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公开(公告)号：US08152447B2
公开(公告)日：2012-04-10
申请号：US12335028
申请日：2008-12-15
IPC分类号： F01D1/02
CPC分类号： B64D27/26 , F01D25/162 , F02C7/20 , F02K3/06 , F05D2220/323 , Y02T50/671
摘要： The invention relates to an intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also front and rear flanges (25, 27) which are arranged radially inside with respect to the outer shell, the casing (21) also comprising structural arms (17) which extend radially between the flanges as far as the shell (23), the rear flange being equipped with receiving means (34) for receiving a fixing bracket for fixing a rod for absorbing the thrust forces, and the first receiving means comprising bosses (36) coming from the rear flange, through which bosses through-orifices (38) are formed which are passed through by fixing screws of the bracket. According to the invention, at least one of the bosses (36) extends as far as making contact with one of the structural arms (17).
摘要翻译： 本发明涉及一种用于飞机喷气发动机的中间壳体（21），其包括外壳（23）以及相对于外壳径向向内设置的前后凸缘（25,27），壳体（21 ）还包括在所述凸缘之间径向延伸至所述壳体（23）的结构臂（17），所述后凸缘装备有用于接收用于固定用于吸收推力的杆的固定支架的接收装置（34），以及 所述第一接收装置包括来自所述后凸缘的凸起（36），通过所述凸起（36）形成所述凸起通孔（38），所述凸起通过所述支架的固定螺钉穿过。 根据本发明，至少一个凸台（36）延伸成与其中一个结构臂（17）接触。
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公开(公告)号：US09771968B2
公开(公告)日：2017-09-26
申请号：US14129458
申请日：2012-07-03
申请人： Thierry Francois Maurice Duchatelle , Virginie Guilbert , Cedric Magret , Thierry Georges Paul Papin
发明人： Thierry Francois Maurice Duchatelle , Virginie Guilbert , Cedric Magret , Thierry Georges Paul Papin
CPC分类号： F16C3/023 , F01D9/065 , F01D25/162 , F02C7/32
摘要： A vaned wheel device traversed by a radial drive shaft includes radial arms, one of which contains the shaft, and stationary vanes manufactured separately from the casing and a ferrule and assembled thereto. A sleeve encompassing the shaft traverses the casing and serves to support a bearing for supporting the shaft with positional accuracy, and maintaining tightness by forming a single cavity with the radial arm cavities traversing the shaft.
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公开(公告)号：US20140135134A1
公开(公告)日：2014-05-15
申请号：US14129458
申请日：2012-07-03
申请人： Thierry Francois Maurice Duchatelle , Virgine Guilbert , Cedric Magret , Thierry Georges Paul Papin
发明人： Thierry Francois Maurice Duchatelle , Virgine Guilbert , Cedric Magret , Thierry Georges Paul Papin
IPC分类号： F16C3/02
CPC分类号： F16C3/023 , F01D9/065 , F01D25/162 , F02C7/32
摘要： A vaned wheel device traversed by a radial drive shaft includes radial arms, one of which contains the shaft, and stationary vanes manufactured separately from the casing and a ferrule and assembled thereto. A sleeve encompassing the shaft traverses the casing and serves to support a bearing for supporting the shaft with positional accuracy, and maintaining tightness by forming a single cavity with the radial arm cavities traversing the shaft.
摘要翻译： 由径向驱动轴穿过的铲车装置包括径向臂，其中一个包含轴，以及与壳体分开制造的固定叶片和组装在其上的套圈。 围绕轴的套筒穿过壳体并用于支撑用于以位置精度支撑轴的轴承，并且通过形成具有穿过轴的径向臂空腔的单个空腔来保持紧密性。
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公开(公告)号：US20090155063A1
公开(公告)日：2009-06-18
申请号：US12335028
申请日：2008-12-15
IPC分类号： F01D1/02
CPC分类号： B64D27/26 , F01D25/162 , F02C7/20 , F02K3/06 , F05D2220/323 , Y02T50/671
摘要： The invention relates to an intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also front and rear flanges (25, 27) which are arranged radially inside with respect to the outer shell, the casing (21) also comprising structural arms (17) which extend radially between the flanges as far as the shell (23), the rear flange being equipped with receiving means (34) for receiving a fixing bracket for fixing a rod for absorbing the thrust forces, and the first receiving means comprising bosses (36) coming from the rear flange, through which bosses through-orifices (38) are formed which are passed through by fixing screws of the bracket. According to the invention, at least one of the bosses (36) extends as far as making contact with one of the structural arms (17).
摘要翻译： 本发明涉及一种用于飞机喷气发动机的中间壳体（21），其包括外壳（23）以及相对于外壳径向向内设置的前后凸缘（25,27），壳体（21 ）还包括在所述凸缘之间径向延伸至所述壳体（23）的结构臂（17），所述后凸缘装备有用于接收用于固定用于吸收推力的杆的固定支架的接收装置（34），以及 所述第一接收装置包括来自所述后凸缘的凸起（36），通过所述凸起（36）形成所述凸起通孔（38），所述凸起通过所述支架的固定螺钉穿过。 根据本发明，至少一个凸台（36）延伸成与其中一个结构臂（17）接触。
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公开(公告)号：US08646744B2
公开(公告)日：2014-02-11
申请号：US12996562
申请日：2009-05-14
申请人： Thierry Francois Maurice Duchatelle , Thierry Georges Paul Papin , Dominique Raulin , Arnaud Sanchez
发明人： Thierry Francois Maurice Duchatelle , Thierry Georges Paul Papin , Dominique Raulin , Arnaud Sanchez
CPC分类号： F01D25/246 , F01D9/04 , F01D25/243 , F05D2230/60 , Y02T50/672
摘要： A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.
摘要翻译： 用于涡轮机械的结构框架，例如中间框架或排气框架，所述框架包括至少两个同轴环，内环和外环以及连接所述环的径向臂。 这些元件中的至少一个包括通过螺栓固定在一起的多个部件。
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6.发明申请INTERMEDIATE CASING EXTENSION FOR AN AIRCRAFT JET ENGINE, COMPRISING A SECTORISED ANNULAR GROOVE FOR RECEIVING THE NACELLE COVERS 有权航空喷气机发动机的中间延伸延伸，包括用于接收NACELLE COVERS的横断面公开(公告)号：US20090155070A1
公开(公告)日：2009-06-18
申请号：US12334949
申请日：2008-12-15
IPC分类号： F01D25/28
CPC分类号： B64D27/26 , B64D29/06 , F01D25/162 , F02C7/20 , F02K3/06 , F05D2220/323 , F05D2230/64 , Y02E10/726 , Y02T50/44 , Y02T50/671
摘要： The invention relates to an extension (30) of an intermediate casing for an aircraft jet engine, intended to project towards the downstream end from an external shell of the intermediate casing, this extension comprising an annular connecting downstream end (64) forming an annular groove (66) open radially towards the outside, intended to receive nacelle covers. According to the invention, the annular connecting downstream end (64) is produced by means of a plurality of angular sectors (76a, 76b).
摘要翻译： 本发明涉及一种用于飞机喷气发动机的中间壳体的延伸部（30），其旨在从中间壳体的外壳向下游端突出，该延伸部包括形成环形凹槽的环形连接下游端（64） （66）朝向外部径向开口，用于接收机舱盖。 根据本发明，通过多个角扇区（76a，76b）产生环形连接下游端（64）。
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7.发明授权Intermediate casing extension for an aircraft jet engine, comprising a sectorised annular groove for receiving the nacelle covers 有权用于飞机喷气发动机的中间套管延伸部，包括用于接纳机舱盖的扇形环形槽公开(公告)号：US08172527B2
公开(公告)日：2012-05-08
申请号：US12334949
申请日：2008-12-15
CPC分类号： B64D27/26 , B64D29/06 , F01D25/162 , F02C7/20 , F02K3/06 , F05D2220/323 , F05D2230/64 , Y02E10/726 , Y02T50/44 , Y02T50/671
摘要： An extension of an intermediate casing for an aircraft jet engine, intended to project towards the downstream end from an external shell of said intermediate casing is disclosed. This extension includes an annular connecting downstream end forming an annular groove open radially towards the outside, intended to receive nacelle covers. The annular connecting downstream end is produced by a plurality of angular sectors.
摘要翻译： 公开了一种用于飞机喷气发动机的中间壳体的延伸部分，其旨在从所述中间壳体的外壳向下游端突出。 该延伸部包括环形连接下游端，形成径向朝向外部开口的环形槽，用于接纳机舱盖。 环形连接下游端由多个角扇区产生。
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公开(公告)号：US20090104027A1
公开(公告)日：2009-04-23
申请号：US12245183
申请日：2008-10-03
IPC分类号： F04D29/06
CPC分类号： F01D25/162 , F01D9/065 , F01D25/18 , F02C7/32 , Y02T50/671
摘要： The present invention relates to an intermediate casing of a turbojet comprising, between an inner hub and an outer cylindrical shroud, a plurality of radial arms at least one of which is hollow, a radial transmission shaft for driving the auxiliary machines being mounted rotatably in said radial arm, a first end of the transmission shaft passing through the inner hub and the second end passing through the outer cylindrical shroud. The housing is notable in that the inner volume consists of a single compartment housing the transmission shaft and forming a passageway for a lubrication fluid.
摘要翻译： 涡轮喷气发动机的中间壳体技术领域本发明涉及一种涡轮喷气发动机的中间壳体，其包括在内轮毂和外圆柱形护罩之间的至少一个中空的多个径向臂，用于驱动辅助机器的径向传动轴，其可旋转地安装在所述 径向臂，传动轴的第一端穿过内轮毂，第二端穿过外圆筒形护罩。 外壳是显着的，因为内部容积由容纳传动轴并形成用于润滑流体的通道的单个隔室组成。
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