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公开(公告)号：US11346224B2
公开(公告)日：2022-05-31
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：US20220082331A1
公开(公告)日：2022-03-17
申请号：US17531906
申请日：2021-11-22
发明人： Roxane Koeune , Nicolas Fellin
IPC分类号： F28D7/10
摘要： A turbine engine heat exchanger for exchanging heat between a first fluid and a second fluid includes a reference axis, a network of tubular meshes having a plurality of meshes each of which is formed, successively in a reference direction, of at least two curvilinear branches, called anterior branches, of a junction where the two anterior branches meet, and of at least two curvilinear branches, called posterior branches, diverging from the junction, wherein the body of the heat exchanger is of cylindrical shape. The present disclosure also concerns a turbine engine comprising the heat exchanger and a manufacturing method for manufacturing the heat exchanger.
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公开(公告)号：US11203935B2
公开(公告)日：2021-12-21
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：US11181322B2
公开(公告)日：2021-11-23
申请号：US16719571
申请日：2019-12-18
发明人： Roxane Koeune , Nicolas Fellin
IPC分类号： F28D7/10
摘要： A turbine engine heat exchanger for exchanging heat between a first fluid and a second fluid includes a reference axis, a network of tubular meshes having a plurality of meshes each of which is formed, successively in a reference direction, of at least two curvilinear branches, called anterior branches, of a junction where the two anterior branches meet, and of at least two curvilinear branches, called posterior branches, diverging from the junction, wherein the meshes are stacked in staggered rows.
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公开(公告)号：US10914198B2
公开(公告)日：2021-02-09
申请号：US15727796
申请日：2017-10-09
发明人： Florian Cleyet , Stephane Bougelet
摘要： The invention relates to a turbojet engine oil tank (30). The tank (30) comprises a main chamber and an envelope (34) delimiting the main chamber, and a fixing portion (44) for example with fixing flanges (46) and a branch (48). The envelope (34) features in particular an envelope part (34) relative to which the fixing portion (44) projects. The envelope part (34) and the fixing portion (44) are produced by layered additive fabrication so as to be in one piece. The invention also relates to a method of fabricating an oil tank (30).
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公开(公告)号：US20200340406A1
公开(公告)日：2020-10-29
申请号：US16758749
申请日：2019-06-21
发明人： Stephane Maljean
摘要： The invention relates to a turbine engine (2), such as an aircraft turbofan engine, comprising: an epicyclic gear (36); a turbine driving in rotation a transmission shaft (34) integral in rotation with the sun gear (60) of the epicyclic gear (36); a fan (18) integral with the outer ring (66) of the epicyclic gear (36); and an electric motor (70) comprising a rotor (72) and a stator (74), the rotor (72) being integral with the planet carrier (68) of the epicyclic gear (36). Alternatively, the fan (18) is secured to the planet carrier and the electric motor (70) is secured to the outer ring.The invention also relates to methods of using said turbofan engine, in particular for regulating the reduction ratio between the shaft and the turbine, for recovering kinetic energy or for taxiing.
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公开(公告)号：US10746184B2
公开(公告)日：2020-08-18
申请号：US15970325
申请日：2018-05-03
发明人： Stéphane Hiernaux
摘要： A system for measuring turbulence of a flow of a turbine engine, notably of a turbine engine compressor includes a first housing with a first pressure sensor and a first inlet, a second housing with a second pressure sensor and a second inlet inclined relative to the first inlet, and a temperature sensor. The system is configured to calculate at least two orientation components of the velocity of the flow on the basis of the pressure sensors and the temperature sensor. The inlets are disposed at the vane foot, on the leading edge at the level of an internal shell.
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公开(公告)号：US20200256887A1
公开(公告)日：2020-08-13
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：US10690147B2
公开(公告)日：2020-06-23
申请号：US15872242
申请日：2018-01-16
发明人： Stephane Hiernaux
IPC分类号： F04D29/58 , F01D25/24 , F01D25/02 , F01D9/04 , F01D11/02 , F01D5/14 , F01D11/00 , F01D15/12 , F01D11/24 , F02C7/14 , F02C7/06 , F01D25/14 , F02C7/047 , F01D25/10 , F01D25/16 , F04D29/54
摘要： An assembly for a turbojet, wherein the assembly includes an outer shroud and an inner shroud that are concentric, wherein the inner shroud is segmented and includes circumferential clearances between the segments thereof. The assembly additionally includes an annular row of stator vanes connecting the inner shroud to the outer shroud, a drive with a reduction ratio that is intended to be coupled to a fan, and a circuit for cooling and for lubricating the drive. The circuit is configured to heat up at least the outer shroud during the operation of the turbine engine such as to circumferentially reduce the circumferential clearances between the segments.
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公开(公告)号：US10668538B2
公开(公告)日：2020-06-02
申请号：US15681090
申请日：2017-08-18
发明人： Brigitte Detry
IPC分类号： B22F5/00 , B30B15/02 , B22F3/02 , B30B15/34 , B22F3/00 , B22F3/14 , B29C70/58 , F01D11/12 , B22F3/12
摘要： A method for producing an abradable seal for a turbomachine, such as a turbojet engine low-pressure compressor. The method comprises the following steps performed as follows: (a) preheating of a metal mould in a furnace; (b) filling of the hot mould with a powdery aluminium-based mixture; (c) degassing of the mixture in the mould; (d) compacting of the mixture in the still-hot mould at ambient temperature, so as to solidify the mixture in the mould. The abradable seal is thus produced in angular segments that form tiles. The angular segments are then bonded into a composite casing of the turbomachine.
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