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1. 发明申请

US20170159464A1 RUN-UP SURFACE FOR THE GUIDE-VANE SHROUD PLATE AND THE ROTOR-BLADE BASE PLATE 审中-公开
公开(公告)号：US20170159464A1
公开(公告)日：2017-06-08
申请号：US15366260
申请日：2016-12-01
申请人： MTU Aero Engines AG
发明人： Markus Schlemmer , Martin Pernleitner , Manfred Dopfer , Marcus Woehler , Oliver Thiele , Bernd Kislinger , Norman Cleesattel , Christoph Lauer , Manfred Schill , Manuel Hein
IPC分类号： F01D9/04 , F01D21/06 , F01D5/12
CPC分类号： F01D9/041 , F01D5/12 , F01D11/001 , F01D21/04 , F01D21/045 , F01D21/06 , F05D2220/32 , F05D2240/12 , F05D2240/24 , F05D2250/232 , F05D2260/90 , F05D2260/902
摘要： A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.

2. 发明申请

US20170067487A1 TURBOMACHINE BLADE 审中-公开
标题翻译：涡轮叶片
公开(公告)号：US20170067487A1
公开(公告)日：2017-03-09
申请号：US15257434
申请日：2016-09-06
申请人： MTU Aero Engines AG
发明人： Andreas Hartung , Karl-Hermann Richter , Herbert Hanrieder , Manfred Schill
IPC分类号： F04D29/66 , F01D5/16 , F04D29/54 , F01D25/06 , F04D29/32 , F01D5/26 , F01D9/04
CPC分类号： F04D29/668 , F01D5/16 , F01D5/26 , F01D9/041 , F01D25/06 , F04D29/324 , F04D29/542 , Y02T50/671
摘要： A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber (10) in which at least one impulse element (11) is disposed with play, at least one second impact chamber (20) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber (10) along a first matrix axis (A) and in which at least one impulse element (21) is disposed with play, and at least one third impact chamber (30) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber (10) along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element (31) is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.
摘要翻译：用于涡轮机的叶片，特别是燃气轮机的压缩机或涡轮级，具有至少一个矩阵，其具有第一冲击室（10），其中至少一个冲击元件（11）在其中放置，至少一个第二冲击室（20），其体积重心沿着第一矩阵轴线（A）从第一冲击室（10）的体积重心偏移，并且其中至少一个冲击元件（21）与游戏一起设置;以及至少一个第三冲击室（30），其体积重心沿横向于第一矩阵轴线（A）的第二矩阵轴线（B）偏离第一冲击室（10）的体积重心，并且其中至少一个冲击元件（31））设置为游隙，提供形成至少60°且不超过120°的角度的涡轮机的第一矩阵轴线（A）和旋转轴线（R）。

3. 发明申请

US20140301853A1 SECURING BLADE ASSORTMENT 有权
标题翻译：保护叶片分类
公开(公告)号：US20140301853A1
公开(公告)日：2014-10-09
申请号：US14248067
申请日：2014-04-08
申请人： MTU Aero Engines AG
发明人： Martin PERNLEITNER , Rudolf Stanka , Manfred Schill
IPC分类号： F01D5/32
CPC分类号： F01D5/32 , F01D5/323 , F05D2230/60
摘要： A securing plate assortment including multiple different securing plates, the securing plates having different geometric codings. A turbine and method is also disclosed.
摘要翻译：固定板分类包括多个不同的固定板，固定板具有不同的几何编码。还公开了一种涡轮机和方法。

4. 发明授权

US10689983B2 Pulse body module with bearing protection 有权
公开(公告)号：US10689983B2
公开(公告)日：2020-06-23
申请号：US15793654
申请日：2017-10-25
申请人： MTU Aero Engines AG
发明人： Markus Schlemmer , Andreas Hartung , Gerhard-Heinz Roesele , Martin Pernleitner , Manfred Schill , Manfred Feldmann , Adrian Ehrenberg
IPC分类号： F01D5/16 , F01D5/10 , F01D5/26 , F01D25/06 , F16F15/10
摘要： An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.

5. 发明授权

US10526896B2 Turbomachine blade assembly 有权
公开(公告)号：US10526896B2
公开(公告)日：2020-01-07
申请号：US15488544
申请日：2017-04-17
申请人： MTU Aero Engines AG
发明人： Andreas Hartung , Manfred Schill
IPC分类号： F01D5/16 , F01D9/02 , F04D29/32 , F04D29/54 , F04D29/66
摘要： The present invention relates to a turbomachine blade or vane arrangement having a first turbomachine blade or vane, a second turbomachine blade or vane adjacent to it, and at least one tuning element guide housing with at least one cavity, in which at least one tuning element is arranged with play of movement for impact contact with the tuning element guide housing, with the tuning element guide housing being arranged at least in part in a recess, in particular in a frame, of the first turbomachine blade or vane, where the second turbomachine blade or vane has at least one first rib for securing the tuning element guide housing arranged in the recess.

6. 发明授权

US09951631B2 Turbomachine rotor blade 有权
公开(公告)号：US09951631B2
公开(公告)日：2018-04-24
申请号：US14316035
申请日：2014-06-26
申请人： MTU Aero Engines AG
发明人： Krzysztof Skura , Marcin Kozdras , Lukasz Sosnowka , Manfred Feldmann , Manfred Schill
IPC分类号： F04D29/08 , F01D5/30
CPC分类号： F01D5/3007 , F05D2250/292 , F05D2250/38 , F05D2250/712
摘要： A rotor blade for a turbomachine, including an airfoil (1) for flow deflection, a blade root (2) for attachment to a rotor of the turbomachine, an inner platform (3) between the airfoil and the blade root, and at least one pocket (4, 5) defined by two axially spaced walls (4.1, 4.2; 5.1, 5.2) extending from the side of the platform opposite the airfoil toward the blade root. A first (4.1, 5.1) of these walls has an outer side (4.1A, 5.1A) that faces away from the pocket and, in at least one cross section perpendicular to a radial longitudinal axis of the rotor blade, slopes outwardly.

7. 发明授权

US10451089B2 Turbomachine blade 有权
公开(公告)号：US10451089B2
公开(公告)日：2019-10-22
申请号：US15257434
申请日：2016-09-06
申请人： MTU Aero Engines AG
发明人： Andreas Hartung , Karl-Hermann Richter , Herbert Hanrieder , Manfred Schill
IPC分类号： F01D9/04 , F04D29/32 , F04D29/66 , F01D5/16 , F01D25/06 , F01D5/26 , F04D29/54
摘要： A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber (10) in which at least one impulse element (11) is disposed with play, at least one second impact chamber (20) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber (10) along a first matrix axis (A) and in which at least one impulse element (21) is disposed with play, and at least one third impact chamber (30) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber (10) along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element (31) is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.

8. 发明申请

US20180119552A1 PULSE BODY MODULE WITH BEARING PROTECTION 审中-公开
公开(公告)号：US20180119552A1
公开(公告)日：2018-05-03
申请号：US15793654
申请日：2017-10-25
申请人： MTU Aero Engines AG
发明人： Markus Schlemmer , Andreas Hartung , Gerhard-Heinz Roesele , Martin Pernleitner , Manfred Schill , Manfred Feldmann , Adrian Ehrenberg
IPC分类号： F01D5/16 , F01D5/26
摘要： An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.

9. 发明申请

US20170314397A1 TURBOMACHINE BLADE ASSEMBLY 审中-公开
公开(公告)号：US20170314397A1
公开(公告)日：2017-11-02
申请号：US15488544
申请日：2017-04-17
申请人： MTU Aero Engines AG
发明人： Andreas Hartung , Manfred Schill
IPC分类号： F01D5/16 , F04D29/32 , F04D29/66 , F01D9/02 , F04D29/54 , F01D25/04
CPC分类号： F01D5/16 , F01D9/02 , F04D29/322 , F04D29/324 , F04D29/542 , F04D29/668 , F05D2220/323 , F05D2250/232 , F05D2260/96 , Y02T50/671
摘要： The present invention relates to a turbomachine blade or vane arrangement having a first turbomachine blade or vane (10), a second turbomachine blade or vane (20) adjacent to it, and at least one tuning element guide housing (30) with at least one cavity, in which at least one tuning element (5) is arranged with play of movement for impact contact with the tuning element guide housing, with the tuning element guide housing being arranged at least in part in a recess (11), in particular in a frame (12), of the first turbomachine blade or vane (10), where the second turbomachine blade or vane (20) has at least one first rib (21) for securing the tuning element guide housing (30) arranged in the recess (11).

10. 发明授权

US09695699B2 Securing blade assortment 有权
公开(公告)号：US09695699B2
公开(公告)日：2017-07-04
申请号：US14248067
申请日：2014-04-08
申请人： MTU Aero Engines AG
发明人： Martin Pernleitner , Rudolf Stanka , Manfred Schill
IPC分类号： B64C11/04 , F01D5/32
CPC分类号： F01D5/32 , F01D5/323 , F05D2230/60
摘要： A securing plate assortment including multiple different securing plates, the securing plates having different geometric codings. A turbine and method is also disclosed.

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