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公开(公告)号：US20220412675A1
公开(公告)日：2022-12-29
申请号：US17756986
申请日：2020-12-08
摘要： A heat exchanger between a fluid and an air flow, includes a heat exchange wall separating the fluid and the air flow, the heat exchange wall including a heat exchange surface that extends parallel to a longitudinal direction of the air flow and with which the air flow is in contact. The heat exchange wall includes at least one turbulence generator extending in a hollow manner in relation to the heat exchange surface.
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公开(公告)号：US20180080332A1
公开(公告)日：2018-03-22
申请号：US15707428
申请日：2017-09-18
CPC分类号： F01D9/041 , F01D5/282 , F01D5/3069 , F01D9/042 , F01D25/246 , F05D2220/36 , F05D2240/12 , F05D2260/31 , F05D2300/603 , Y02T50/672
摘要： An OGV wheel comprising guide vanes made of polymer matrix composite material reinforced by fibers, each having a vane root and a vane tip, the vane roots being fastened on a hub of the wheel by first connection means and the vane tip being fastened on an outer shroud of the wheel by second connection means, the first connection means including a bearing plane secured to the hub and a first backing plate for securing to the hub, the vane roots being sandwiched between the bearing plane and the first backing plate, and the second connection means including a second backing plate for securing to the shroud, the vane tip being sandwiched between the shroud and the second backing plate.
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公开(公告)号：US20230010301A1
公开(公告)日：2023-01-12
申请号：US17757035
申请日：2020-12-08
摘要： An assembly for a turbomachine through which an air flow passes, includes a stator including guide vanes extending radially in relation to a longitudinal axis, at least one inter-vane platform extending between the radially outer ends of two circumferentially consecutive guide vanes, each inter-vane platform including an outer surface that faces the axis, a heat exchanger located downstream of the stator in relation to a direction of circulation of the air flow in the turbomachine during operation, this stator including a heat exchange surface extending in the extension of an inter-vane platform. At least one inter-vane platform located in the upstream extension of the heat exchange surface is provided with at least one turbulence generator on its outer surface.
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公开(公告)号：US20190120071A1
公开(公告)日：2019-04-25
申请号：US16167951
申请日：2018-10-23
IPC分类号： F01D9/04
摘要： The invention relates to a straightening assembly (28) comprising two radially inner and outer coaxial shells (34) between which extend vanes (36) made of composite material, fixed to a first end portion on the radially inner shell and to a second end portion on the radially outer shell, characterized in that: for each vane (36), in a plane perpendicular to the axis of the radially inner and outer shells (34), a straight line passing through a junction between said first and second end portions and the useful part forms an angle α with a radius of the radially inner shell, passing through the junction between said first end portion and the useful part of said vane (36), such that 0°
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公开(公告)号：US20220162952A1
公开(公告)日：2022-05-26
申请号：US17430228
申请日：2020-02-06
摘要： A turbomachine blade including a body that extends mainly in a plane defined by a main axis B and a longitudinal direction, which is defined by a lower surface wall, an upper surface wall, a leading edge located at a first longitudinal end of the body and a trailing edge located at a second longitudinal end of the body, wherein the body of the blade includes a plurality of first pipes that extend mainly along the direction of the main axis B, for circulation of a gas flow, and a plurality of second pipes that extend mainly along the longitudinal direction, for circulation of a second gas flow.
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公开(公告)号：US20190106998A1
公开(公告)日：2019-04-11
申请号：US16096832
申请日：2017-04-27
摘要： The invention relates to a straightening assembly for an air flow of a turbomachine, comprising two respectively coaxial radially inner and outer shrouds (30), between which extend the vanes (32) made of composite material attached, at a first end portion (42) thereof, to the radially inner shroud and at a second end portion (44) thereof, to the radially outer shroud (30), with the vanes (32) comprising a useful portion extending between the two end portions (42, 44). According to the invention, for each vane (32) in a plane perpendicular to the axis of the radially inner and outer shrouds (30), a straight line passing through a junction between said first and second end portions (42, 44) and the useful portion forms, with a radius of the radially inner shroud passing through the junction between said first end portion and the useful portion of said vane (32), an angle α such that 0°
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公开(公告)号：US20190072003A1
公开(公告)日：2019-03-07
申请号：US16123339
申请日：2018-09-06
摘要： A gas turbine casing made of composite material, the casing presenting an axisymmetric shape and including, in an axial direction: an upstream flange; a retention zone presenting thickness greater than the remainder of the casing; and a downstream flange. The casing presents, in section on a plane defined by the axial direction and by a radial direction, a profile including at least first and second inclined portions that are inclined relative to each other and relative to the axis of the casing. The first and second inclined portions meet at a point situated between the retention zone and one of the flanges, this point corresponding to the vertex of an angle formed by the first and second inclined portions. The distance between the vertex of the angle and the mean radius of the casing lies in the range 1.5% and 4% of the mean radius of the casing.
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公开(公告)号：US20220025833A1
公开(公告)日：2022-01-27
申请号：US17297079
申请日：2019-11-21
摘要： A turbofan engine including an exhaust casing traversed by a primary flow and surrounded by a secondary flow and an outlet cone carried by this exhaust casing, the exhaust casing and the outlet cone together defining an internal space. The exhaust casing includes a hollow radial arm traversing the primary flow in order to convey part of the secondary flow so as to form a cooling flow for supplying the internal space, and the outlet cone is terminated by an opening for discharging the cooling flow.
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公开(公告)号：US20220010735A1
公开(公告)日：2022-01-13
申请号：US17294593
申请日：2019-11-21
摘要： A turbojet engine including a shaft surrounded by a low-pressure rotor surrounded by a coaxial and independent high-pressure spool, this turbojet engine including from upstream to downstream: a fan driven by the shaft; a low-pressure compressor carried by the rotor; an inter-compressor casing; a high-pressure compressor and a high-pressure turbine carried by the high-pressure spool; an inter-turbine casing; a low-pressure turbine carried by the rotor; an exhaust casing; this turbojet engine including an upstream rotor bearing carried by the inter-compressor casing; a downstream rotor bearing carried by the exhaust casing; a gearbox downstream of the downstream bearing and through which the rotor drives the shaft; a downstream shaft bearing downstream of the downstream rotor bearing.
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10.发明申请公开(公告)号：US20190338661A1
公开(公告)日：2019-11-07
申请号：US16462264
申请日：2017-11-28
发明人： Cédric ZACCARDI , Christophe Marcel Lucien PERDRIGEON , Mohamed-Lamine BOUTALEB , Sébastien Vincent François DREANO
摘要： The invention relates to a guide vane for a bypass aircraft turbomachine, its aerodynamic part comprising a first lubricant cooling interior passage in which heat transfer structures are arranged and a second lubricant cooling interior passage in which heat transfer structures are arranged, the aerodynamic part comprising a bent area connecting a lubricant output end of the first interior passage to a lubricant input end of the second passage, the bent area extending along a curved generatrix and being partly delimited by the intrados wall and the extrados wall of the vane. According to the invention, the bent area comprises one or more lubricant guide(s) arranged between the intrados and extrados walls of the vane, and each extending substantially parallel to the curved generatrix of the bent area.
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