专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20140301854A1 SECUREMENT SYSTEM AND METHOD FOR SECURING AN ATTACHMENT PORTION OF AT LEAST ONE ROTOR BLADE OR ROTOR BLADE SEGMENT IN A MOUNTING SITE OF A ROTOR BASE 有权
标题翻译：安全系统和方法，用于在转子基座的安装位置保护至少一个转子叶片或转子叶片部分的附着部分
公开(公告)号：US20140301854A1
公开(公告)日：2014-10-09
申请号：US14245686
申请日：2014-04-04
申请人： MTU Aero Engines AG
发明人： Frank STIEHLER , Felix KERN
IPC分类号： F01D5/02
CPC分类号： F01D5/02 , F01D5/3007 , F01D5/323 , Y10T29/4932
摘要： A securement system for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base. The securement system has at least one holder element and a second holder element, each of which has a holding portion and a connecting portion. The connecting portions can be introduced into the mounting site so as to establish a clip connection and can be locked together in the mounting site. The holding portions are configured so as to fasten the attachment portion of the at least one rotor blade or of the rotor blade segment in the mounting site in the locked state of the connecting portions. Further disclosed is a method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base and a rotor having a securement system.
摘要翻译：一种固定系统，用于将至少一个转子叶片或转子叶片段的附接部分固定在转子基座的安装位置。固定系统具有至少一个保持器元件和第二保持器元件，每个保持器元件和第二保持器元件具有保持部分和连接部分。连接部分可以被引入安装位置，以便建立夹子连接并且可以在安装位置被锁定在一起。保持部被配置为在连接部的锁定状态下将安装位置中的至少一个转子叶片或转子叶片段的安装部分固定。还公开了一种用于将至少一个转子叶片或转子叶片段的附接部分固定在转子基座的安装位置和具有固定系统的转子上的方法。

2. 发明申请

US20200018171A1 BLADE OR VANE ASSEMBLY FOR A GAS TURBINE AND METHOD OF MANUFACTURE THEREOF 审中-公开
公开(公告)号：US20200018171A1
公开(公告)日：2020-01-16
申请号：US16503689
申请日：2019-07-05
申请人： MTU Aero Engines AG
发明人： Frank STIEHLER , Lars SCHELLHORN
IPC分类号： F01D5/18
摘要： A method for manufacturing a blade or vane assembly having at least one hollow airfoil (10) for a gas turbine, profile sections (A, B, C) of this airfoil being configured (S20) on the basis of a predetermined desired torsion of the airfoil, and the airfoil being manufactured (S30) on the basis of the configured profile sections using an additive manufacturing process (S30).

3. 发明申请

US20170226887A1 GUIDE VANE SYSTEM FOR A TURBOMACHINE 审中-公开
公开(公告)号：US20170226887A1
公开(公告)日：2017-08-10
申请号：US15417959
申请日：2017-01-27
申请人： MTU Aero Engines AG
发明人： Joachim WULF , Frank STIEHLER
IPC分类号： F01D17/16 , F01D11/00 , F01D9/04
CPC分类号： F01D17/162 , F01D9/042 , F01D11/003 , F04D29/563 , F05D2220/323 , F05D2230/60 , F05D2260/36
摘要： The invention relates to a guide vane system for a turbomachine with at least one guide vane, which can be rotatably mounted around an adjustment axis and is arranged with a radially inner end region in a corresponding recess of an inner ring, wherein the arrangement of the guide vane on the inner ring is secured by a securing element in a form-fitting manner. For an especially advantageous securing of this arrangement, it is provided that the securing element is designed as an oblong element, which is arranged at least in a recess and/or through-opening of the radially inner end region of the guide vane directed in the peripheral direction of the turbomachine and is arranged at least in a recess and/or through-opening of the inner ring directed in the peripheral direction of the turbomachine. In addition, the invention relates to a turbomachine, in particular an aircraft engine, and to a method for assembling a guide vane system.

4. 发明申请

US20150061228A1 SEALING ARRANGEMENT IN AN AXIAL TURBOMACHINE 有权
标题翻译：密封安装在轴向涡轮机
公开(公告)号：US20150061228A1
公开(公告)日：2015-03-05
申请号：US14474966
申请日：2014-09-02
申请人： MTU Aero Engines AG
发明人： Frank STIEHLER
IPC分类号： F01D11/00
CPC分类号： F01D11/00 , F01D11/001 , F05D2240/56 , F05D2250/183 , F05D2250/184 , F16J15/3288 , Y02T50/671
摘要： A sealing arrangement (100) in an axial turbomachine between, on the one hand, a rotor (1) and, on the other hand, a stator (3) and/or a housing, including a support device (7, 7′) and a sealing element, whereby the support device (7, 7′) extends essentially in the radial direction (r). In the axial direction (u) of the turbomachine, the support device (7, 7′) has an axial contour that effectuates a stiffening effect for the support device (7, 7′).
摘要翻译：轴向涡轮机中的密封装置（100）一方面在转子（1）之间，另一方面是定子（3）和/或壳体，包括支撑装置（7,7'）和密封元件，由此支撑装置（7,7'）基本上沿径向方向（r）延伸。在涡轮机的轴向（u）上，支撑装置（7,7'）具有轴向轮廓，其对支撑装置（7,7'）施加加强作用。

5. 发明申请

US20140227080A1 SEAL SUPPORT OF TITANIUM ALUMINIDE FOR A TURBOMACHINE 审中-公开
标题翻译：钛酸钡的密封支持用于涡轮机
公开(公告)号：US20140227080A1
公开(公告)日：2014-08-14
申请号：US14166167
申请日：2014-01-28
申请人： MTU Aero Engines AG
发明人： Frank STIEHLER , Stephan KLAEN , Stefan BUSAM , Bernhard THEIS
IPC分类号： F02C7/28
CPC分类号： F02C7/28 , F01D11/001 , F05D2300/182 , Y10T29/49297
摘要： Disclosed is a turbomachine having an annular flow duct and a housing structure surrounding the flow duct and a multiplicity of guide vanes and rotor blades which are arranged in the flow duct. The rotor blades are rotatably accommodated in the housing structure whereas the guide vanes are fixed in the housing structure, a plurality of guide vanes forming an annular guide vane ring. The housing structure has a seal in the region of the radially inner flow duct boundary in order to prevent hot gas escaping from the flow duct, which seal is arranged on guide vane roots of the guide vanes of the guide vane ring via a seal support and forms a seal against a rotatable seal surface, the seal support being formed from an intermetallic material, in particular a TiAl material.
摘要翻译：公开了一种涡轮机，其具有环形流动管道和围绕流动管道的壳体结构以及布置在流动管道中的多个导向叶片和转子叶片。转子叶片可旋转地容纳在壳体结构中，而导叶固定在壳体结构中，多个导叶形成环形导叶环。壳体结构在径向内流道边界的区域中具有密封，以防止热气从流动管道逸出，该密封件通过密封支撑件设置在导向叶片环的导向叶片的导叶根部上，形成对可旋转密封表面的密封，密封支撑由金属间材料，特别是TiAl材料形成。

6. 发明申请

US20160003360A1 BRUSH SEAL 有权
公开(公告)号：US20160003360A1
公开(公告)日：2016-01-07
申请号：US14790663
申请日：2015-07-02
申请人： MTU Aero Engines AG
发明人： Stephan KLAEN , Julian WEBER , Frank STIEHLER , Christoph CERNAY , Thomas HESS
IPC分类号： F16J15/32 , F01D11/00
CPC分类号： F16J15/3288 , F01D11/00 , F01D11/001 , F05D2220/32 , F05D2240/56 , F05D2250/132 , F05D2250/22 , F05D2250/283 , F05D2250/294 , F16J15/322 , F16J15/3268
摘要： A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.
摘要翻译：公开了一种用于燃气轮机，特别是飞机发动机的刷密封件。刷密封件包括支撑环，支撑环具有支撑板和支撑结构，其中支撑结构相对于支撑板布置在下游。刷子密封件还包括布置在相对于支撑环的上游的刷毛，其中刷毛的端部径向向内突出超出支撑板。当在支撑结构的第一侧表面上施加径向向外作用的刮擦力时，支撑结构产生，其中第一侧表面径向向内指向，并且当在第二侧表面上产生轴向作用力时，支撑结构不会屈服的支撑结构。

7. 发明申请

US20150167479A1 BLADE CASCADE 有权
标题翻译：刀片卡
公开(公告)号：US20150167479A1
公开(公告)日：2015-06-18
申请号：US14570285
申请日：2014-12-15
申请人： MTU Aero Engines AG
发明人： Andreas HARTUNG , Frank STIEHLER , Martin PERNLEITNER
IPC分类号： F01D5/28 , F01D5/14
CPC分类号： F01D5/28 , F01D5/14 , F01D5/22 , F01D5/26 , F04D29/023 , F04D29/324 , F04D29/542 , F04D29/666 , F05D2260/961 , F05D2300/607 , Y02T50/671 , Y10T29/49321
摘要： The invention relates to a blade cascade for a turbomachine, having a number of blades (11, . . . 14; 21, . . . 25; 31, . . . 37) which include a monocrystalline material, each blade having a crystal orientation value (|α|), which is dependent on a crystal of first blades (11, . . . 14) being less than a first limiting value and the crystal orientation values of second blades (21, . . . 25; 31, . . . 37) being at least equal to the first limiting value; and the blade cascade having at least one first sector (1), which includes at least three successive first blades (14, 12, 11, 13), and having at least one second sector (2+3; 2′+3′; 2″+3″), which includes at least three successive second blades (22, 21, 23, 24, 25; 31, 34, 36, 37, 33, 32, 35; and/or at least one first blade has a first body arrangement having at least one first body mounted so it is movable on the first blade and at least one second blade has a second body arrangement, which differs therefrom, having at least one second body mounted so it is movable on the second blade.
摘要翻译：本发明涉及一种用于涡轮机的叶片级联，其具有多个包括单晶材料的叶片（11 ... 14; 21，... 25; 31，...），每个叶片具有晶体取向取决于第一叶片（11，...）的晶体的值（|α|）小于第一限制值和第二叶片（21，... 25; 31，...）的晶体取向值。 ... 37）至少等于第一极限值; 并且叶片级联具有至少一个第一扇区（1），其包括至少三个连续的第一叶片（14,12,11,13），并且具有至少一个第二扇区（2 + 3; 2'+ 3'; 2“+3”），其包括至少三个连续的第二叶片（22,21,23,24,25; 31,34,36,37,33,32,35）和/或至少一个第一叶片具有第一主体装置具有至少一个第一本体安装，使得其可在第一叶片上移动，并且至少一个第二叶片具有与之不同的第二主体装置，其具有至少一个安装在第二叶片上的第二主体。

8. 发明申请

US20140348639A1 TURBOMACHINE BLADE 有权
标题翻译：涡轮叶片
公开(公告)号：US20140348639A1
公开(公告)日：2014-11-27
申请号：US14283973
申请日：2014-05-21
申请人： MTU Aero Engines AG
发明人： Frank STIEHLER , Andreas Hartung
IPC分类号： F01D5/16 , F01D5/18 , F04D29/66
CPC分类号： F01D5/16 , F01D5/18 , F01D5/26 , F01D25/06 , F04D29/661 , Y02T50/671
摘要： A blade (1) for a turbomachine, including a turbine blade (1.1) which has a channel (1.5), an impact chamber (2) having a constricted cross section being situated in the channel for the purpose of accommodating a single impulse body (3) is provided.
摘要翻译：一种用于涡轮机的叶片（1），包括具有通道（1.5）的涡轮机叶片（1.1），具有收缩横截面的冲击室（2）位于所述通道中以用于容纳单个脉冲体（ 3）。

9. 发明申请

US20220372892A1 BEARING CHAMBER HOUSING FOR A TURBOMACHINE 有权
公开(公告)号：US20220372892A1
公开(公告)日：2022-11-24
申请号：US16273280
申请日：2019-02-12
申请人： MTU Aero Engines AG
发明人： Frank STIEHLER , Georg KEMPINGER , Juergen KRAUS , Steffen SCHLOTHAUER , Christian LIEBL , Alois EICHINGER , Thomas KOEBKE
IPC分类号： F01D25/16 , F01D25/18
摘要： A bearing chamber housing for supporting a shaft of a turbomachine is provided, the bearing chamber housing including an additively built-up housing wall which bounds an oil chamber of the bearing chamber housing radially outwardly relative to an axis of rotation of the shaft, the housing wall being built up with an oil duct which has an inlet opening toward the oil chamber for admission of oil from the oil chamber into the oil duct, and which has an outlet opening for discharging the oil from the oil duct, the outlet opening being located at a different axial position and at a different circumferential position than the inlet opening, considered relative to the axis of rotation of the shaft, and the oil duct having an extent with both an axial component and a circumferential component, at least over a portion thereof.

10. 发明申请

US20200088044A1 GAS TURBINE MOVING BLADE 审中-公开
公开(公告)号：US20200088044A1
公开(公告)日：2020-03-19
申请号：US16571380
申请日：2019-09-16
申请人： MTU Aero Engines AG
发明人： Frank STIEHLER , Lars SCHELLHORN
IPC分类号： F01D5/20 , F01D5/14
摘要： A moving blade for a turbine or compressor stage of a gas turbine is provided, including a vane (10) and a radially outer shroud (20), for at least one contour point (PK) of an outer contour of a profile cross section (P) of the vane at a radial outer gas channel boundary, the wall thickness of the shroud at at least one edge point (PR) of the shroud, whose connecting line (V), including the contour point with a normal (N), which is perpendicular to the outer contour of the profile cross section in the contour point, encloses an angle (σ), which is no more than 5°, is less than a wall thickness of the shroud at the contour point, the wall thickness of the shroud decreasing strictly monotonously along the connecting line.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式