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公开(公告)号：US10364827B2
公开(公告)日：2019-07-30
申请号：US14672333
申请日：2015-03-30
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Hermann Klingels
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.
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公开(公告)号：US10352178B2
公开(公告)日：2019-07-16
申请号：US15043643
申请日：2016-02-15
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Hermann Klingels
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.
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公开(公告)号：US09771896B2
公开(公告)日：2017-09-26
申请号：US14244050
申请日：2014-04-03
Applicant: MTU Aero Engines AG
Inventor： Hermann Klingels , Stephan Klaen , Christian Scherer , Uwe Vogel
Abstract: The invention relates to a mixing device and a turbofan engine having such a mixing device 30 for mixing a first gas flow 40 with a second gas flow 50 in a turbofan engine 20, having an actuating device 95 and walls 60, which bound a channel 65 for the first gas flow 40 and a channel 70 lying radially outside for the second gas flow 50, the actuating device 95 comprising a coupling element 110 that is coupled to the walls (60), the actuating device 95 being designed to pivot the walls 60 between a first position and a second position disposed radially outside relative to the first position, the actuating device 95 comprising an adjusting ring 105 that can be rotated between a first rotating position and a second rotating position in the peripheral direction and that is joined to the coupling element 110.
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公开(公告)号：US09664141B2
公开(公告)日：2017-05-30
申请号：US14299727
申请日：2014-06-09
Applicant: MTU Aero Engines AG
Inventor： Hermann Klingels , Stephan Klaen , Christian Scherer , Uwe Vogel
CPC classification number: F02K1/008 , B64D33/04 , F02K1/006 , F02K1/1207 , F02K1/80 , F05D2250/42 , F05D2260/50 , F05D2260/56 , F05D2260/57
Abstract: A thrust deflecting device for deflecting a thrust stream is disclosed, which includes a flap system having a plurality of deflecting flaps, each of which is pivotable around its yaw axis, the flap system being situated between parallel control surfaces such as baffle plates which, together with the flap system, form a box structure, which is pivotable around a pivot axis running in the direction of the transverse axis for the purpose of deflecting the thrust stream in the pitch direction, an aircraft engine also being disclosed.
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公开(公告)号：US20150226155A1
公开(公告)日：2015-08-13
申请号：US14299727
申请日：2014-06-09
Applicant: MTU Aero Engines AG
Inventor： Hermann Klingels , Stephan Klaen , Christian Scherer , Uwe Vogel
CPC classification number: F02K1/008 , B64D33/04 , F02K1/006 , F02K1/1207 , F02K1/80 , F05D2250/42 , F05D2260/50 , F05D2260/56 , F05D2260/57
Abstract: A thrust deflecting device for deflecting a thrust stream is disclosed, which includes a flap system having a plurality of deflecting flaps, each of which is pivotable around its yaw axis, the flap system being situated between parallel control surfaces such as baffle plates which, together with the flap system, form a box structure, which is pivotable around a pivot axis running in the direction of the transverse axis for the purpose of deflecting the thrust stream in the pitch direction, an aircraft engine also being disclosed.
Abstract translation: 公开了一种用于偏转推力流的推力偏转装置，其包括具有多个偏转翼片的翼片系统，每个翼片可绕其偏转轴线枢转，所述翼片系统位于平行控制表面之间，例如挡板 与翼片系统形成盒结构，其可围绕在横向轴线方向上运行的枢转轴线枢转，用于偏转俯仰方向上的推力流，还公开了一种飞机发动机。
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Patent Agency Ranking
公开(公告)号：US20240209797A1
公开(公告)日：2024-06-27
申请号：US18545289
申请日：2023-12-19
Applicant: MTU Aero Engines AG
Inventor： Sascha Kaiser , Hermann Klingels , Paul Ziegler
Abstract: The invention is a method for operating a turbomachine for a flight propulsion drive having a compressor through which a gas stream flows in a flow direction, a combustion chamber, a turbine, and a heat exchange device situated downstream of the turbine, wherein the heat exchange device extracts water from the gas stream and the water is supplied in the combustion chamber for the combustion of fuel.
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公开(公告)号：US20230332522A1
公开(公告)日：2023-10-19
申请号：US18040460
申请日：2021-08-02
Applicant: MTU Aero Engines AG
Inventor： Hermann Klingels
CPC classification number: F01N3/0205 , F02C7/141 , F02C7/16 , F05D2220/323 , F05D2260/213
Abstract: The present invention relates to an exhaust-gas treatment device for an aircraft engine, comprising an exhaust-gas channel, through which an exhaust gas of the aircraft engine flows, and a first cooling unit for cooling with ambient air, characterized by a second cooling unit, which is downstream of the first cooling unit with respect to an exhaust-gas flow in the exhaust-gas channel.
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公开(公告)号：US20230286661A1
公开(公告)日：2023-09-14
申请号：US18040444
申请日：2021-08-02
Applicant: MTU Aero Engines AG
Inventor： Hermann Klingels
CPC classification number: B64D27/18 , B64D27/26 , B64D33/10 , B64D29/06 , F02C7/141 , F02C3/305 , F05D2220/323 , F05D2260/213 , F05D2270/08
Abstract: The present invention relates to an aircraft comprising at least one wing, at least one flight propulsion drive, and a retainer, particularly an engine pylon, which interconnects the wing and the flight propulsion drive. The aircraft comprises at least one heat exchanger for cooling exhaust gas of the fight propulsion drive and/or at least one water removal channel having at least one removal apparatus for removing water from exhaust gas of the flight propulsion drive, especially after the exhaust gas has flowed through the heat exchanger. The removal apparatus is disposed on, more particularly in, the retainer or is connected to the wing by means of the retainer, and/or the flight propulsion drive is fastened to the retainer by means of at least one flight propulsion drive suspension means, and the heat exchanger is fastened, independently thereof, to the retainer by means of at least one heat exchanger suspension means.
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公开(公告)号：US11215073B2
公开(公告)日：2022-01-04
申请号：US16382471
申请日：2019-04-12
Applicant: MTU Aero Engines AG
Inventor： Hermann Klingels
Abstract: A stator vane (3) for a turbine (50c) of a turbomachine (50), the stator vane having a stator vane airfoil (3c), an inner shroud (3a) and an outer shroud (3b), the inner shroud (3a) and the outer shroud (3b) bounding an annular space (2), in which working gas (51) is conveyed during operation, radially with respect to a longitudinal axis (52) of the turbomachine (50), and the stator vane airfoil (3c) having a stator vane airfoil channel (3d) extending through its interior between a radially inner inlet (6) and a radially outer outlet (7). A characteristic features is that the inlet (6) is disposed in such a manner that a gas (8) flowing through the stator vane airfoil channel (3d) during operation is at least partially formed of the working gas (51) conveyed in the annular space (2), and thus the working gas is redistributed from radially inward to radially outward.
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公开(公告)号：US10393160B2
公开(公告)日：2019-08-27
申请号：US15919781
申请日：2018-03-13
Applicant: MTU Aero Engines AG
Inventor： Hermann Klingels , Wolfgang Bickmeier
Abstract: Disclosed is a component with a component section and a flange that is arranged at the component section for connection of the component another element. Arranged at the flange is one or a plurality of oblique flange channels, that is, channels for respectively accommodating a section of a connection element that runs obliquely to a surface portion of the component section that lies opposite to the flange. Further disclosed is a flange connection with at least one component of this kind, another component, and at least one connection element. Disclosed, in addition, is a turbomachine with a housing that is assembled from two or more components by means of such a flange connection.
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