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公开(公告)号：US20230160322A1
公开(公告)日：2023-05-25
申请号：US17919166
申请日：2021-04-13
CPC分类号： F01D25/20 , F01D21/003 , F05D2260/606 , F05D2260/607 , F05D2260/609 , F05D2270/804
摘要： A device for detecting particles in a lubricating oil of a machine, comprising a particle separator; at least one particle detector; a bypass conduit for the particle-concentrating oil, fluidly connected to an oil outlet of the particle separator, concentrating the particles; and wherein the at least one particle detector is operatively mounted on the bypass conduit so as to be able to detect particles in the bypass conduit.
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公开(公告)号：US11619169B2
公开(公告)日：2023-04-04
申请号：US16723715
申请日：2019-12-20
发明人： David Weicker , Roel Vleugels , Nicolas Fellin
IPC分类号： F02C7/18 , F02C7/14 , B33Y80/00 , F28D1/02 , F28F7/02 , B33Y10/00 , F01D25/12 , F02C3/04 , F02C9/18
摘要： A matrix for exchanging heat between a first fluid and a second fluid, in particular for an air-oil application in a turbine engine, includes an envelope defining a flow path of the first fluid and a network extending into the flow path and in which the second fluid flows. Along the axis defined by the curvature of the matrix, the dimensions of the envelope vary circumferentially (T(A)) and radially (R(A)). The matrix may be used with a heat exchanger.
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公开(公告)号：US11408907B2
公开(公告)日：2022-08-09
申请号：US16784464
申请日：2020-02-07
摘要： A method of testing and/or controlling the operation of an axial turbomachine through which passes a gas stream, includes the following actions: measurement of operating parameters of the turbomachine, said parameters including pressure in the gas stream at different axial positions, and calculation of operating conditions of the turbomachine from the measured parameters and the Laplace coefficient γ of the gas passing through the turbomachine, wherein the measurement of parameters includes a measurement of the temperature of the gas stream, and the calculation of operating conditions includes a determination of the Laplace coefficient γ on the basis of the measurement of the temperature of the gas stream.
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公开(公告)号：US11040506B2
公开(公告)日：2021-06-22
申请号：US16155179
申请日：2018-10-09
发明人： Alain Derclaye , Philippe Berot
IPC分类号： B29C70/84 , B29C70/38 , F01D25/24 , B29C70/78 , B29C70/46 , B29C70/68 , B29K309/08 , B29K307/04 , B29L31/00 , B29K705/00 , B29L31/30 , B29C70/54 , B29C70/88
摘要： A method for manufacturing a curved composite casing for a turbomachine, notably for a low-pressure compressor of an aircraft turbojet engine, includes the following sequence of steps: (a) draping a preform by automatic placement of carbon fibres on a concave form, referred to as a female form; (b) laying a glass-fibre ply on a convex form, referred to as a male form; (c) transferring the preform onto the convex form, covering the glass-fibre ply on the convex form. Step (b) laying includes a phase (α) of laying a metal strip and/or an epoxy profile on the convex form, then a phase (β) of covering the metal strip with the glass-fibre ply.
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公开(公告)号：US10882128B2
公开(公告)日：2021-01-05
申请号：US15906459
申请日：2018-02-27
摘要： A spark erosion machine includes a frame with a space for spark erosion of a workpiece, a wire for cutting by spark erosion, and a wire guide head for guiding the wire across the workpiece, so as to detach an offcut from it; an offcut support mounted movably relative to the guide head, the support being configured to move at least between a retention position under the spark erosion space, where it can collect the offcut, and a retracted position; and an offcut extractor.
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公开(公告)号：US10746036B2
公开(公告)日：2020-08-18
申请号：US15994101
申请日：2018-05-31
发明人： Stéphane Hiernaux
摘要： A low-pressure compressor for a turbine engine, such as an aircraft turbojet engine includes a rotor with two rows of rotor blades between which two annular ribs are positioned; and one annular row of stator blades between the rotor blades. An internal shroud is connected to the stator blades. The internal shroud includes abradable material collaborating with the annular ribs, and annular teeth made of an abradable material and which extend radially towards the rotor, so as to provide sealing. The system may be used in a method for manufacturing a bypass turbojet engine compressor.
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公开(公告)号：US20200248556A1
公开(公告)日：2020-08-06
申请号：US16747371
申请日：2020-01-20
发明人： Alain Derclaye
摘要： A rotor for an axial turbomachine includes a drum formed of several parts including: composite rings made of composite material and metallic rings interposed between the composite rings. The metallic rings carry the rotor blades. The metallic rings have an axial branch axially overlapping the composite rings and at least one radial branch in contact with the composite rings.
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公开(公告)号：US10676215B2
公开(公告)日：2020-06-09
申请号：US15928810
申请日：2018-03-22
发明人： Nicolas Raimarckers
IPC分类号： B64F5/60 , B64D29/00 , B64F5/40 , B64D45/00 , F01M11/12 , F16N19/00 , F01D21/00 , B64D29/08 , F01M11/10 , G07C5/00 , G07C5/08 , F01D25/18
摘要： A jet engine includes an external cowling, a member such as an oil reservoir, and a monitoring system for the member that is able to determine information relating to the member. The external cowling includes a visualization screen that is able to communicate with the monitoring system or directly with the member, so as to display the information specific to the member. When installed in the nacelle of the jet engine, this cowling becomes a smart cowling. The system also includes a method for inspecting a member of an aircraft jet engine and a corresponding computer program.
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公开(公告)号：US20200080423A1
公开(公告)日：2020-03-12
申请号：US16556586
申请日：2019-08-30
发明人： Stéphane Hiernaux
摘要： A turbine engine compressor blade includes a leading edge, a trailing edge, a suction surface, and a pressure surface. In addition, the blade includes at least one irregularity in the form of a projecting protuberance of the suction surface or the pressure surface or in the form of a recess nested in the suction surface or the pressure surface. The irregularity may have a direction of longest dimension substantially parallel to the leading edge or substantially axial.
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公开(公告)号：US10526963B2
公开(公告)日：2020-01-07
申请号：US15062716
申请日：2016-03-07
申请人： Techspace Aero S.A.
发明人： Vincent Duprez
摘要： An axial turbine engine for an aircraft, in particular a ducted fan turbine engine. The engine comprises an oil circuit with a cooler fitted with a first heat exchange surface in contact with oil of the oil circuit, and a second heat exchange surface in contact with a secondary air flow entering the turbine engine. The cooler is of the air/oil type (ACOC) and comprises fins. To increase the capacity of the cooler, the cooler is fitted with a device for injecting a cooling liquid, e.g., water with additives. The thermal capacity of the water amplifies the cooling. Evacuation of the water increases the thrust of the turbine engine. A method is also provided for cooling the turbine engine of an aircraft by injection of a cooling liquid at the time of take-off.
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