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    System for deicing the nose cone of an aircraft turbojet with oil
    2.
    发明授权
    System for deicing the nose cone of an aircraft turbojet with oil 有权
    用油除冰飞机涡轮喷气机鼻锥的系统

    公开(公告)号：US07647761B2

    公开(公告)日：2010-01-19

    申请号：US12029212

    申请日：2008-02-11

    申请人： Gerard Philippe Gauthier ,  Laurent Gille ,  Serge Rene Morreale ,  Jean-Yves Picart

    发明人： Gerard Philippe Gauthier ,  Laurent Gille ,  Serge Rene Morreale ,  Jean-Yves Picart

    IPC分类号： F02C7/047 ,  F02C7/06

    CPC分类号： F01D25/02 ,  F02C7/047 ,  F02C7/14 ,  F05D2240/50 ,  F05D2260/205 ,  F16C33/6677 ,  F16C2360/23 ,  Y02T50/671 ,  Y02T50/675

    摘要： The turbojet has a bearing which supports, in rotation and in thrust, a low-pressure compressor shaft of axis Z-Z of the engine. The bearing is lubricated with oil by means of two nozzles. A feed tube is fastened to the nose cone of the engine. This tube connects the low-pressure compressor shaft to the engine nose cone. A skin lines the wall of the engine nose cone, leaving a passage for the circulation of oil. A plurality of radial oil return tubes are placed between the most eccentric part of the skin relative to the Z-Z axis and the bearing, for returning the oil to the bearing. The return of the oil into the bearing is located at a distance R from the Z-Z axis larger than the radius r of the feed tube.

    摘要翻译： 涡轮喷气发动机具有在发动机的轴线Z-Z的低压压缩机轴的旋转和推力中支撑的轴承。 轴承通过两个喷嘴用油润滑。 进料管固定在发动机的鼻锥上。 该管将低压压缩机轴连接到发动机鼻锥。 皮肤划线在发动机鼻锥体的墙壁上，留下一个通道用于油循环。 多个径向回油管被放置在皮肤相对于Z-Z轴的最偏心部分和轴承之间，用于将油返回到轴承。 将油返回到轴承中的位置距离Z-Z轴的距离R大于进料管的半径r。

    SYSTEM FOR DEICING THE NOSE CONE OF AN AIRCRAFT TURBOJET WITH OIL
    3.
    发明申请
    SYSTEM FOR DEICING THE NOSE CONE OF AN AIRCRAFT TURBOJET WITH OIL 有权
    用于检测具有油的飞机涡轮机的噪声系统

    公开(公告)号：US20080190093A1

    公开(公告)日：2008-08-14

    申请号：US12029212

    申请日：2008-02-11

    申请人： Gerard Philippe GAUTHIER ,  Laurent Gille ,  Serge Rene Morreal ,  Jean-Yves Picart

    发明人： Gerard Philippe GAUTHIER ,  Laurent Gille ,  Serge Rene Morreal ,  Jean-Yves Picart

    IPC分类号： F02C7/047 ,  F01M11/02

    CPC分类号： F01D25/02 ,  F02C7/047 ,  F02C7/14 ,  F05D2240/50 ,  F05D2260/205 ,  F16C33/6677 ,  F16C2360/23 ,  Y02T50/671 ,  Y02T50/675

    摘要： The turbojet has a bearing which supports, in rotation and in thrust, a low-pressure compressor shaft of axis Z-Z of the engine. The bearing is lubricated with oil by means of two nozzles. A feed tube is fastened to the nose cone of the engine. This tube connects the low-pressure compressor shaft to the engine nose cone. A skin lines the wall of the engine nose cone, leaving a passage for the circulation of oil. A plurality of radial oil return tubes are placed between the most eccentric part of the skin relative to the Z-Z axis and the bearing, for returning the oil to the bearing. The return of the oil into the bearing is located at a distance R from the Z-Z axis larger than the radius r of the feed tube.

    摘要翻译： 涡轮喷气发动机具有在发动机的轴线Z-Z的低压压缩机轴的旋转和推力中支撑的轴承。 轴承通过两个喷嘴用油润滑。 进料管固定在发动机的鼻锥上。 该管将低压压缩机轴连接到发动机鼻锥。 皮肤划线在发动机鼻锥体的墙壁上，留下一个通道用于油循环。 多个径向回油管被放置在皮肤相对于Z-Z轴的最偏心部分和轴承之间，用于将油返回到轴承。 将油返回到轴承中的位置距离Z-Z轴的距离R大于进料管的半径r。

    DEVICE FOR REGULATING THE FLOW RATE OF AIR FEEDING A TURBINE VENTILATION CAVITY OF A TURBOMACHINE TURBINE SECTION
    5.
    发明申请
    DEVICE FOR REGULATING THE FLOW RATE OF AIR FEEDING A TURBINE VENTILATION CAVITY OF A TURBOMACHINE TURBINE SECTION 有权
    用于调节空气进给流量的装置涡轮机涡轮部分的涡轮通风孔

    公开(公告)号：US20100119356A1

    公开(公告)日：2010-05-13

    申请号：US12615798

    申请日：2009-11-10

    申请人： Ion FINTESCU ,  Laurent Gille ,  Jean-Pierre Andre Joseph Mourlan ,  Matthieu Savarit

    发明人： Ion FINTESCU ,  Laurent Gille ,  Jean-Pierre Andre Joseph Mourlan ,  Matthieu Savarit

    IPC分类号： F01D17/00

    CPC分类号： F01D17/145 ,  F01D9/065 ,  F02C6/08 ,  F05D2260/205 ,  F05D2270/3015 ,  F16K15/038 ,  Y02T50/676 ,  Y10T137/7839 ,  Y10T137/7848

    摘要： The invention relates to a device for regulating the flow rate of air feeding a turbine ventilation cavity of a turbomachine turbine section, the device comprising at least one tubular duct opening into a take-off cavity and leading into a turbine ventilation cavity, the pressure inside the take-off cavity being higher than the pressure inside the turbine ventilation cavity, an air flow rate regulation valve disposed in the tubular duct, the valve being suitable for moving under the effect of the pressure difference between the take-off cavity and the turbine ventilation cavity, and mechanical return means for holding the valve in a maximum closure position for the duct so long as the pressure difference between the take-off cavity and the turbine ventilation cavity remains below a predetermined threshold pressure.

    摘要翻译： 本发明涉及一种用于调节供应涡轮机涡轮机部分的涡轮机通风腔的空气的流量的装置，该装置包括至少一个管状管道，该管状管道通向起飞腔并进入涡轮机通风腔，内部压力 所述起飞腔高于所述涡轮机通风腔内的压力，设置在所述管状管道中的空气流量调节阀，所述阀适于在所述引出腔和所述涡轮机之间的压力差的作用下移动 通风腔和机械返回装置，用于将阀保持在用于管道的最大关闭位置，只要起飞腔和涡轮机通风腔之间的压力差保持在预定阈值压力以下。

    Seal for a rotating shaft
    6.
    发明授权
    Seal for a rotating shaft 失效
    旋转轴的密封

    公开(公告)号：US5039115A

    公开(公告)日：1991-08-13

    申请号：US490306

    申请日：1990-03-08

    申请人： Michel J. H. Hebert ,  Laurent Gille

    发明人： Michel J. H. Hebert ,  Laurent Gille

    IPC分类号： F01D25/16 ,  F01D11/00 ,  F16J15/30 ,  F16J15/34 ,  F16J15/40

    CPC分类号： F16J15/30 ,  F01D11/00 ,  F01D11/003 ,  F16J15/406

    摘要： A seal for a rotating shaft is disclosed which seals the shaft as it passes through a stationary partition wall. The seal has a segmented graphite sealing ring extending around the shaft located in an annular recess of a casing attached to the partition wall. A retaining ring having axial projections extending into radial grooves defined by the sealing ring is attached to the casing and a retaining washer extends circumferentially between the graphite segments and the retaining ring to prevent any relative axial movement between the elements. Relative rotation and axial movement between the retaining ring and the casing is prevented by stop pegs and a stop ring.

    摘要翻译： 公开了一种用于旋转轴的密封件，其在穿过静止分隔壁时密封轴。 密封件具有分段的石墨密封环，所述分段石墨密封环围绕位于连接到分隔壁的壳体的环形凹部中的轴延伸。 具有延伸到由密封环限定的径向凹槽中的轴向突起的保持环附接到壳体，并且保持垫圈在石墨段和保持环之间周向延伸，以防止元件之间的任何相对轴向移动。 通过止动销和止动环来防止保持环和外壳之间的相对旋转和轴向运动。

    Method and a device for balancing pressure in a turbojet bearing enclosure
    7.
    发明授权
    Method and a device for balancing pressure in a turbojet bearing enclosure 有权
    方法和用于平衡涡轮喷气轴承外壳中的压力的​​装置

    公开(公告)号：US08714905B2

    公开(公告)日：2014-05-06

    申请号：US12934784

    申请日：2009-03-24

    申请人： Ion Fintescu ,  Laurent Gille ,  Jean-Pierre Mourlan

    发明人： Ion Fintescu ,  Laurent Gille ,  Jean-Pierre Mourlan

    IPC分类号： F04D27/02

    CPC分类号： F01D25/16 ,  F01D25/183 ,  F02C7/06 ,  F05D2240/63

    摘要： A pressure-balancing device for balancing pressure in at least one bearing enclosure of a turbojet, the enclosure including a mechanism feeding the bearing with lubricating liquid, an air intake, at least one sealing system placed between the stator and the rotor in front of and/or behind the bearing, a recovery mechanism recovering the lubricating liquid, and a removal mechanism removing the mixture of air and of traces of lubricating liquid towards a venting circuit. Downstream from the bearing enclosure and in the venting circuit, the balancing device includes a regulator system regulating the air removal flow rate, thereby enabling the flow rate to be variable as a function of the speed of the engine, to remain non-zero, and, at high speeds, to be lower than when the regulator system is not included.

    摘要翻译： 一种用于平衡涡轮喷气发动机的至少一个轴承罩中的压力的​​压力平衡装置，所述外壳包括将所述轴承与润滑液体一起供给的机构，进气口，置于所述定子和所述转子之前的至少一个密封系统， /或在轴承后面，回收润滑液的回收机构，以及去除空气和痕量润滑液体的混合物朝向排气回路的去除机构。 在轴承箱和通气回路下游，平衡装置包括调节排气流量的调节器系统，从而使流量可根据发动机的速度而变化，保持非零，以及 ，高速度，低于不包括调节器系统时。

    METHOD AND SYSTEM FOR LUBRICATING A TURBINE ENGINE
    8.
    发明申请
    METHOD AND SYSTEM FOR LUBRICATING A TURBINE ENGINE 有权
    用于润滑涡轮发动机的方法和系统

    公开(公告)号：US20110198155A1

    公开(公告)日：2011-08-18

    申请号：US13120163

    申请日：2009-09-11

    申请人： Gilles Alain Charier ,  Gerard Philippe Gauthier ,  Laurent Gille ,  Serge Rene Morreale

    发明人： Gilles Alain Charier ,  Gerard Philippe Gauthier ,  Laurent Gille ,  Serge Rene Morreale

    IPC分类号： F01D25/18 ,  F01M11/08 ,  F01D25/20 ,  F02C7/06

    CPC分类号： F01D25/16 ,  F01D25/125 ,  F01D25/183 ,  F01D25/20 ,  F02C7/06 ,  F05D2240/40 ,  Y02T50/675

    摘要： A method and a system for lubricating a turbine engine including at least three separate housings each including at least one roller bearing. The method pressurizes the housings through seals, of which two main housings are pressurized at a pressure higher than that of a remaining secondary housing, lubricates a secondary roller bearing only by injecting an oil mist from at least one of the main housings, the oil mist being supplied by a pressure difference between the main housings and the secondary housing, recovers a remainder of the lubrication oil injected into the main housings to supply the same to an oil tank, and supplies the air/oil mixture from the secondary housing to an oil separator.

    摘要翻译： 一种用于润滑涡轮发动机的方法和系统，包括至少三个分离的壳体，每个壳体包括至少一个滚子轴承。 该方法通过密封件对壳体进行加压，其中两个主壳体以比剩余的副壳体高的压力被加压，仅通过从主壳体，油雾中的至少一个喷射油雾来润滑次级滚子轴承 由主壳体和副壳体之间的压力差供给，回收注入到主壳体中的润滑油的剩余部分，以将其供应到油箱，并将空气/油混合物从次级壳体供应到油 分隔器。

    Sealing system between two coaxial rotary shafts
    10.
    发明授权
    Sealing system between two coaxial rotary shafts 有权
    两个同轴旋转轴之间的密封系统

    公开(公告)号：US07938616B2

    公开(公告)日：2011-05-10

    申请号：US11868043

    申请日：2007-10-05

    申请人： Laurent Gille ,  Serge Rene Morreale

    发明人： Laurent Gille ,  Serge Rene Morreale

    IPC分类号： F01D11/04

    CPC分类号： F16J15/42

    摘要： A dynamic sealing system between two coaxial rotary shafts respectively comprising an inner shaft and an outer shaft. Connected to the inner shaft, the system comprises a sectorized annular assembly of wipers that are movable under the effect of centrifugal force, and an annular receptacle for liquid arranged in the inside surface of the outer shaft.

    摘要翻译： 分别包括内轴和外轴的同轴旋转轴之间的动态密封系统。 该系统连接到内轴，该系统包括在离心力作用下可移动的刮水器扇形环形组件和布置在外轴内表面中的用于液体的环形容器。