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公开(公告)号：US20230043732A1
公开(公告)日：2023-02-09
申请号：US17817177
申请日：2022-08-03
Applicant: MTU Aero Engines AG
Inventor： Axel Stettner , Christian Roth , Werner Humhauser
Abstract: The invention relates to a connecting device for an adjustable blade or vane of a gas turbine, comprising a journal element connected to a respective blade or vane and a lever element connected to the journal element, wherein the lever element and the journal element are jointly movable about a journal axis of rotation. A clamping element is provided, being situated between the lever element and the journal element, such that a force-locking connection is or can be produced between the journal element, the clamping element, and the lever element. The lever element, the clamping element, and the journal element are aligned relative to each other by means of a positioning element, the positioning element being received in a first seat of the journal element and a corresponding second seat of the lever element.
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公开(公告)号：US10982558B2
公开(公告)日：2021-04-20
申请号：US16211483
申请日：2018-12-06
Applicant: MTU Aero Engines AG
Inventor： Vitalis Mairhanser , Stephen Royston Williams , Werner Humhauser
Abstract: Disclosed is a lever linkage for the rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine, wherein the guide vane has a vane shaft, which extends along a vertical axis. In accordance with the invention, the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve, which coaxially surrounds the vane shaft in sections, and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection, and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by means of a fastening element, in particular a threaded nut. In consequence thereof, a separation of two different force flows that act on the guide vanes is obtained, as a result of which local load peaks are reduced.
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公开(公告)号：US20190178096A1
公开(公告)日：2019-06-13
申请号：US16211483
申请日：2018-12-06
Applicant: MTU Aero Engines AG
Inventor： Vitalis Mairhanser , Stephen Royston Williams , Werner Humhauser
Abstract: Disclosed is a lever linkage for the rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine, wherein the guide vane has a vane shaft, which extends along a vertical axis. In accordance with the invention, the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve, which coaxially surrounds the vane shaft in sections, and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection, and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by means of a fastening element, in particular a threaded nut. In consequence thereof, a separation of two different force flows that act on the guide vanes is obtained, as a result of which local load peaks are reduced.
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公开(公告)号：US20170159470A1
公开(公告)日：2017-06-08
申请号：US15363914
申请日：2016-11-29
Applicant: MTU Aero Engines AG
Inventor： Lothar Albers , Georg Zotz , Vitalis Mairhanser , Werner Humhauser
Abstract: 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.
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公开(公告)号：US20160245101A1
公开(公告)日：2016-08-25
申请号：US15043643
申请日：2016-02-15
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Hermann Klingels
CPC classification number: F01D5/326 , F01D5/3007 , F01D5/3038 , F01D5/32 , F04D29/322 , F05D2220/323 , F05D2260/30
Abstract: A locking element for a row of blades of a turbomachine includes a number of blades that are inserted by their roots in an anchoring groove on the rotor side and are thereby held in the radial direction in form-fitting manner in the anchoring groove. The locking element has a basic body that has a front bearing surface and a back bearing surface for form-fitting with opposite-lying groove surfaces, a front lock projection and a back lock projection for engaging in opposite-lying recesses of the anchoring groove, and a threaded region for interacting with a tightening element. Access to the threaded region for the tightening element is blocked on one side.
Abstract translation: 用于一列涡轮机叶片的锁定元件包括多个叶片，它们的根部被插入到转子侧的锚定槽中，从而沿径向保持在锚定槽中。 锁定元件具有基体，该基体具有用于与相对的凹槽表面成形的前支承表面和后支承表面，前锁定突起和用于接合在锚定槽的相对的凹部中的后锁定突起， 以及用于与紧固元件相互作用的螺纹区域。 进入紧固元件的螺纹区域在一侧被阻挡。
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Patent Agency Ranking
公开(公告)号：US20160017797A1
公开(公告)日：2016-01-21
申请号：US14335107
申请日：2014-07-18
Applicant: MTU Aero Engines AG
Inventor： Klaus Peter RUED , Werner Humhauser , Hermann Klingels , Rudolf Stanka , Eckart Heinrich , Hans-Peter Hackenberg , Stefan Weber , Claus Rieger , Erich Steinhardt , Jochen Gier , Manfred Feldmann , Norbert Huebner , Karl Maar
Abstract: A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W1) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W2) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (DF) of the fan to a maximum blade diameter (DL) of the second turbine is at least 3.5, in particular at least 4.
Abstract translation: 具有主要管道（C）的涡轮风扇飞机发动机，包括燃烧室（BK），设置在燃烧室下游的第一涡轮机（HT），设置在燃烧室上游并连接（W1）至 第一涡轮机和设置在第一涡轮机下游的第二涡轮机（L），并且经由减速机构（G）经由减速机构（G）连接到用于供给涡轮风扇发动机的辅助管道（B）的风扇（F）。 风扇的最大叶片直径（DF）与第二涡轮机的最大叶片直径（DL）的比率的平方至少为3.5，特别是至少4。
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公开(公告)号：US20150275683A1
公开(公告)日：2015-10-01
申请号：US14672333
申请日：2015-03-30
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Hermann Klingels
CPC classification number: F04D29/563 , F01D1/02 , F01D7/00 , F01D9/041 , F01D17/162 , F01D25/16 , F04D29/083 , F04D29/321 , F05D2220/30 , F05D2220/32 , F05D2230/90 , F05D2240/12 , F05D2240/56 , Y02T50/671
Abstract: An adjustable guide vane ring of a turbomachine having an inner ring, the guide vanes of which each have a radially inner vane disk with disk thickness increasing in the direction of flow and acting as a bearing pin; a guide vane, as well as an inner ring for such a guide vane ring, as well as a turbomachine are disclosed.
Abstract translation: 具有内环的涡轮机的可调导叶环，其导叶各自具有径向内叶片盘，盘片厚度在流动方向上增加并用作轴承销; 引导叶片以及用于这种导叶环的内圈以及涡轮机。
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公开(公告)号：US10436054B2
公开(公告)日：2019-10-08
申请号：US15444971
申请日：2017-02-28
Applicant: UNITED TECHNOLOGIES CORPORATION , MTU AERO ENGINES AG
Inventor： Nicholas R. Leslie , Fadi S. Maalouf , Georg Zotz , Werner Humhauser
IPC: F01D11/12
Abstract: 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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公开(公告)号：US20190249562A1
公开(公告)日：2019-08-15
申请号：US16271842
申请日：2019-02-10
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser
CPC classification number: F01D17/162 , F01D9/041 , F01D9/042 , F04D29/563 , F05D2230/60 , F05D2250/294 , F05D2260/36 , F05D2260/50 , F05D2260/79
Abstract: Disclosed is a lever connection for a guide vane adjustment for connecting a guide vane of a turbomachine to an adjusting ring of an actuator, which is arranged in such a way that an adjusting lever of the lever connection is pushed radially from a first mounting direction, in relation to a machine longitudinal axis of the turbomachine, onto a vane shaft of the guide vane, and is locked with the vane shaft in a form-fitting and, in particular, rotationally rigid manner by means of a movement in a second mounting direction; a mounting method; and a turbomachine.
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公开(公告)号：US10001083B2
公开(公告)日：2018-06-19
申请号：US14335107
申请日：2014-07-18
Applicant: MTU Aero Engines AG
Inventor： Klaus Peter Rued , Werner Humhauser , Hermann Klingels , Rudolf Stanka , Eckart Heinrich , Hans-Peter Hackenberg , Stefan Weber , Claus Riegler , Erich Steinhardt , Jochen Gier , Manfred Feldmann , Norbert Huebner , Karl Maar
Abstract: A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W1) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W2) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (DF) of the fan to a maximum blade diameter (DL) of the second turbine is at least 3.5, in particular at least 4.
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