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公开(公告)号：US20180112555A1
公开(公告)日：2018-04-26
申请号：US15793012
申请日：2017-10-25
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser
CPC classification number: F01D25/164 , F01D9/041 , F01D9/042 , F01D17/162 , F01D25/06 , F02C7/06 , F04D29/563 , F05D2230/60 , F05D2240/12 , F05D2240/50 , F05D2260/38 , F05D2260/96
Abstract: An annular guide vane assembly includes an inner ring and a plurality of guide vanes. A radially inner end of each of the guide vanes is inserted into a respective one of the bearing members, and the inner ring has (at its radially outer surface) a receiving channel extending in the circumferential direction for the bearing members. The annular guide vane assembly further includes at least one damping element disposed in the receiving channel between the bearing members and the inner ring. A method provides that a damping element is inserted into a receiving channel of an inner ring segment, and a plurality of bearing elements are strung together within the receiving channel of the inner ring segment. After that, the inner ring segment and at least one additional inner ring segment are connected together to form an inner ring.
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公开(公告)号：US20170074271A1
公开(公告)日：2017-03-16
申请号：US15245388
申请日：2016-08-24
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Roland Matzgeller
CPC classification number: F04D29/324 , F04D19/028 , F04D29/544 , F05B2220/303 , F05D2220/323 , F05D2250/70
Abstract: The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point σ and the aspect ratio ARax, which is defined by the quotient between average channel height (h) and average chord length (lax), satisfy the condition σ>−1.33×ARax+5.16.
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公开(公告)号：US20160146027A1
公开(公告)日：2016-05-26
申请号：US14942342
申请日：2015-11-16
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Hermann Klingels
Abstract: The invention is directed to a guide vane ring for a turbomachine, in which a vane bearing is produced in the inner ring via platform plates of the vanes and reliability against disintegration is produced via journals that extend radially inward from the platform plates, as well as a turbomachine.
Abstract translation: 本发明涉及一种用于涡轮机的导向叶片环，其中通过叶片的平台板在内圈中产生叶片轴承，并且通过从平台板径向向内延伸的轴颈产生可靠的抗分解性，以及 涡轮机。
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公开(公告)号：US20140044526A1
公开(公告)日：2014-02-13
申请号：US13957716
申请日：2013-08-02
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser
IPC: F01D11/00
CPC classification number: F01D11/003 , B33Y80/00 , F01D17/162 , F05D2230/60 , F05D2250/411 , Y02T50/671 , Y10T29/49336
Abstract: Disclosed is an adjustable stationary blade ring of a turbomachine, whose stationary blades are each supported in a bearing body onto which an inner ring, which is divided into two half rings and acts as a seal carrier, is pushed without deformation, viewed in the circumferential direction, as well as a method for assembling a stationary blade ring of this type and a turbomachine having a stationary blade ring of this type.
Abstract translation: 公开了一种涡轮机的可调节的固定叶片环，其固定叶片各自支撑在轴承体中，在圆周上观察分为两个半环并用作密封载体的内圈，而不会变形 方向，以及用于组装这种类型的固定叶片环的方法和具有这种类型的固定叶片环的涡轮机。
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公开(公告)号：US12123419B2
公开(公告)日：2024-10-22
申请号：US18345319
申请日：2023-06-30
Applicant: MTU Aero Engines AG
Inventor： Sergio Elorza Gomez , Werner Humhauser , Roland Matzgeller
Abstract: The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.
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Patent Agency Ranking
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：US10280934B2
公开(公告)日：2019-05-07
申请号：US15245388
申请日：2016-08-24
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Roland Matzgeller
Abstract: The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point σ and the aspect ratio ARax, which is defined by the quotient between average channel height (h) and average chord length (lax), satisfy the condition σ>−1.33·ARax+5.16.
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公开(公告)号：US20180274380A1
公开(公告)日：2018-09-27
申请号：US15933410
申请日：2018-03-23
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser
CPC classification number: F01D11/005 , F01D9/041 , F01D9/042 , F01D11/001 , F01D17/162 , F05D2220/32 , F05D2230/60 , F05D2240/12 , F05D2240/50 , F05D2240/55
Abstract: A guide vane assembly according to the invention comprises an inner ring, on whose radially outer surface an uptake channel runs in the peripheral direction; a plurality of bearing members, which are arranged in the uptake channel of the inner ring; a plurality of guide vanes, each of which is inserted by its radially inner end into one of the bearing members; and at least one sealing element for sealing at least one gap between the inner ring and at least one of the bearing members and/or between two bearing members. A turbomachine according to the invention comprises a guide vane assembly according to the invention. A method according to the invention serves for the installation of a guide vane assembly.
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公开(公告)号：US10041363B2
公开(公告)日：2018-08-07
申请号：US14546675
申请日：2014-11-18
Applicant: MTU Aero Engines AG
Inventor： Werner Humhauser , Herman Klingels , Alexander Kloetzer
CPC classification number: F01D5/3038 , F01D5/147 , F01D5/32 , F05D2230/60 , Y10T29/49321
Abstract: A blade-disk assembly of a turbomachine is provided, the blade-disk assembly having a plurality of adjacent rotor blades and a closure blade which are tilted into an anchoring groove, and at least one circumferential retention element which interlockingly cooperates with at least one blade, as well as a plurality of tilt-out prevention elements which are disposed between the groove base and the root portions and which, in the rest state, space the blades from the groove base when in the upper position. The blade-disk assembly further has a locking element, a portion of which is located between the groove base and the root portions and which, in the rest state, spaces the closure blade from the groove base when in the upper position. A method for assembling such a blade-disk assembly, as well as a turbomachine, is also provided.
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