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1. 发明授权

US10436054B2 Blade outer air seal for a gas turbine engine 有权
公开(公告)号：US10436054B2
公开(公告)日：2019-10-08
申请号：US15444971
申请日：2017-02-28
申请人： UNITED TECHNOLOGIES CORPORATION , MTU AERO ENGINES AG
发明人： Nicholas R. Leslie , Fadi S. Maalouf , Georg Zotz , Werner Humhauser
IPC分类号： F01D11/12
摘要： A blade outer air seal (BOAS) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

2. 发明授权

US10066668B2 Split inner ring 有权
公开(公告)号：US10066668B2
公开(公告)日：2018-09-04
申请号：US14278151
申请日：2014-05-15
申请人： MTU Aero Engines AG
发明人： Georg Zotz
IPC分类号： F16C33/04 , F01D9/04 , F01D17/16 , F16C43/02
摘要： The present invention provides a split inner ring for an adjustable guide blade arrangement, having a ring segment arrangement with at least two ring segments (1, 2) and a bearing bush arrangement with at least one bearing bush (5) for mounting an adjustable guide blade (4) of the guide blade arrangement, in which a ring segment and another ring segment of the ring segment arrangement can be joined together by the bearing bush arrangement.

3. 发明申请

US20140348449A1 SPLIT INNER RING 审中-公开
标题翻译：分体内圈
公开(公告)号：US20140348449A1
公开(公告)日：2014-11-27
申请号：US14278151
申请日：2014-05-15
申请人： MTU Aero Engines AG
发明人： Georg Zotz
IPC分类号： F16C33/04 , F16C43/02
CPC分类号： F16C33/046 , F01D9/042 , F01D17/162 , F16C43/02 , Y10T29/49668
摘要： The present invention provides a split inner ring for an adjustable guide blade arrangement, having a ring segment arrangement with at least two ring segments (1, 2) and a bearing bush arrangement with at least one bearing bush (5) for mounting an adjustable guide blade (4) of the guide blade arrangement, in which a ring segment and another ring segment of the ring segment arrangement can be joined together by the bearing bush arrangement.
摘要翻译：本发明提供了一种用于可调节导向叶片装置的分割内圈，具有至少两个环形段（1,2）的环形段布置，以及具有至少一个轴承衬套（5）的轴承衬套布置，用于安装可调导轨导向叶片装置的叶片（4），其中环形段装置的环形段和另一个环形段可以通过轴承衬套装置连接在一起。

4. 发明授权

US10151206B2 Turbomachine, circulation structure and method 有权
公开(公告)号：US10151206B2
公开(公告)日：2018-12-11
申请号：US14315066
申请日：2014-06-25
申请人： MTU Aero Engines AG
发明人： Georg Zotz , Giovanni Brignole , Harsimar Sahota , Vitalis Mairhanser
IPC分类号： F04D29/68 , F01D9/02 , F04D29/52 , F04D29/64 , F04D29/56 , F04D27/02
摘要： A turbomachine having at least one circulation structure is disclosed. The circulation structure has an annular space with baffle elements surrounding a main flow path and is open to the main flow path. A housing of the turbomachine to receive the circulation structure is divided in an axial plane into a front housing region and a rear housing region and the circulation structure is divided into a front structure region and a rear structure region in the axial plane of separation. A circulation structure divided into two parts in the axial direction and a method for the same is also disclosed.

5. 发明申请

US20170175756A1 GUIDE VANE FOR A TURBOMACHINE, GUIDE VANE CASCADE, AND METHOD FOR MANUFACTURING A GUIDE VANE OR A GUIDE VANE CASCADE 审中-公开
公开(公告)号：US20170175756A1
公开(公告)日：2017-06-22
申请号：US15446241
申请日：2017-03-01
申请人： MTU Aero Engines AG
发明人： Georg Zotz
IPC分类号： F04D29/16 , F04D29/56 , F04D29/54 , B22F5/04 , B33Y10/00 , B33Y80/00 , B22F3/105 , F04D19/00 , B23K26/342
CPC分类号： F04D29/164 , B22F3/1055 , B22F5/04 , B22F2998/10 , B23K26/342 , B23K2101/001 , B23P15/04 , B33Y10/00 , B33Y80/00 , F01D5/18 , F01D5/20 , F01D11/00 , F01D11/08 , F01D11/10 , F01D17/14 , F01D17/16 , F01D17/162 , F04D19/00 , F04D29/544 , F04D29/56 , Y02T50/673 , Y02T50/676 , Y10T29/49336
摘要： A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade.

6. 发明申请

US20170159470A1 INNER RING SYSTEM FOR AN INLET GUIDE VANE CASCADE OF A TURBOMACHINE 审中-公开
公开(公告)号：US20170159470A1
公开(公告)日：2017-06-08
申请号：US15363914
申请日：2016-11-29
申请人： MTU Aero Engines AG
发明人： Lothar Albers , Georg Zotz , Vitalis Mairhanser , Werner Humhauser
IPC分类号： F01D11/00 , F01D9/04
摘要： The invention relates to an inner ring system for an inlet guide vane cascade (14) of a turbomachine (10). The inner ring system comprises an intermediate casing (28) for accommodating structural loads and an inner ring (26), which is divided axially into a first ring segment (24a) and a second ring segment (24b), which together form recesses (22) for bearing radially inner end portions (18) of guide vanes (16) of the inlet guide vane cascade (14), wherein at least the second ring segment (24b) is fixed in place on the intermediate casing (28) by screw connection). The invention further relates to an inner ring (26) and to an intermediate casing (28) for such an inner ring system, as well as a turbomachine (10) that has such an inner ring system.

7. 发明申请

US20170159467A1 GUIDE VANE RING CASING FOR A TURBOMACHINE AND TURBOMACHINE HAVING A GUIDE VANE RING CASING 审中-公开
公开(公告)号：US20170159467A1
公开(公告)日：2017-06-08
申请号：US15367930
申请日：2016-12-02
申请人： MTU Aero Engines AG
发明人： Lothar Albers , Georg Zotz , Vitalis Mairhanser
IPC分类号： F01D9/04 , F01D17/16
CPC分类号： F01D9/042 , F01D9/041 , F01D17/162 , F05D2240/128
摘要： An inventive guide vane ring casing 10′ for a turbomachine has a casing surface 11 extending about and facing a central axis A, the casing surface having formed therein a plurality of receiving recesses 12′, each intended to receive a vane disk 21a of a guide vane 20. A radial cut-out 16 is formed between at least two adjacent receiving recesses 12′ in the casing surface 11 and connects the two receiving recesses. A turbomachine includes a plurality of guide vanes 20 as well as an inventive guide vane ring casing 10′, each of the receiving recesses 12′ in the guide vane ring casing having a guide vane disk 21a of a respective one of the guide vanes placed therein.

8. 发明授权

US09587499B2 Inner ring of a fluid flow machine and stator vane array 有权
标题翻译：流体流动机和定子叶片阵列的内圈
公开(公告)号：US09587499B2
公开(公告)日：2017-03-07
申请号：US14537848
申请日：2014-11-10
申请人： MTU Aero Engines AG
发明人： Lothar Albers , Georg Zotz , Rudolf Pilzweger , Hermann Becker
IPC分类号： F01D9/04 , F01D5/22 , F01D11/00
CPC分类号： F01D9/042 , F01D5/225 , F01D9/04 , F01D11/001 , F01D11/005 , F05D2240/11
摘要： An inner ring of a fluid flow machine includes fixing rings and seal carriers split into at least two fixing ring segments and into at least two seal carrier segments, respectively. The fixing ring segments and the seal carrier segments are arranged with the respective end faces facing each other. A first fixing ring segment has a first ring segment shoulder and a second fixing ring segment has an offset second ring segment shoulder. A first seal carrier segment has a first carrier segment shoulder, and a second seal carrier segment has a second carrier segment shoulder, which is offset with respect to the first carrier segment shoulder. In a separation plane of the inner ring, the first carrier segment shoulder abuts the second ring segment shoulder at the end face. Also in the separation plane, the second carrier segment shoulder abuts the first ring segment shoulder at the end face.
摘要翻译：流体流动机械的内圈包括分别分成至少两个固定环段并分成至少两个密封载体段的固定环和密封载体。固定环段和密封载体段布置成相应的端面彼此面对。第一固定环段具有第一环形段肩部，而第二固定环段具有偏移的第二环形段肩部。第一密封载体段具有第一载体段肩部，第二密封载体段具有相对于第一载体段肩部偏移的第二载体区段肩部。在内圈的分离平面中，第一行星架台阶在端面处邻接第二环形台肩。同样在分离平面中，第二载体段肩部在端面处邻接第一环形段肩部。

9. 发明授权

US10060439B2 Guide vane for a turbomachine, guide vane cascade, and method for manufacturing a guide vane or a guide vane cascade 有权
公开(公告)号：US10060439B2
公开(公告)日：2018-08-28
申请号：US15446241
申请日：2017-03-01
申请人： MTU Aero Engines AG
发明人： Georg Zotz
IPC分类号： F01D11/00 , F01D11/08 , F01D5/18 , F01D5/20 , F04D29/16 , F04D19/00 , F04D29/56 , F04D29/54 , B23K26/342 , B33Y10/00 , B33Y80/00 , B22F3/105 , B22F5/04 , B23K101/00
CPC分类号： F04D29/164 , B22F3/1055 , B22F5/04 , B22F2998/10 , B23K26/342 , B23K2101/001 , B23P15/04 , B33Y10/00 , B33Y80/00 , F01D5/18 , F01D5/20 , F01D11/00 , F01D11/08 , F01D11/10 , F01D17/14 , F01D17/16 , F01D17/162 , F04D19/00 , F04D29/544 , F04D29/56 , Y02T50/673 , Y02T50/676 , Y10T29/49336
摘要： A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade.

10. 发明申请

US20170306784A1 BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170306784A1
公开(公告)日：2017-10-26
申请号：US15444971
申请日：2017-02-28
申请人： UNITED TECHNOLOGIES CORPORATION , MTU AERO ENGINES AG
发明人： Nicholas R. Leslie , Fadi S. Maalouf , Georg Zotz , Werner Humhauser
IPC分类号： F01D11/12
CPC分类号： F01D11/122 , F01D11/125 , F01D11/127 , F05D2230/312 , Y02T50/6765
摘要： A blade outer air seal (BOAS) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

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