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71. 发明申请

US20060197400A1 ROTATING MACHINE 有权
标题翻译：旋转机
公开(公告)号：US20060197400A1
公开(公告)日：2006-09-07
申请号：US11276360
申请日：2006-02-27
申请人： Andrea De Simone , Jonas Faltstrom , Holger Kiewel , Thomas Kramer , Markus Wiebe
发明人： Andrea De Simone , Jonas Faltstrom , Holger Kiewel , Thomas Kramer , Markus Wiebe
IPC分类号： H02K1/00
CPC分类号： F01D5/30 , F01D5/303 , F01D5/3038 , F01D11/001 , F05D2240/60 , F05D2250/14
摘要： A rotating machine (10), in particular a compressor or turbine, has a rotor shaft (11) which is rotatable about an axis (20) and is provided with at least one slot (14). The mechanical stresses in the region of the slot are reduced in that the at least one slot (14) has a slot bottom (17) with an elliptic cross-sectional contour (24).
摘要翻译：旋转机器（10），特别是压缩机或涡轮机具有转子轴（11），该转子轴可绕轴线（20）旋转并且设置有至少一个槽（14）。槽的区域中的机械应力减小，因为至少一个槽（14）具有具有椭圆形横截面轮廓（24）的槽底（17）。

72. 发明授权

US06902376B2 Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge 失效
公开(公告)号：US06902376B2
公开(公告)日：2005-06-07
申请号：US10327949
申请日：2002-12-26
申请人： James Charles Gautreau , Nicholas Francis Martin
发明人： James Charles Gautreau , Nicholas Francis Martin
IPC分类号： F04D29/38 , F01D5/16 , F01D5/30 , F04D29/32 , F04D29/34
CPC分类号： F01D5/326 , F01D5/16 , F01D5/30 , F04D29/322 , Y10S416/50
摘要： A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.

73. 发明授权

US06761536B1 Turbine blade platform trailing edge undercut 有权
标题翻译：涡轮叶片平台后缘底切
公开(公告)号：US06761536B1
公开(公告)日：2004-07-13
申请号：US10355883
申请日：2003-01-31
申请人： Gary Bash , J. Page Strohl
发明人： Gary Bash , J. Page Strohl
IPC分类号： F01D518
CPC分类号： F01D5/18 , F01D5/30
摘要： A gas turbine blade having an airfoil to platform interface configured to minimize thermal and vibratory stresses is disclosed. This configuration minimizes exposure to the conditions that are known to cause high cycle fatigue and low cycle fatigue cracks. The turbine blade incorporates a channel in the platform trailing edge that extends from the platform concave face to the platform convex face and has a portion having a constant radius. The channel extends a sufficient distance into a stress field created by the aerodynamic loading of the turbine blade airfoil in order to redirect the mechanical stresses away from the blade trailing edge while allowing the platform trailing edge region to be more responsive to thermal fluctuations.
摘要翻译：公开了一种具有构造成使热和振动应力最小化的翼型到平台接口的燃气轮机叶片。这种构造使得暴露于已知导致高循环疲劳和低循环疲劳裂纹的条件下。涡轮机叶片包括平台后缘中的从平台凹面延伸到平台凸面的通道，并且具有恒定半径的部分。通道延伸到由涡轮叶片翼型件的空气动力学负载产生的应力场中的足够的距离，以便将机械应力从叶片后缘重定向，同时允许平台后缘区域对热波动更加响应。

74. 发明申请

US20040126239A1 Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge 失效
标题翻译：压缩机叶片采用燕尾槽开槽，以减少翼型前缘的应力
公开(公告)号：US20040126239A1
公开(公告)日：2004-07-01
申请号：US10327949
申请日：2002-12-26
发明人： James Charles Gautreau , Nicholas Francis Martin
IPC分类号： F01D005/30
CPC分类号： F01D5/326 , F01D5/16 , F01D5/30 , F04D29/322 , Y10S416/50
摘要： A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.
摘要翻译：一种轴流式压缩机的叶片，包括：具有前缘和根部的翼型件; 附着于翼型根部的平台; 连接在与翼型件相对的平台的一侧的燕尾榫; 靠近平台的燕尾脖颈和颈部中的大致平行于平台的狭槽，并且狭槽从颈部的前部延伸到颈部的位置，超过由叶片的前缘形成的线。

75. 发明申请

US20040115046A1 Sealing of steam turbine nozzle hook leakages using a braided rope seal 失效
标题翻译：使用编织绳密封密封汽轮机喷嘴钩泄漏
公开(公告)号：US20040115046A1
公开(公告)日：2004-06-17
申请号：US10316103
申请日：2002-12-11
发明人： John Thomas Murphy , Steven Sebastian Burdgick
IPC分类号： F01D011/00
CPC分类号： F01D9/042 , F01D5/30 , F01D11/00
摘要： A steam turbine includes a stator supporting a plurality of turbine nozzles. The stator has shaped grooves for receiving a complementary-shaped nozzle hook formed on an end of each of the turbine nozzles. A rope seal is disposed in each interface between the nozzle hooks and the shaped grooves, respectively. The rope seal serves to seal a leakage path that may exist over the nozzle hooks between the nozzles and respective stator grooves.
摘要翻译：蒸汽轮机包括支撑多个涡轮喷嘴的定子。定子具有成形槽，用于接收形成在每个涡轮喷嘴的端部上的互补形状的喷嘴钩。分别在喷嘴钩和成形槽之间的每个界面中设置绳密封件。绳索密封件用于密封可能存在于喷嘴与相应定子槽之间的喷嘴钩之间的泄漏路径。

76. 发明授权

US06640437B2 Method for installing stator vanes 有权
标题翻译：定子叶片安装方法
公开(公告)号：US06640437B2
公开(公告)日：2003-11-04
申请号：US10355574
申请日：2003-01-31
申请人： Christopher C. McFarland
发明人： Christopher C. McFarland
IPC分类号： B23P1500
CPC分类号： B25B27/00 , B25B27/14 , F01D5/30 , F05D2230/60 , Y10T29/37 , Y10T29/49229 , Y10T29/49318 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49721 , Y10T29/53
摘要： A method for installing stator vanes comprises the steps of installing a first rotor assembly within a case, placing a first inflatable tool over a portion of the first rotor assembly, positioning a first vane array having at least one vane on a surface of the tool, inflating the tool so that a portion of each vane and the first vane array is loaded against the case, and connecting each vane in the first vane array to the case.
摘要翻译：一种用于安装定子叶片的方法包括以下步骤：将第一转子组件安装在壳体内，将第一可充气工具放置在第一转子组件的一部分上，将具有至少一个叶片的第一叶片阵列定位在工具的表面上，使工具膨胀，使得每个叶片和第一叶片阵列的一部分被装载到壳体上，并将第一叶片阵列中的每个叶片连接到壳体。

77. 发明申请

US20030140493A1 Pneumatic press vane lift installation tool 有权
公开(公告)号：US20030140493A1
公开(公告)日：2003-07-31
申请号：US10355574
申请日：2003-01-31
发明人： Christopher C. McFarland
IPC分类号： B21K003/04 , B23P015/02
CPC分类号： B25B27/00 , B25B27/14 , F01D5/30 , F05D2230/60 , Y10T29/37 , Y10T29/49229 , Y10T29/49318 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49721 , Y10T29/53
摘要： The present invention relates to a pneumatic press vane lift installation tool. The tool is formed by two inflatable, substantially semi-circular tubes which are placed between a rotor assembly and a vane assembly during the installation of the vane assembly. The tubes are each positioned adjacent an inner end of the vanes in the vane assembly and are each inflated to apply a lifting force to the vanes. The vanes are then attached to the engine case.

78. 发明授权

US06234756B1 Segmented ring blade retainer 失效
标题翻译：分段环形刀片保持架
公开(公告)号：US06234756B1
公开(公告)日：2001-05-22
申请号：US09179028
申请日：1998-10-26
申请人： Robert Anthony Ress, Jr. , Edward Claude Rice
发明人： Robert Anthony Ress, Jr. , Edward Claude Rice
IPC分类号： F01D532
CPC分类号： F01D5/30 , F01D5/3015 , Y10T29/49948 , Y10T403/60
摘要： A retainer for a rotor disk assembly of a gas turbine engine forms one aspect of the present invention. The retainer prevents axial displacement of a plurality of blades coupled to the rotor disk. The retainer includes a plurality of retaining segments and a locking segment. The locking segment is positioned between two of the retaining segments to define a first joint and a second joint. The first and second joints are offset a distance from and are substantially parallel to an axis extending through the center of the rotor disk assembly. The retainer may also be provided with means for preventing displacement of the retainer towards the center of the rotor disk assembly.
摘要翻译：用于燃气涡轮发动机的转子盘组件的保持器形成本发明的一个方面。保持器防止耦合到转子盘的多个叶片的轴向位移。保持器包括多个保持段和锁定段。锁定段位于两个保持段之间，以限定第一关节和第二关节。第一和第二关节偏离与延伸穿过转子盘组件的中心的轴线的距离并且基本平行于轴线。保持器还可以设置有用于防止保持器朝向转子盘组件的中心的位移的装置。

79. 发明授权

US6139276A Ceiling fan assembly and method for assembling same 失效
公开(公告)号：US6139276A
公开(公告)日：2000-10-31
申请号：US196798
申请日：1998-11-20
申请人： Frank Blateri , Wang Liang Chou
发明人： Frank Blateri , Wang Liang Chou
IPC分类号： F01D5/30 , F01D25/06 , F04D25/08 , F04D29/34 , B63H1/20
CPC分类号： F04D29/34 , F01D25/06 , F01D5/30 , F04D25/088
摘要： A fan assembly according to which a block member is connected to a rotor end casing and an arm member having a blade connected thereto is mounted to the block member. One of the members has a radially extending slot formed therein and the other member has a mounting flange adapted to extend into the slot when the arm is moved radially outwardly relative to the block member to mount the arm to the block member without the need for additional components.

80. 发明授权

US5224831A Fan blade protection system 失效
标题翻译：风扇叶片保护系统
公开(公告)号：US5224831A
公开(公告)日：1993-07-06
申请号：US877351
申请日：1992-04-30
申请人： Thomas C. Hermans , Thomas G. Wakeman , Ambrose A. Hauser
发明人： Thomas C. Hermans , Thomas G. Wakeman , Ambrose A. Hauser
IPC分类号： B64C11/02 , F01D5/30 , F01D21/04
CPC分类号： F01D21/045 , B64C11/06 , B64C11/306 , F01D5/30 , B64D2027/005 , F05D2220/324 , Y02T50/66
摘要： In one type of aircraft propulsion system, propeller blades are mounted on a ring which surrounds a turbine. An annular space exists between the turbine and the ring. If a propeller blade should break free, the unbalanced centrifugal load tends to deform the ring. The invention reduces the deformation, as by locating spacers between the turbine and the ring.
摘要翻译：在一种类型的飞行器推进系统中，螺旋桨叶片安装在环绕涡轮机的环上。在涡轮和环之间存在环形空间。如果螺旋桨叶片脱落，离心力不平衡会使环变形。本发明通过在涡轮机和环之间定位隔板来减少变形。

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