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1. 发明申请

US20180171878A1 ADJUSTMENT DEVICE FOR ADJUSTING SEVERAL GUIDE VANES OF AN ENGINE 审中-公开
公开(公告)号：US20180171878A1
公开(公告)日：2018-06-21
申请号：US15842076
申请日：2017-12-14
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Mats Rudolf MOJEM
IPC分类号： F02C9/22
CPC分类号： F02C9/22 , F01D17/162 , F05D2230/644 , F16C3/12 , F16C3/28 , F16C17/02 , F16C17/18 , F16C2360/23 , F16C2361/61
摘要： An adjustment device for adjusting several guide vanes of the engine, wherein the adjustment device includes at least one adjusting element that couples with the guide vanes and is mounted in an adjustable manner, a connection element that couples with the adjusting element, as well as a crank shaft for controlling an adjusting movement of the adjusting element, and the crank shaft has at least one coupling element which couples with the connection element and at which the connection element is hinged to transform a rotational movement of the crank shaft about a longitudinal axis of the crank shaft into an adjusting movement of the adjusting element for adjusting the guide vanes. The crank shaft has a modular design with at least two shaft modules that are arranged behind each other along the longitudinal axis of the crank shaft.

2. 发明申请

US20180087400A1 TURBINE RING ASSEMBLY COMPRISING A COOLING AIR DISTRIBUTION ELEMENT 有权
公开(公告)号：US20180087400A1
公开(公告)日：2018-03-29
申请号：US15818039
申请日：2017-11-20
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Lucien Henri Jacques QUENNEHEN , Sébastien Serge Francis CONGRATEL , Clément Jean Pierre DUFFAU , Nicolas Paul TABLEAU
IPC分类号： F01D25/12 , F01D25/00 , F01D25/24 , F01D11/08
CPC分类号： F01D25/12 , F01D11/08 , F01D11/24 , F01D25/005 , F01D25/246 , F01D25/28 , F05D2220/32 , F05D2230/64 , F05D2230/642 , F05D2230/644 , F05D2240/11 , F05D2250/75 , F05D2260/221 , F05D2260/30 , F05D2300/5021 , F05D2300/50212 , F05D2300/6033
摘要： A turbine ring assembly includes a plurality of ring segments and a ring support structure, the ring assembly further including, for each ring segment, a cooling distribution element fixed to the ring support structure and positioned in a first cavity delimited between the turbine ring and the ring support structure.

3. 发明授权

US09896963B2 Coupling part structure for vane and jet engine including the same 有权
公开(公告)号：US09896963B2
公开(公告)日：2018-02-20
申请号：US14398360
申请日：2014-10-31
申请人： IHI CORPORATION , IHI AEROSPACE CO., LTD
发明人： Takaomi Inada , Shinichi Tanaka
IPC分类号： F01D25/00 , F01D9/02 , F01D5/28 , F01D25/24
CPC分类号： F01D25/005 , F01D5/282 , F01D9/02 , F01D25/24 , F05D2230/644 , F05D2240/12 , F05D2260/31 , F05D2300/44 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： A coupling support member including a pair of divided pieces is placed in a coupling part between a vane proximal end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane proximal end portion from both the sides in the vane thickness direction. A groove is formed in one end portion joint surface of the coupling support member, a linear protrusion is formed on the other end portion joint surface, the vane proximal end portion is formed into a concavo-convex shape, a linear protrusion that is engaged with the groove which is formed in the end portion joint surface is formed on a joint surface to the one end portion joint surface, a groove that is engaged with the linear protrusion formed on the end portion joint surface is formed in the joint surface to the other end portion joint surface. The vane proximal end portion is held between the pair of divided pieces of the coupling support member, by the fastening force that is applied to the coupling support member from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine.

4. 发明申请

US20170370245A1 GAS TURBINE ENGINE FRAME ALIGNMENT TOOL 审中-公开
公开(公告)号：US20170370245A1
公开(公告)日：2017-12-28
申请号：US15584902
申请日：2017-05-02
申请人： Rolls-Royce Corporation
发明人： Daniel J. Hassan, III
IPC分类号： F01D21/00 , G01B11/27 , F02C3/04 , F02C7/20
CPC分类号： F01D21/003 , F01D25/24 , F02C3/04 , F02C7/20 , F05D2220/32 , F05D2230/64 , F05D2230/644 , F05D2240/35 , F05D2240/90 , F05D2260/80 , G01B5/0004 , G01B11/27
摘要： Devices, systems, and methods for alignment of gas turbine engine components including frame components.

5. 发明授权

US09840937B2 Turbine exhaust cylinder/ turbine exhaust manifold bolted stiffening ribs 有权
公开(公告)号：US09840937B2
公开(公告)日：2017-12-12
申请号：US14596684
申请日：2015-01-14
申请人： Siemens Energy, Inc.
发明人： Yevgeniy P. Shteyman , John Giaimo , Daniel M. Eshak , Thomas Heylmun
IPC分类号： F01D25/30 , F01D25/04 , F01D25/16
CPC分类号： F01D25/04 , F01D25/162 , F01D25/30 , F05D2230/644
摘要： Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer.

6. 发明授权

US09587511B2 Turbomachine cold clearance adjustment 有权
标题翻译：涡轮机冷间隙调整
公开(公告)号：US09587511B2
公开(公告)日：2017-03-07
申请号：US14105834
申请日：2013-12-13
申请人： General Electric Company
发明人： Fred Thomas Willett, Jr. , Kenneth Michael Koza
IPC分类号： F01D11/22 , F01D21/00 , F01D25/24 , G01B7/14 , G01B11/14
CPC分类号： F01D21/003 , F01D25/24 , F05D2230/644 , F05D2260/80 , F05D2270/804 , F05D2270/821 , G01B7/14 , G01B11/14 , Y10T29/49323
摘要： A system and method for measuring and adjusting rotor to stator clearances is disclosed, as well as a turbomachine embodying the system and method. In an embodiment, a turbomachine is assembled, including a stator having an upper and a lower stator shell, and a rotor disposed within the stator. A cold clearance between the rotor and the stator is determined at each of a plurality of clearance measurement points using an in situ clearance sensor system. Each of the clearance measurement points is axially spaced from each other clearance measurement point. The cold clearance between the rotor and the stator is adjusted based on the determined cold clearances, by displacing one of the upper stator shell or the lower stator shell relative to a foundation, thereby changing a shape of the upper stator shell or the lower stator shell to accommodate a position of the rotor within the stator.
摘要翻译：公开了一种用于测量和调整转子到定子间隙的系统和方法，以及体现该系统和方法的涡轮机。在一个实施例中，组装涡轮机，包括具有上和下定子壳的定子和设置在定子内的转子。使用原位间隙传感器系统，在多个间隙测量点的每一个处确定转子和定子之间的冷空隙。每个间隙测量点与彼此的间隙测量点轴向间隔开。基于所确定的冷间隙，通过使上定子壳或下定子壳中的一个相对于基座移位，从而改变上定子壳或下定子壳的形状来调节转子和定子之间的冷空隙以容纳转子在定子内的位置。

7. 发明申请

US20160305287A1 POSITIONING DEVICE, ROTARY MACHINE COMPRISING SAME, AND POSITIONING METHOD 审中-公开
标题翻译：定位装置，包括它的旋转机和定位方法
公开(公告)号：US20160305287A1
公开(公告)日：2016-10-20
申请号：US15102392
申请日：2014-12-17
申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.
发明人： Shinya HONDA , Akihiko SHIROTA
IPC分类号： F01D25/24 , F01D9/04
CPC分类号： F01D25/246 , F01D9/041 , F01D25/26 , F05D2220/31 , F05D2230/64 , F05D2230/644 , F05D2240/128 , F05D2240/14
摘要： A pin insertion hole penetrating an outer member from an outer circumferential side to an inner circumferential side is formed in the outer member. A pin groove that is concave from an outer circumferential side to an inner circumferential side is formed in an inner member. A positioning device includes a pin that is inserted into the pin insertion hole of the outer member and the pin groove of the inner member, a liner holder that comes in contact with a groove side surface of the pin groove, and a liner that is disposed between the liner holder and the pin in the pin groove.
摘要翻译：在外部构件中形成有从外周侧向内周侧贯穿外侧构件的销插入孔。在内部构件中形成从外周侧向内周侧凹陷的销槽。定位装置包括插入到外部构件的销插入孔和内部构件的销槽中的销，与销槽的槽侧表面接触的衬垫保持器和布置在衬套中的衬垫在衬套保持器和销槽中的销之间。

8. 发明授权

US09441501B2 Turbine shell with pin support 有权
公开(公告)号：US09441501B2
公开(公告)日：2016-09-13
申请号：US14046426
申请日：2013-10-04
申请人： General Electric Company
发明人： Henry Grady Ballard, Jr. , Fred Thomas Willett, Jr.
IPC分类号： F01D25/26 , F01D25/28
CPC分类号： F01D25/26 , F01D25/28 , F05D2230/642 , F05D2230/644 , F05D2240/40 , F05D2260/36
摘要： A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.

9. 发明申请

US20150345336A1 APPARATUS AND METHOD FOR ADJUSTING AN INNER CASING OF A TURBOMACHINE 有权
标题翻译：用于调节涡轮调节剂的内装的装置和方法
公开(公告)号：US20150345336A1
公开(公告)日：2015-12-03
申请号：US14291070
申请日：2014-05-30
申请人： General Electric Company
发明人： James Adaickalasamy , Pramod Akulu , Kenneth Damon Black
IPC分类号： F01D25/28 , F01D25/24
CPC分类号： F01D25/28 , F01D25/24 , F05D2230/644
摘要： A support assembly for externally adjusting an inner casing with respect to an outer casing for a turbomachine includes a carrier plate, a carrier block that is fixedly connected to the carrier plate, a restrictor block fixedly connected to the carrier plate, a rod coupled to the carrier plate, and a plate threadably connected to the rod. The carrier block includes an inclined side and a carrier side. The restrictor block includes a restrictor side and an inclined side. The restrictor side is generally oriented towards the carrier side. A vertical gap for receiving a support arm of an inner turbine casing is defined between the restrictor side and the carrier side. The plate may be rotated about the rod to cause simultaneous movement of the rod, the carrier plate, the carrier block and the restrictor block, thus adjusting the inner casing with respect to the outer casing.
摘要翻译：用于相对于用于涡轮机的外壳外部调节内壳的支撑组件包括承载板，固定地连接到承载板的承载块，固定地连接到承载板的限制块，连接到所述承载板的杆承载板和螺纹连接到杆的板。载体块包括倾斜侧和载体侧。限流块包括限流器侧和倾斜侧。限流器侧通常朝向载体侧定向。用于接收内涡轮机壳体的支撑臂的垂直间隙限定在限流器侧和载体侧之间。板可以围绕杆旋转以引起杆，承载板，承载块和限制块的同时移动，从而相对于外壳调节内壳。

10. 发明授权

US09057281B2 Axial turbomachine having an axially displaceable guide-blade carrier 有权
标题翻译：轴向涡轮机具有可轴向移动的导向叶片载体
公开(公告)号：US09057281B2
公开(公告)日：2015-06-16
申请号：US13260406
申请日：2010-03-22
申请人： Francois Benkler , Andreas Böttcher , Uwe Kahlstorf , Torsten Matthias , Dieter Minninger , Oliver Schneider , Peter Schröder , Vyacheslav Veitsman
发明人： Francois Benkler , Andreas Böttcher , Uwe Kahlstorf , Torsten Matthias , Dieter Minninger , Oliver Schneider , Peter Schröder , Vyacheslav Veitsman
IPC分类号： F01D1/04 , F01D11/22
CPC分类号： F01D11/22 , F05D2230/64 , F05D2230/644 , F05D2250/314 , F05D2260/50
摘要： An axial turbomachine including a rotor-blade cascade is provided. The turbomachine includes a casing in which the cascade is installed and a guide-blade carrier which encloses the cascade and is integrated into the inner side of the housing. The guide-blade carrier is arranged immediately adjacently to the blade tips faulting a radial gap, wherein the guide-blade carrier is mounted in the housing, such that it may be displaced parallel to the axis of the axial turbomachine, and includes an adjusting ring which is supported on contact surfaces on the housing and guide-blade carrier and may be rotated about the axis, wherein the contact surfaces of the adjusting ring and of the housing and/or of the guide-blade carrier are set with respect to a plane perpendicular to the axis, so that, when the adjusting ring is rotated about the axis, the guide-blade carrier is displaced axially by the adjusting ring.
摘要翻译：提供了包括转子叶片级联的轴向涡轮机。涡轮机包括其中安装有级联的壳体和围绕级联的导向叶片载体并且整合到壳体的内侧。引导叶片托架被紧紧地布置在与刀片尖端相邻的位置上，该刀片尖端具有径向间隙，其中引导刀片托架安装在壳体中，使得其可以平行于轴向涡轮机的轴线移位，并且包括调节环其被支撑在壳体和引导叶片载体上的接触表面上并且可以围绕轴线旋转，其中调节环和壳体的接触表面和/或引导叶片载体的接触表面相对于平面垂直于轴线，使得当调节环围绕轴线旋转时，导向叶片托架由调节环轴向移动。

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