专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US09822706B2 Gas turbine subassembly 有权
公开(公告)号：US09822706B2
公开(公告)日：2017-11-21
申请号：US14829288
申请日：2015-08-18
申请人： MTU Aero Engines AG
发明人： Martin Hoeger
IPC分类号： F01D25/12 , F02C7/18 , F01D5/14 , F01D25/26 , F02C3/04
CPC分类号： F02C7/18 , F01D5/143 , F01D25/12 , F01D25/26 , F02C3/04 , F05D2220/32 , F05D2240/35 , F05D2260/20 , Y02T50/673
摘要： The present invention relates to a subassembly for a gas turbine, in particular a gas turbine aircraft engine, having a turbine casing (11); a midframe (14), which is adjacent downstream to the turbine casing and has a number of support ribs (15) spaced apart in the peripheral direction. The turbine casing and the midframe define a flow duct (33) for a working gas exiting a combustion chamber of the gas turbine, and a cavity, in particular a cooling air duct (19), with an opening on the flow duct side is formed between the turbine casing and the midframe. An edge contour (40) of the opening on the turbine casing side varies along the periphery radially and/or axially.

2. 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.

3. 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.

4. 发明申请

US20160061111A1 GAS TURBINE SUBASSEMBLY 有权
标题翻译：气体涡轮增压
公开(公告)号：US20160061111A1
公开(公告)日：2016-03-03
申请号：US14829288
申请日：2015-08-18
申请人： MTU Aero Engines AG
发明人： Martin Hoeger
IPC分类号： F02C7/18 , F01D25/12 , F02C3/04 , F01D25/26
CPC分类号： F02C7/18 , F01D5/143 , F01D25/12 , F01D25/26 , F02C3/04 , F05D2220/32 , F05D2240/35 , F05D2260/20 , Y02T50/673
摘要： The present invention relates to a subassembly for a gas turbine, in particular a gas turbine aircraft engine, having a turbine casing (11); a midframe (14), which is adjacent downstream to the turbine casing and has a number of support ribs (15) spaced apart in the peripheral direction. The turbine casing and the midframe define a flow duct (33) for a working gas exiting a combustion chamber of the gas turbine, and a cavity, in particular a cooling air duct (19), with an opening on the flow duct side is formed between the turbine casing and the midframe. An edge contour (40) of the opening on the turbine casing side varies along the periphery radially and/or axially.
摘要翻译：本发明涉及一种用于燃气轮机的子组件，特别是具有涡轮机壳体（11）的燃气涡轮机飞机发动机。中间框架（14），其邻近涡轮机壳体的下游并且具有在周向方向上间隔开的多个支撑肋（15）。涡轮机壳体和中架限定用于离开燃气轮机的燃烧室的工作气体的流动管道（33），并且形成具有在流动管道侧上的开口的空腔，特别是冷却空气管道（19）在涡轮机壳体和中架之间。涡轮机壳体侧的开口的边缘轮廓（40）沿径向和/或轴向沿周边变化。

5. 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.

6. 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.

7. 发明授权

US09920640B2 Extruded profile for manufacturing a blade of an outlet guide vane 有权
公开(公告)号：US09920640B2
公开(公告)日：2018-03-20
申请号：US14595094
申请日：2015-01-12
申请人： MTU Aero Engines AG
发明人： Martin Hoeger
IPC分类号： F01D9/04 , B21C23/16 , F01D5/14
CPC分类号： F01D9/041 , B21C23/16 , F01D5/141 , F05D2220/3215 , F05D2230/24 , F05D2230/61 , F05D2240/12 , F05D2250/70 , F05D2250/713 , F05D2250/72 , F05D2250/73 , F05D2250/75 , Y02T50/673
摘要： An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine. A cross-sectional area has an axial length LAX and a thickness D/LAX relative to the axial length LAX. A cross-sectional area has an at least nearly axisymmetric leading edge region, a first transition region having a varying relative thickness D/LAX. A first constant region has a relative thickness D/LAX at least substantially constant and, relative to a leading edge of the extruded profile, begins at the closest at 10% LAX and ends at the furthest at 50% LAX. A second transition region has a varying relative thickness D/LAX and, relative to the leading edge of the extruded profile, begins at the closest at 30% LAX and ends at the furthest at 90% LAX. A second constant region has a relative thickness D/LAX at least substantially constant and an axial length X of 40% LAX at most; and an at least nearly axisymmetric trailing edge region.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式