4); a weather protect...
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WO/2021/229167A1 |
The invention relates to a turbomachine (1) for an aircraft, comprising: a first rotor (8) comprising a first shaft (80), a second rotor (9) comprising a second shaft (90), a mechanical reduction gearing (14) having an epicyclic gear set...
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WO/2021/224681A1 |
An improved power generation system and methods of its operation are provided, wherein the system combines: (i) a wave reformer, (ii) an optional second wave rotor, and (iii) a gas turbine in a flexible range of novel designs. Such a hyb...
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WO/2021/225631A1 |
A highly adaptive seal for use in advanced aircraft propulsion and missile systems is provided. The seal is capable of effectively limiting invasive thermal energy and corrosive airflow from entering the internal systems and hardware of ...
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WO/2021/224557A1 |
The invention relates to an arrangement (60) for an aircraft turbine engine, comprising a shaft (11) and a follower element (52) rotatably coupled to the shaft (11) by a spline connection (62), the arrangement comprising: - upstream and ...
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WO/2021/223910A1 |
A drive system for driving a load, such as a pump, a compressor or the like, is disclosed. The drive system comprises two clutches operable so that it is possible to exclude the load, so as to maximize the power transferred to the electr...
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WO/2021/225589A1 |
Systems and techniques for engine starter control may include determining a current speed band associated with an engine start for a current time increment, determining a previous speed band associated with the engine start for a previou...
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WO/2021/220950A1 |
A seal device according to at least one embodiment comprises three or more arcuate fins arranged in an axial direction. The arcuate fins include: a first fin, which is one of two outermost fins positioned farthest to the outer side in th...
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WO/2021/222021A2 |
An evaporative cooling pack formed from first and second corrugated media sheets is provided. The evaporative cooling pack cools a flow of air using a cooling fluid. The first and second corrugated media sheets have flutes that extend at...
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WO/2021/219461A1 |
The invention relates to an exhaust gas turbocharger (30) with a silencer. The silencer comprises a multiplicity of damping elements (41) which are arranged concentrically about a central axis (42) of the silencer and are spaced apart co...
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WO/2021/218969A1 |
A vehicle-mounted gas turbine generator set, comprising a chassis vehicle (7), a main box body (C) and at least one of an inlet air filtration system (3), a ventilation and filtration system (5) and an exhaust system (1). The chassis veh...
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WO/2021/205092A1 |
The invention relates to a mold (1) for manufacturing a turbine engine fan casing from a composite material, comprising: a mandrel (2) around which a fibrous fan casing preform is to be wound; a plurality of angular sectors (3) of a coun...
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WO/2021/206884A1 |
Fuel isolation systems, apparatuses and methods are described. In some embodiments, a system comprises a fuel tank, a fuel pump, an engine, a firewall, a fuel line from the fuel tank to the engine, a connector coupled inline with the fue...
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WO/2021/205125A1 |
An analysis device (130) for detecting solid particles suspended in a lubricant, the analysis device (100) comprising one or more ferromagnetic solid particle sensors (234, 235, 236, 237), one or more other sensors (238, 239, 240, 241) c...
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WO/2021/207089A1 |
A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be di...
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WO/2021/205126A1 |
Removable closure member (50) configured to close a female portion (40) received in an external opening (16b) formed in the external surface (16) of a nacelle (10) for an aircraft engine, the female portion (40) comprising at least one a...
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WO/2021/205127A1 |
The invention relates to an inlet guide vane (20) for an aircraft turbine engine, this inlet guide vane (20) comprising: - an inner annular shroud (22) extending around an axis (X), - an outer annular shroud (24) extending around the axi...
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WO/2021/198583A1 |
Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: - a rolling bearing (8), - an oil distributor ring (5) and - an annular track (26) of a dynamic seal (22), characterised in that it furthe...
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WO/2021/198601A1 |
The invention relates to a turbine engine module, comprising: - a fan shaft (6), - a power shaft (15) rotating the fan shaft via a speed reducer (21) arranged in a lubrication chamber (22), - a lubrication system (50) for the speed reduc...
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WO/2021/198581A1 |
The invention relates to a dual flow aircraft propulsion assembly (1) comprising a retractable heat exchanger (25). The exchanger (25) can be deployed in a secondary channel (11B) of the propulsion assembly (1) so as to cool a fluid flow...
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WO/2021/197665A1 |
An integrated hermetically sealed turboexpander-generator (21) comprises a hermetically sealed casing arrangement (23), a turboexpander (25), a compressor (27) and an electric generator (29), arranged in the hermetically sealed casing ar...
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WO/2021/199992A1 |
A labyrinth seal according to an embodiment of the present disclosure is provided with a first member including a plurality of sealing fins arranged spaced apart in the axial direction, and a second member which faces the first member wi...
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WO/2021/198602A1 |
The invention relates to an assembly (22) for an aircraft turbine engine, comprising a fan drive reduction gear (20) and a lubrication system (24) comprising: - a reduction gear housing (31a); - a lubricant tank (26); - a lubricant suppl...
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WO/2021/200634A1 |
A ceramic coating according to at least one embodiment of the present disclosure is provided with a bond coat layer formed on a base material and a ceramic layer formed on the bond coat layer. The ceramic layer has a first region being i...
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WO/2020/170227A9 |
A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces...
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WO/2021/197664A1 |
An integrated hermetically sealed turboexpander-generator (21) comprises a hermetically sealed casing arrangement (23), a turboexpander (25), a compressor (27) and an electric generator (29), arranged in the hermetically sealed casing ar...
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WO/2021/199993A1 |
A labyrinth seal according to an embodiment of the present disclosure is provided with a first member, and a second member facing the first member, wherein: the first member includes a plurality of sealing fins which are disposed spaced ...
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WO/2021/200702A1 |
This early sign detection device comprises: a plurality of sensors; a data acquisition unit for acquiring the time-series change data of a physical quantity from the plurality of sensors; a calculation unit for calculating, from the time...
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WO/2021/200256A1 |
The present invention reduces the possibility of spontaneous combustion of pulverized fuel that has been pulverized in a pulverizer without the use of an auxiliary burner. The invention is provided with: a pulverizer (10) for pulverizing...
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WO/2021/199995A1 |
A unison ring for a gas turbine engine has a fiber-reinforced resin containing a resin and reinforcing fibers, comprises an annular body or a plurality of arcuate bodies, and has a pin hole through which a pin is inserted in the radial d...
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WO/2021/191521A1 |
Method for manufacturing a metal component (1), characterized in that it comprises the following steps: a shell (2) made of a titanium-based material is provided, the shell (2) having a first surface (3) and a second surface (4) remote f...
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WO/2021/193434A1 |
This combustor is provided with an outer cylinder, an inner cylinder, a direct injection nozzle, a tail pipe, and a base end side acoustic attenuator. The outer cylinder is disposed inside a gas turbine casing. The inner cylinder is disp...
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WO/2021/194482A1 |
An electric machine and a turning gear system for aircraft gas turbine engines are provided. The system has an electric machine designed for dual mode operation and a controller. The stator winding arrangement in the electric machine ena...
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WO/2021/191588A1 |
A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat ...
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WO/2021/191523A1 |
The invention relates to a turbomachine comprising a device for ventilating and pressurising a turbine rotor of a turbomachine of axis (A), the device comprising at least one collection pipe suitable for collecting a fraction of the air ...
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WO/2021/191569A2 |
Turbomachine (10) for an aircraft, comprising a casing (30), a fan (20), a compressor (50) and a turbine (90), and a planetary gearing (40) comprising an input that is driven in rotation by the turbine (90), a first output stage configur...
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WO/2021/192599A1 |
A heat conductive film comprises a graphene sheet extending in the in-plane direction and a resin sheet provided by being laminated in the out-of-plane direction orthogonal to the in-plane direction of the graphene sheet, a plurality of ...
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WO/2021/192758A1 |
In this method for mounting a combustor component, a component hanging step for attaching a string material to a hanging jig mounted on a combustor component and hanging the combustor component with the string material together with the ...
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WO/2021/194473A1 |
A method of modulating a cooling supply in a gas turbine engine includes providing the engine comprising a compressor section and a turbine section and including a cooling flow circuit, the cooling flow circuit supplying a cooling air fl...
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WO/2021/191528A1 |
Turbofan engine (10) of longitudinal axis (X-X') comprising a primary duct (20), in which there flows a primary flow (F1) at a primary pressure (P3), and a secondary duct (19), which radially surrounds said primary duct (20) and in which...
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