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1. 发明授权

US09657576B2 Airfoil having a profiled trailing edge for a fluid flow machine, blade, and integrally blade rotor 有权
公开(公告)号：US09657576B2
公开(公告)日：2017-05-23
申请号：US14248037
申请日：2014-04-08
申请人： MTU Aero Engines AG
发明人： Guenter Ramm , Christine Lang
IPC分类号： F01D5/04 , F01D5/14 , F04D29/32 , F04D29/68
CPC分类号： F01D5/145 , F01D5/142 , F04D29/324 , F04D29/681 , F05D2240/122 , F05D2240/304 , F05D2250/18 , F05D2260/96
摘要： The present invention relates to an airfoil for a fluid flow machine (100), having a suction side (5), a pressure side (7) and an airfoil trailing edge (200). The airfoil (100), at least in portions thereof, has a profile (9) in the region of the airfoil trailing edge (200), which profile extends over the suction side (5) and the pressure side (7) of the airfoil trailing edge (200). The present invention also relates to a blade and an integrally bladed rotor.

2. 发明授权

US10746131B2 Turbine module for a turbomachine 有权
公开(公告)号：US10746131B2
公开(公告)日：2020-08-18
申请号：US16219323
申请日：2018-12-13
申请人： MTU Aero Engines AG
发明人： Guenter Ramm , Martin Hoeger , Irene Raab , Yavuz Guendogdu
IPC分类号： F01D5/14 , F02K3/06 , F01D9/04 , F01D9/06 , F01D25/24
摘要： The present invention relates to a turbine module for a turbomachine, comprising a first flow bypass structure and a second flow bypass structure, said flow bypass structures being arranged in a hot gas duct, which is bounded by the turbine module and is designed to convey a hot gas and, namely, being arranged in succession in relation to a longitudinal axis of the turbine module in a direction of rotation, wherein, in relation to the bypass flow in the hot gas duct, the flow bypass structures each have a leading edge, and, downstream thereto, a trailing edge, and the second flow bypass structure is provided as a deflecting blade, wherein the second flow bypass structure has a smaller profile thickness than the first flow bypass structure, and wherein the hot gas duct is enclosed by a radial width.

3. 发明申请

US20150098809A1 TURBOMACHINE 有权
标题翻译：涡轮机
公开(公告)号：US20150098809A1
公开(公告)日：2015-04-09
申请号：US14508709
申请日：2014-10-07
申请人： MTU Aero Engines AG
发明人： Guenter Ramm
IPC分类号： F01D11/12
CPC分类号： F01D11/12 , F01D11/02 , F01D11/08 , Y02T50/671
摘要： A turbomachine is described, which includes an annular space seal for at least reducing a fluid exchange between an annular space, through which a main stream flows, and at least one cavity situated radially on the inside and/or radially on the outside of the annular space, the annular space seal having a plurality of sheet-like elastic elements, which are oriented in the radial direction of the turbomachine and in the flow direction of a main stream flowing through the particular guide blade row, and thereby acting as a protective device for the rotor and/or stator during a relative axial displacement with respect to the stator in addition to providing an improved cavity coverage.
摘要翻译：描述了一种涡轮机，其包括环形空间密封件，用于至少减少主流流过的环形空间与径向位于环形空间内部和/或径向上位于环形空间之间的流体交换空间，环形空间密封件具有多个片状弹性元件，其沿涡轮机的径向定向并且沿着主流的流动方向流过特定的导向叶片排，从而用作保护装置对于转子和/或定子，除了提供改进的空腔覆盖之外，相对于定子的相对轴向位移。

4. 发明授权

US11098599B2 Flow channel for a turbomachine 有权
公开(公告)号：US11098599B2
公开(公告)日：2021-08-24
申请号：US16205403
申请日：2018-11-30
申请人： MTU Aero Engines AG
发明人： Guenter Ramm
IPC分类号： F01D9/02 , F01D25/16 , F01D9/06 , F01D9/04
摘要： A flow channel for a turbomachine, in particular a gas turbine, having a plurality of ribs that are disposed between a radially inner lateral surface and a radially outer lateral surface of the flow channel and are circumferentially distributed; a first rib of the ribs having a first rib thickness and a first rib length, and a second rib of the ribs having a second rib thickness and a second rib length, the second rib length being shorter than the first rib length, and/or the second rib thickness being smaller than the first rib thickness; a spacing in the circumferential direction between the first rib and the second rib adjacent thereto, and a spacing in the circumferential direction between at least two adjacent ribs of the ribs mutually deviating, and at least one of these ribs having a non-deflecting external profile and or an internal structure being disposed therein.

5. 发明申请

US20190024521A1 FLOW ARRANGEMENT FOR PLACING IN A HOT GAS DUCT OF A TURBOMACHINE 审中-公开
公开(公告)号：US20190024521A1
公开(公告)日：2019-01-24
申请号：US16037056
申请日：2018-07-17
申请人： MTU Aero Engines AG
发明人： Martin Hoeger , Fadi Maatouk , Guenter Ramm , Yavuz Guendogdu , Irene Raab
IPC分类号： F01D9/04 , F01D5/14
摘要： The invention relates to a flow arrangement for placing in the hot gas duct of a turbomachine, having a first surrounding-flow structure and a second surrounding-flow structure, the surrounding-flow structures each having, in reference to the surrounding flow in the hot gas duct, a leading edge and, downstream thereof, a trailing edge, wherein the second surrounding-flow structure is provided as a deflecting blade with a suction side and a pressure side and has a lesser profile thickness than the first surrounding-flow structure, which is arranged on the suction side of the second surrounding-flow structure, and wherein, although the second surrounding-flow structure has a partial axial overlap with the first surrounding-flow structure referred to a longitudinal axis of the turbomachine, the trailing edge of the second surrounding-flow structure is, at the same time, displaced axially downstream relative to the trailing edge of the first surrounding-flow structure.

6. 发明授权

US11371370B2 Flow arrangement for placing in a hot gas duct of a turbomachine 有权
公开(公告)号：US11371370B2
公开(公告)日：2022-06-28
申请号：US16037056
申请日：2018-07-17
申请人： MTU Aero Engines AG
发明人： Martin Hoeger , Fadi Maatouk , Guenter Ramm , Yavuz Guendogdu , Irene Raab
IPC分类号： F01D9/04 , F01D9/06 , F01D5/14
摘要： The invention relates to a flow arrangement for placing in the hot gas duct of a turbomachine, having a first surrounding-flow structure and a second surrounding-flow structure, the surrounding-flow structures each having, in reference to the surrounding flow in the hot gas duct, a leading edge and, downstream thereof, a trailing edge, wherein the second surrounding-flow structure is provided as a deflecting blade with a suction side and a pressure side and has a lesser profile thickness than the first surrounding-flow structure, which is arranged on the suction side of the second surrounding-flow structure, and wherein, although the second surrounding-flow structure has a partial axial overlap with the first surrounding-flow structure referred to a longitudinal axis of the turbomachine, the trailing edge of the second surrounding-flow structure is, at the same time, displaced axially downstream relative to the trailing edge of the first surrounding-flow structure.

7. 发明申请

US20190186417A1 TURBINE MODULE FOR A TURBOMACHINE 审中-公开
公开(公告)号：US20190186417A1
公开(公告)日：2019-06-20
申请号：US16219323
申请日：2018-12-13
申请人： MTU Aero Engines AG
发明人： Guenter Ramm , Martin Hoeger , Irene Raab , Yavuz Guendogdu
IPC分类号： F02K3/06 , F01D9/04 , F01D25/24
CPC分类号： F02K3/06 , F01D5/142 , F01D5/143 , F01D5/146 , F01D9/041 , F01D9/06 , F01D9/065 , F01D25/24 , F05D2240/12 , F05D2240/14 , F05D2250/37
摘要： The present invention relates to a turbine module for a turbomachine, comprising a first flow bypass structure and a second flow bypass structure, said flow bypass structures being arranged in a hot gas duct, which is bounded by the turbine module and is designed to convey a hot gas and, namely, being arranged in succession in relation to a longitudinal axis of the turbine module in a direction of rotation, wherein, in relation to the bypass flow in the hot gas duct, the flow bypass structures each have a leading edge, and, downstream thereto, a trailing edge, and the second flow bypass structure is provided as a deflecting blade, wherein the second flow bypass structure has a smaller profile thickness than the first flow bypass structure, and wherein the hot gas duct is enclosed by a radial width.

8. 发明申请

US20190169989A1 FLOW CHANNEL FOR A TURBOMACHINE 审中-公开
公开(公告)号：US20190169989A1
公开(公告)日：2019-06-06
申请号：US16204954
申请日：2018-11-29
申请人： MTU Aero Engines AG
发明人： Guenter Ramm
IPC分类号： F01D1/02 , F01D25/28
摘要： The present invention relates to a method for designing a flow channel for a turbomachine, in particular a gas turbine that comprises a guide vane cascade having a plurality of guide vanes, which are distributed in the peripheral direction, and flow passages, each of which is bounded by two successive guide vanes, and a support rib arrangement having at least one support rib, wherein a design of one of the flow passages is adapted to this support rib, that it is situated downstream of, in order to reduce a pressure loss and/or a vibrational stimulation.

9. 发明授权

US09835040B2 Turbomachine 有权
公开(公告)号：US09835040B2
公开(公告)日：2017-12-05
申请号：US14508709
申请日：2014-10-07
申请人： MTU Aero Engines AG
发明人： Guenter Ramm
IPC分类号： F01D11/02 , F01D11/12 , F01D11/08
CPC分类号： F01D11/12 , F01D11/02 , F01D11/08 , Y02T50/671
摘要： A turbomachine is described, which includes an annular space seal for at least reducing a fluid exchange between an annular space, through which a main stream flows, and at least one cavity situated radially on the inside and/or radially on the outside of the annular space, the annular space seal having a plurality of sheet-like elastic elements, which are oriented in the radial direction of the turbomachine and in the flow direction of a main stream flowing through the particular guide blade row, and thereby acting as a protective device for the rotor and/or stator during a relative axial displacement with respect to the stator in addition to providing an improved cavity coverage.

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