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1. 发明申请

US20170276023A1 METHOD FOR MANUFACTURING A HOUSING OF A TURBOMACHINE AND TURBOMACHINE HOUSING 审中-公开
公开(公告)号：US20170276023A1
公开(公告)日：2017-09-28
申请号：US15455534
申请日：2017-03-10
申请人： MTU Aero Engines AG
发明人： Karl-Hermann Richter
IPC分类号： F01D25/24 , B23K26/21 , B23K26/38 , B23K15/00
CPC分类号： F01D25/24 , B22F3/1055 , B22F5/009 , B22F7/062 , B22F7/08 , B23K15/0046 , B23K26/21 , B23K26/38 , B23K2101/001 , B33Y10/00 , B33Y80/00 , F05D2220/32 , F05D2230/11 , F05D2230/13 , F05D2230/232 , F05D2230/233 , F05D2230/234 , F05D2230/50 , Y02P10/295
摘要： The invention relates to a method for manufacturing a housing of a turbomachine, in particular a gas turbine. The method comprises at least the steps: providing a housing blank (10), manufacturing a housing element (14), producing an assembly opening (12) corresponding to the housing element (14) in the housing blank (10), arranging the housing element (14) in the assembly opening (12), and joining the housing element (14) to the housing blank (10) by means of a welding method. In addition, the invention relates to a turbomachine housing.

2. 发明申请

US20170067487A1 TURBOMACHINE BLADE 审中-公开
标题翻译：涡轮叶片
公开(公告)号：US20170067487A1
公开(公告)日：2017-03-09
申请号：US15257434
申请日：2016-09-06
申请人： MTU Aero Engines AG
发明人： Andreas Hartung , Karl-Hermann Richter , Herbert Hanrieder , Manfred Schill
IPC分类号： F04D29/66 , F01D5/16 , F04D29/54 , F01D25/06 , F04D29/32 , F01D5/26 , F01D9/04
CPC分类号： F04D29/668 , F01D5/16 , F01D5/26 , F01D9/041 , F01D25/06 , F04D29/324 , F04D29/542 , Y02T50/671
摘要： A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber (10) in which at least one impulse element (11) is disposed with play, at least one second impact chamber (20) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber (10) along a first matrix axis (A) and in which at least one impulse element (21) is disposed with play, and at least one third impact chamber (30) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber (10) along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element (31) is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.
摘要翻译：用于涡轮机的叶片，特别是燃气轮机的压缩机或涡轮级，具有至少一个矩阵，其具有第一冲击室（10），其中至少一个冲击元件（11）在其中放置，至少一个第二冲击室（20），其体积重心沿着第一矩阵轴线（A）从第一冲击室（10）的体积重心偏移，并且其中至少一个冲击元件（21）与游戏一起设置;以及至少一个第三冲击室（30），其体积重心沿横向于第一矩阵轴线（A）的第二矩阵轴线（B）偏离第一冲击室（10）的体积重心，并且其中至少一个冲击元件（31））设置为游隙，提供形成至少60°且不超过120°的角度的涡轮机的第一矩阵轴线（A）和旋转轴线（R）。

3. 发明申请

US20140342169A1 METHOD FOR HARDFACING THE Z-NOTCH OF TIAL BLADES 有权
标题翻译：用于硬化钛刀片的Z形槽的方法
公开(公告)号：US20140342169A1
公开(公告)日：2014-11-20
申请号：US14360241
申请日：2012-11-06
申请人： MTU Aero Engines AG
发明人： Bernd Daniels , Herbert Hanrieder , Karl-Hermann Richter , Michael Strasser
IPC分类号： B22F7/04 , F01D5/28
CPC分类号： B22F7/04 , B22F7/062 , B23K1/0018 , B23K1/008 , B23K2101/001 , B23K2101/35 , C22C1/0433 , C23C28/021 , C23C28/028 , C23C30/00 , F01D5/22 , F01D5/28 , Y10T428/31678
摘要： A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.
摘要翻译：公开了一种用于在组件，特别是TiAl驱动单元部件上布置涂层，特别是表面硬化的方法。涂层包括金属涂层材料。形成生坯的涂料是在组分存在焊料的情况下配置的，并通过组合的焊料烧结工艺形成涂层并固定在部件上。

4. 发明授权

US11306596B2 Gas turbine blade impulse body module 有权
公开(公告)号：US11306596B2
公开(公告)日：2022-04-19
申请号：US16712513
申请日：2019-12-12
申请人： MTU Aero Engines AG
发明人： Karl-Hermann Richter , Herbert Hanrieder , Steffen Gerloff
IPC分类号： F01D5/16 , F01D5/26 , B23K101/00 , F01D5/14 , F01D9/04
摘要： The present invention relates to an impulse body module group with at least two impulse body modules, which, in particular, are identical in construction, for a gas turbine blade, wherein each of the impulse body modules comprises a housing, which, in particular, is of one piece and which has a first cavity, which is closed, in particular in an airtight manner, by a first cover, which is joined to the housing, in particular in a material-bonded manner, and in which a single, in particular spherical or cylindrical, first impulse body is accommodated with play of movement in at least one first direction of impact, wherein the housing has no additional cavity or a single additional cavity, in which a single, in particular spherical or cylindrical, additional impulse body is accommodated with play of movement in at least one direction of impact.

5. 发明授权

US10550720B2 Guide vane segment 有权
公开(公告)号：US10550720B2
公开(公告)日：2020-02-04
申请号：US15483565
申请日：2017-04-10
申请人： MTU Aero Engines AG
发明人： Markus Schlemmer , Andreas Hartung , Karl-Hermann Richter , Herbert Hanrieder
IPC分类号： F01D25/06 , F01D9/04 , F04D29/54 , F04D29/66
摘要： A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

6. 发明授权

US10415425B2 Turbomachine stage 有权
公开(公告)号：US10415425B2
公开(公告)日：2019-09-17
申请号：US15407416
申请日：2017-01-17
申请人： MTU Aero Engines AG
发明人： Markus Schlemmer , Andreas Hartung , Karl-Hermann Richter , Herbert Hanrieder
IPC分类号： F01D25/06 , F01D5/12 , F01D5/30 , F01D5/34 , F01D5/16 , F01D5/26 , F01D25/26 , F01D9/04
摘要： The invention relates to a turbomachine including:a guide baffle, whose sv guide blades are situated on c guide blade carriers; andan adjacent moving baffle including sb moving blades;the guide baffle nv including impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle nb including impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient ∑ i = 1 n v ⁢ ⁢ m i s v - c of sum ∑ i = 1 n v ⁢ ⁢ m i of the masses of all impulse bodies of the guide baffle divided by the difference (sv−c) of the number sv of all guide blades minus the number c of all guide blade carriers amounts to at least 1.5 times quotient ∑ j = 1 n b ⁢ ⁢ m j s b of sum ∑ j = 1 n b ⁢ ⁢ m j of the masses of all impulse bodies of the moving baffle divided by the number sb of all moving blades ( ∑ i = 1 n v ⁢ ⁢ m i s v - c ≥ 1.5 · ∑ j = 1 n b ⁢ ⁢ m j s b ) .

7. 发明授权

US10006300B2 Armoring sealing fins of TiAl vanes by induction brazing hard-material particles 有权
公开(公告)号：US10006300B2
公开(公告)日：2018-06-26
申请号：US14358939
申请日：2012-11-06
申请人： MTU Aero Engines AG
发明人： Bernd Daniels , Karl-Hermann Richter
IPC分类号： F01D9/04 , F01D5/22 , F01D5/28 , C23C24/10 , B23K1/00 , B23K1/002
CPC分类号： F01D9/041 , B23K1/0018 , B23K1/002 , C23C24/103 , F01D5/225 , F01D5/288
摘要： A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material.

8. 发明申请

US20170292403A1 Guide Vane Segment 审中-公开
公开(公告)号：US20170292403A1
公开(公告)日：2017-10-12
申请号：US15483565
申请日：2017-04-10
申请人： MTU Aero Engines AG
发明人： Markus Schlemmer , Andreas Hartung , Karl-Hermann Richter , Herbert Hanrieder
IPC分类号： F01D25/06 , F04D29/54 , F04D29/66 , F01D9/04
摘要： A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

9. 发明申请

US20170292387A1 Guide Vane Segment 审中-公开
公开(公告)号：US20170292387A1
公开(公告)日：2017-10-12
申请号：US15483478
申请日：2017-04-10
申请人： MTU Aero Engines AG
发明人： Markus Schlemmer , Andreas Hartung , Karl-Hermann Richter , Herbert Hanrieder
IPC分类号： F01D5/26 , F01D5/16 , F01D25/06
CPC分类号： F01D5/26 , F01D5/14 , F01D5/16 , F01D25/06 , F05D2250/241 , F05D2260/96 , Y02T50/671
摘要： A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (B) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

10. 发明授权

US11002140B2 Guide vane segment 有权
公开(公告)号：US11002140B2
公开(公告)日：2021-05-11
申请号：US15483478
申请日：2017-04-10
申请人： MTU Aero Engines AG
发明人： Markus Schlemmer , Andreas Hartung , Karl-Hermann Richter , Herbert Hanrieder
IPC分类号： F01D5/26 , F01D5/16 , F01D25/06 , F01D5/14
摘要： A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (B) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

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