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1.发明授权Stationary actuator device for controlling the pitch of fan blades of a turboprop 有权用于控制涡轮螺旋桨发生器风扇叶片间距的固定致动器装置公开(公告)号：US09284041B2
公开(公告)日：2016-03-15
申请号：US13375024
申请日：2010-04-16
CPC分类号： B64C11/32 , B64C11/48 , B64D2027/026 , F01D7/00 , F05D2260/79
摘要： A device for controlling pitch of fan blades of a turboprop including at least one set of variable-pitch fan blades constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade coupled for pitch adjustment to a synchronization ring. A turntable is mounted via a rotary connection to a rod of an actuator that is secured to a stationary structural element of the turboprop, the turntable being mechanically connected to the synchronization ring by a plurality of connection arms hinge-mounted on the turntable and connected to the synchronization ring such that a longitudinal movement of the turntable under drive from the actuator causes the synchronization ring to turn about the longitudinal axis.
摘要翻译： 一种用于控制涡轮螺旋桨飞机的风扇叶片间距的装置，包括至少一组可变桨距风扇叶片，其被限制为以纵向轴线为中心并机械地连接到涡轮机转子的旋转环旋转，每个叶片被耦合用于俯仰调节到 同步环 转盘通过旋转连接安装到致动器的杆上，致动器的杆被固定到涡轮螺旋桨发生器的固定结构元件上，转盘通过铰链安装在转台上的多个连接臂机械连接到同步环上，并连接到 所述同步环使得在来自致动器的驱动下的转台的纵向运动导致同步环围绕纵向轴线转动。
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2.发明申请DEVICE FOR ATTACHING HAMMER CLAMP BLADES, ASSOCIATED COMPRESSOR HUB, COMPRESSOR AND TURBINE ENGINE 有权用于连接HAMMER夹紧刀片，相关压缩机座，压缩机和涡轮发动机的装置公开(公告)号：US20110255983A1
公开(公告)日：2011-10-20
申请号：US13141586
申请日：2009-12-01
IPC分类号： F01D5/30
CPC分类号： F01D5/3038 , F01D5/32 , Y02T50/673
摘要： The invention relates to a locking device for enabling the circular locking of a set of blades provided with a hammer base (5) on the rim of a turbine engine compressor hub (3), said rim comprising a peripheral groove (4) on the outer surface thereof for receiving the bases (5) of the blades of said set and two shoulders (7) framing said groove with surfaces which form bearings for holding said blades, said rim also comprising a cut-out (8) provided in at least one of said shoulders (7) to enable the bases (5) of the blades to be inserted in said groove (4), said device comprising a means (10) for translatably immobilising the blades in said groove, suitable for being positioned in said groove (4) between two consecutive blades and in turn translatably held in said groove by an attachment means, characterised in that said carrier is shaped so as to fit into said cut-out (8) and to rest circumferentially on at least one engagement surface (9a, 9b) of said shoulder (7).
摘要翻译： 本发明涉及一种锁定装置，用于能够在涡轮发动机压缩机毂（3）的轮辋上设置有锤槌基座（5）的一组叶片的圆形锁定，所述轮辋包括在外侧的周向槽（4） 用于接收所述组件的叶片的基部（5）的表面和两个肩部（7），所述两个肩部（7）用形成用于保持所述叶片的轴承的表面构成所述凹槽，所述边缘还包括切口（8），设置在至少一个 的所述肩部（7）上以使得所述刀片的基部（5）能够插入所述凹槽（4）中，所述装置包括用于可移动地固定所述凹槽中的刀片的装置（10），适于定位在所述凹槽 （4），并且通过附接装置可转动地保持在所述凹槽中，其特征在于，所述托架成形为适合于所述切口（8）并且周向地搁置在至少一个接合表面（ 9a，9b）。
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3.发明申请STATIONARY ACTUATOR DEVICE FOR CONTROLLING THE PITCH OF FAN BLADES OF A TURBOPROP 有权用于控制涡轮风机叶片的定位致动器装置公开(公告)号：US20120099987A1
公开(公告)日：2012-04-26
申请号：US13375024
申请日：2010-04-16
IPC分类号： B64C11/30
CPC分类号： B64C11/32 , B64C11/48 , B64D2027/026 , F01D7/00 , F05D2260/79
摘要： A device for controlling pitch of fan blades of a turboprop including at least one set of variable-pitch fan blades constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade coupled for pitch adjustment to a synchronization ring. A turntable is mounted via a rotary connection to a rod of an actuator that is secured to a stationary structural element of the turboprop, the turntable being mechanically connected to the synchronization ring by a plurality of connection arms hinge-mounted on the turntable and connected to the synchronization ring such that a longitudinal movement of the turntable under drive from the actuator causes the synchronization ring to turn about the longitudinal axis.
摘要翻译： 一种用于控制涡轮螺旋桨飞机的风扇叶片间距的装置，包括至少一组可变桨距风扇叶片，其被限制为以纵向轴线为中心并机械地连接到涡轮机转子的旋转环旋转，每个叶片被耦合用于俯仰调节到 同步环 转盘通过旋转连接安装到致动器的杆上，致动器的杆被固定到涡轮螺旋桨发生器的固定结构元件上，转盘通过铰链安装在转台上的多个连接臂机械连接到同步环上，并连接到 所述同步环使得在来自致动器的驱动下的转台的纵向运动导致同步环围绕纵向轴线转动。
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公开(公告)号：US20120093652A1
公开(公告)日：2012-04-19
申请号：US13320438
申请日：2010-05-11
IPC分类号： F01D7/00
CPC分类号： B64C11/306 , B64C11/06 , B64C11/32 , B64C11/48 , B64D2027/005 , F01D7/00 , F02C6/206 , F04D29/323 , F05D2250/34 , F05D2260/74 , F05D2260/79 , Y02T50/66
摘要： A turbomachine including at least one unducted propeller with variable pitch blades, the blades being carried by respective plates mounted to pivot in radial housings of a rotor element and connected to a control ring that is driven in rotation about the axis of the turbomachine together with the rotor element, and that is movable in translation along the axis to pivot the plates about their axes, the control ring being centered and guided in rotation about the axis on a mechanism that is stationary in rotation and movable in translation along the axis by an actuator carried by the stator of the turbomachine.
摘要翻译： 一种涡轮机，包括至少一个具有可变桨距叶片的未被驱动的推进器，所述叶片由相应的板承载，所述叶片安装成在转子元件的径向壳体中枢转并连接到控制环，所述控制环与所述涡轮机的轴线一起旋转驱动， 转子元件，并且其可沿着轴线平移地移动以使板围绕其轴线枢转，控制环在围绕轴线旋转的中心并被引导在机构上，该机构在旋转中是静止的并且可以通过致动器沿轴线平移地移动 由涡轮机的定子承载。
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公开(公告)号：US08864470B2
公开(公告)日：2014-10-21
申请号：US13320438
申请日：2010-05-11
IPC分类号： B64C11/40 , B64C11/30 , B64C11/48 , F02C6/20 , F04D29/32 , F01D7/00 , B64C11/32 , B64C11/06 , B64D27/00
CPC分类号： B64C11/306 , B64C11/06 , B64C11/32 , B64C11/48 , B64D2027/005 , F01D7/00 , F02C6/206 , F04D29/323 , F05D2250/34 , F05D2260/74 , F05D2260/79 , Y02T50/66
摘要： A turbomachine including at least one unducted propeller with variable pitch blades, the blades being carried by respective plates mounted to pivot in radial housings of a rotor element and connected to a control ring that is driven in rotation about the axis of the turbomachine together with the rotor element, and that is movable in translation along the axis to pivot the plates about their axes, the control ring being centered and guided in rotation about the axis on a mechanism that is stationary in rotation and movable in translation along the axis by an actuator carried by the stator of the turbomachine.
摘要翻译： 一种涡轮机，包括至少一个具有可变桨距叶片的未被驱动的推进器，所述叶片由相应的板承载，所述叶片安装成在转子元件的径向壳体中枢转并连接到控制环，所述控制环与所述涡轮机的轴线一起旋转驱动， 转子元件，并且其可沿着轴线平移地移动以使板围绕其轴线枢转，控制环在围绕轴线旋转的中心并被引导在机构上，该机构在旋转中是静止的并且可以通过致动器沿轴线平移地移动 由涡轮机的定子承载。
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6.发明授权Device for attaching hammer clamp blades, associated compressor hub, compressor and turbine engine 有权用于连接锤式夹片，相关压缩机毂，压缩机和涡轮发动机的装置公开(公告)号：US08834124B2
公开(公告)日：2014-09-16
申请号：US13141586
申请日：2009-12-01
CPC分类号： F01D5/3038 , F01D5/32 , Y02T50/673
摘要： A locking device for enabling the circular locking of a set of blades provided with a hammer base on the rim of a turbine engine compressor hub is disclosed. The rim includes a peripheral groove on the outer surface thereof for receiving the bases of the blades of the set and two shoulders framing the groove with surfaces which form bearings for holding the blades; and a cut-out provided in at least one of the shoulders to enable the bases of the blades to be inserted in the groove. The locking device translatably immobilizes the blades in the groove and is positioned in the groove between two consecutive blades and in turn translatably held in the groove by an attachment device. A carrier is shaped so as to fit into the cut-out and to rest circumferentially on at least one engagement surface of the shoulder.
摘要翻译： 公开了一种用于实现在涡轮发动机压缩机毂的边缘上设置有锤基座的一组叶片的圆形锁定的锁定装置。 边缘包括在其外表面上的周边槽，用于接纳该组件的叶片的基部，并且两个肩部的凹槽与形成用于保持叶片的轴承的表面相结合; 以及设置在至少一个肩部中的切口，以使刀片的基部能够插入凹槽中。 锁定装置将刀片平滑地固定在凹槽中，并且定位在两个连续刀片之间的槽中，并且通过附接装置可转动地保持在凹槽中。 托架被成形为适合于切口并且周向地搁置在肩部的至少一个接合表面上。
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7.发明授权公开(公告)号：US08303189B2
公开(公告)日：2012-11-06
申请号：US12478281
申请日：2009-06-04
摘要： A bearing support journal for an internal shaft of a gas turbine engine including a device for retaining a sealing sleeve surrounding the shaft is disclosed. The retaining device includes a full radial annular flange formed upstream on an axial cylindrical part of the journal, the full flange being intended to butt axially against a radial annular flange of the sealing sleeve; and a tangential immobilizing device for immobilizing the sealing sleeve with respect to the journal, the tangential immobilizing device being created downstream on the axial cylindrical part of the journal.
摘要翻译： 公开了一种用于燃气涡轮发动机的内轴的轴承支撑轴颈，其包括用于保持围绕轴的密封套筒的装置。 保持装置包括形成在轴颈的轴向圆柱形部分上游的全径向环形凸缘，整个凸缘旨在轴向抵靠密封套筒的径向环形凸缘; 以及用于相对于轴颈固定密封套筒的切向固定装置，切向固定装置在轴颈的轴向圆柱形部分的下游形成。
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8.发明授权Turbine engine stator wheel and a turbine or a compressor including such a stator wheel 有权涡轮发动机定子轮和包括这种定子轮的涡轮或压缩机公开(公告)号：US09518472B2
公开(公告)日：2016-12-13
申请号：US14234268
申请日：2012-07-18
CPC分类号： F01D9/04 , F01D9/042 , F01D25/246 , F05D2300/21 , F05D2300/222 , F05D2300/603 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing.
摘要翻译： 涡轮喷嘴包括多个复合材料叶片，每个叶片包括内平台，在外部具有附接凸片的外平台以及在内平台和外平台之间延伸并固定到其上的至少一个翼型件。 叶片的附接突片接合在支撑所有叶片的金属组件环上，沿着相邻叶片的外平台连续延伸，并且在叶片和涡轮壳体之间形成不同的组件部分。
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公开(公告)号：US08932020B2
公开(公告)日：2015-01-13
申请号：US13322027
申请日：2010-05-21
CPC分类号： F01D5/066 , F05D2250/712 , Y02T50/671
摘要： A low-pressure turbine for a turbomachine including turbine disks with festooned annular flanges for fastening to a festooned annular flange of a drive cone connecting the turbine disks to a turbine shaft, solid portions of the festooned annular flanges of the turbine disks and of the drive cone being connected to peripheries of the turbine disks and of the drive cone, respectively, via concave filets that are asymmetrical.
摘要翻译： 一种用于涡轮机的低压涡轮机，包括具有带有环形凸缘的涡轮盘，其具有用于紧固到将涡轮盘连接到涡轮轴的驱动锥的花键环形凸缘，涡轮盘的花式环形凸缘和驱动器的实心部分 锥体分别通过不对称的凹形盘连接到涡轮盘和驱动锥的周边。
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10.发明申请TURBINE ENGINE STATOR WHEEL AND A TURBINE OR A COMPRESSOR INCLUDING SUCH A STATOR WHEEL 有权涡轮发动机定子轮和涡轮机或包括这种定子轮的压缩机公开(公告)号：US20140147264A1
公开(公告)日：2014-05-29
申请号：US14234268
申请日：2012-07-18
IPC分类号： F01D9/04
CPC分类号： F01D9/04 , F01D9/042 , F01D25/246 , F05D2300/21 , F05D2300/222 , F05D2300/603 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing.
摘要翻译： 涡轮喷嘴包括多个复合材料叶片，每个叶片包括内平台，在外部具有附接凸片的外平台以及在内平台和外平台之间延伸并固定到其上的至少一个翼型件。 叶片的附接突片接合在支撑所有叶片的金属组件环上，沿着相邻叶片的外平台连续延伸，并且在叶片和涡轮壳体之间形成不同的组件部分。
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