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公开(公告)号：US10393314B2
公开(公告)日：2019-08-27
申请号：US15643521
申请日：2017-07-07
IPC分类号： F16N19/00 , B29C64/106 , F02C7/06 , G01F23/26 , F01D21/00 , B33Y10/00 , B33Y70/00 , B33Y80/00 , B29L31/00 , F01D25/18 , F01M11/12
摘要： An oil tank fitted to a turbomachine, for example an aeroplane turbo-jet engine. The tank includes an inner chamber containing the oil of the turbomachine, a wall with an inner surface surrounding the inner chamber, and a capacitive device for measuring the oil level. The device includes at least one electrode and potentially two parallel electrodes forming the inner surface. These electrodes are immersed in the oil to measure the oil level by measuring capacitance. A method for manufacturing a tank in which the electrodes are printed on the wall.
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公开(公告)号：US20190128118A1
公开(公告)日：2019-05-02
申请号：US16171456
申请日：2018-10-26
发明人： Stéphane Hiernaux
IPC分类号： F01D5/02
摘要： A compressor for a turbine engine includes an annular row of blades including a first blade with an extrados surface and a second blade with an intrados surface; and a connecting surface joining the intrados surface to the extrados surface, the connecting surface having a bulge of volume VB and a recess of volume VC, the bulge and recess forming a contouring 3D. The volume of the bulge VB is greater than four times the volume VC of the recess, the connecting surface includes a flat or axisymmetric band circumferentially separating the bulge from the recess, and the bottom of the recess being formed against the intrados surface.
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公开(公告)号：US10226651B2
公开(公告)日：2019-03-12
申请号：US15415939
申请日：2017-01-26
IPC分类号： G01M15/14 , A62C2/14 , A62C2/24 , A62C3/00 , A62C35/00 , E06B9/04 , F02C7/25 , G01M15/02 , F01D25/28 , G01M9/04 , A62C99/00 , A62C3/08
摘要： A test cell for an aircraft turbojet, wherein the test cell comprises a U-shaped configuration, with a passageway in the form of an elongated corridor, an inlet chimney, and an outlet chimney. The corridor includes a securing area with a securing arm for holding the turbojet during its test. The passageway furthermore reveals an upstream shutter and a downstream shutter, the two shutters including one pivoting flap or a series of pivoting flaps. In the event of a fire, the shutters close due to autonomous return means. Gravity allows the flap(s) to come down to the closed position and to confine the turbojet in order to rapidly stifle the fire.
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公开(公告)号：US20180347579A1
公开(公告)日：2018-12-06
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：US20180320700A1
公开(公告)日：2018-11-08
申请号：US15970325
申请日：2018-05-03
发明人： Stéphane Hiernaux
IPC分类号： F04D27/00
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：US20180283192A1
公开(公告)日：2018-10-04
申请号：US15940163
申请日：2018-03-29
发明人： Stéphane Hiernaux , Nicolas Habotte
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F05D2220/32 , F05D2230/60 , F05D2240/56 , F05D2250/232 , F05D2250/314 , F16J15/3288 , Y02T50/672
摘要： An aircraft turbojet low-pressure compressor includes a sealing device for a turbine engine. The device includes an internal stator shroud connected to an external casing via an annular row of stator vanes and a rotor with two brush seals arranged inside the shroud and respectively upstream and downstream. The internal shroud includes a frustoconial internal surface, which is associated with each brush seal. Each frustoconical surface lies flush with and is inclined with respect to the bristles of the brush seal, so as to seal with the said brush. A method for assembling a sealing device is also proposed.
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公开(公告)号：US20170216637A1
公开(公告)日：2017-08-03
申请号：US15415939
申请日：2017-01-26
CPC分类号： A62C2/14 , A62C2/24 , A62C3/00 , A62C3/08 , A62C35/00 , A62C99/0018 , E06B9/04 , F01D25/285 , F02C7/25 , F05D2220/323 , F05D2260/12 , G01M9/04 , G01M15/02 , G01M15/14
摘要： A test cell for an aircraft turbojet, wherein the test cell comprises a U-shaped configuration, with a passageway in the form of an elongated corridor, an inlet chimney, and an outlet chimney. The corridor includes a securing area with a securing arm for holding the turbojet during its test. The passageway furthermore reveals an upstream shutter and a downstream shutter, the two shutters including one pivoting flap or a series of pivoting flaps. In the event of a fire, the shutters close due to autonomous return means. Gravity allows the flap(s) to come down to the closed position and to confine the turbojet in order to rapidly stifle the fire.
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公开(公告)号：US20170043877A1
公开(公告)日：2017-02-16
申请号：US15233340
申请日：2016-08-10
CPC分类号： B64D15/04 , B64D33/02 , B64D2033/0233 , F01D25/02 , F02C7/047 , F05D2220/323 , Y02T50/671
摘要： A de-icing and anti-icing splitter for an axial turbine engine low-pressure compressor has an external annular wall delimiting the secondary or bypass flow, and an internal annular wall; notably an external stator shroud; delimiting the primary or main stream. The upstream edge of the internal wall is fixed to the upstream annular hook of the external wall. The splitter has a series of notches which pass radially through the internal wall to allow de-icing fluid to circulate through the hook. The notches may form crescents. The splitter becomes simpler while at the same time maintaining optimal efficiency.
摘要翻译： 用于轴向涡轮发动机低压压缩机的除冰和防冰分流器具有限定次级或旁路流的外部环形壁和内部环形壁; 特别是外部定子护罩; 划分主流或主流。 内壁的上游边缘固定在外壁的上游环形钩上。 分流器具有一系列凹口，其径向通过内壁，以允许除冰液体通过钩子循环。 缺口可能会形成新月。 分离器变得更简单，同时保持最佳效率。
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公开(公告)号：US11946384B2
公开(公告)日：2024-04-02
申请号：US17604652
申请日：2020-04-10
发明人： Morgan Vyvey
CPC分类号： F01D25/24 , F01D11/122 , F01D17/162 , F04D29/522
摘要： A compressor casing for a turbine engine, the casing comprising: a housing comprising a radially inner e surface; an upstream ferrule; and a downstream ferrule; each of the ferrules having a respective inner surface capable of defining an air stream, and each of the ferrules having an outer surface facing the inner surface of the housing, the ferrules being attached to the cantilevered housing and being axially arranged so as to be separated by an axial clearance. Additionally, a turbine engine comprising such a casing and a stage of variable-setting vanes.
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公开(公告)号：US11781562B2
公开(公告)日：2023-10-10
申请号：US17796981
申请日：2021-02-26
CPC分类号： F04D29/544 , F04D21/00 , F04D29/324 , F04D29/547
摘要： A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.
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