公开(公告)号：US20190017174A1

公开(公告)日：2019-01-17

申请号：US16033984

申请日：2018-07-12

Applicant: MTU Aero Engines AG

Inventor： Martin Metscher ,  Benedikt Heidenreich ,  Jan Haegert ,  Nils Hiller ,  Patrick Lang

IPC: C23C24/08 ,  F01D25/16 ,  F01D9/00 ,  F01D25/00

Abstract: The invention relates to a method for coating a component, which is provided for the hot gas duct of a turbomachine, wherein the coating material is applied onto the uncoated component surface in the form of particles in mixture with a binding agent, and the component with the particle-treated binding agent thereupon then undergoes thermal treatment in such a way that the binding agent is released and the coating material remains on the component.

公开(公告)号：US09726042B2

公开(公告)日：2017-08-08

申请号：US14638775

申请日：2015-03-04

Applicant: MTU Aero Engines AG

Inventor： Stefan Sasse ,  Martin Metscher ,  Jan Haegert

IPC: F01D25/24 ,  F01D9/06 ,  F01D25/16 ,  F02C7/20

CPC classification number: F01D25/243 ,  F01D9/065 ,  F01D25/162 ,  F02C7/20 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2240/14 ,  F05D2260/30 ,  F05D2260/36 ,  F05D2260/37 ,  Y10T29/49229

Abstract: A gas turbine duct casing, in particular for an aircraft engine, is disclosed. The duct casing has a first wall segment and a second wall segment which is connected to the first wall segment by a clamp arrangement. The clamp arrangement has at least one clamp and one bolt which passes through a hole in the clamp and is screwed to a nut on a side of the clamp facing away from the wall segments. The nut braces at least one first leg of the clamp against the first wall segment, in particular by an intermediate element, and braces at least one second leg of the clamp against the second wall segment. The bolt has a head which is guided in a form-fitting manner in a groove on the outside of the first wall segment facing away from the gas duct.

公开(公告)号：US20150252691A1

公开(公告)日：2015-09-10

申请号：US14638775

申请日：2015-03-04

Applicant: MTU Aero Engines AG

Inventor： Stefan SASSE ,  Martin Metscher ,  Jan Haegert

IPC: F01D25/24 ,  F02C7/20

CPC classification number: F01D25/243 ,  F01D9/065 ,  F01D25/162 ,  F02C7/20 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2240/14 ,  F05D2260/30 ,  F05D2260/36 ,  F05D2260/37 ,  Y10T29/49229

Abstract: A gas turbine duct casing, in particular for an aircraft engine, is disclosed. The duct casing has a first wall segment and a second wall segment which is connected to the first wall segment by a clamp arrangement. The clamp arrangement has at least one clamp and one bolt which passes through a hole in the clamp and is screwed to a nut on a side of the clamp facing away from the wall segments. The nut braces at least one first leg of the clamp against the first wall segment, in particular by an intermediate element, and braces at least one second leg of the clamp against the second wall segment. The bolt has a head which is guided in a form-fitting manner in a groove on the outside of the first wall segment facing away from the gas duct.

Abstract translation: 公开了一种特别用于飞机发动机的燃气涡轮机导管外壳。 管道壳体具有第一壁段和第二壁段，其通过夹具装置连接到第一壁段。 夹具装置具有至少一个夹具和一个螺栓，其穿过夹具中的孔，并且螺纹连接到夹紧器侧面上远离壁段的螺母。 螺母将夹具的至少一个第一腿支撑抵靠第一壁段，特别是通过中间元件，并且将夹具的至少一个第二腿支撑抵靠第二壁段。 螺栓具有头部，其以形状配合的方式被引导到第一壁段的背离气体管道的外侧的凹槽中。

公开(公告)号：US11359289B2

公开(公告)日：2022-06-14

申请号：US16033984

申请日：2018-07-12

Applicant: MTU Aero Engines AG

Inventor： Martin Metscher ,  Benedikt Heidenreich ,  Jan Haegert ,  Nils Hiller ,  Patrick Lang

IPC: C23C24/08 ,  F01D25/16 ,  F01D5/28 ,  F01D9/00 ,  F01D25/00 ,  C23C10/20 ,  C23C10/18 ,  C23C10/48 ,  C23C12/02 ,  C23C10/30 ,  C23C10/50 ,  C23C10/04

Abstract: The invention relates to a method for coating a component, which is provided for the hot gas duct of a turbomachine, wherein the coating material is applied onto the uncoated component surface in the form of particles in mixture with a binding agent, and the component with the particle-treated binding agent thereupon then undergoes thermal treatment in such a way that the binding agent is released and the coating material remains on the component.

公开(公告)号：US20190170017A1

公开(公告)日：2019-06-06

申请号：US16199363

申请日：2018-11-26

Applicant: MTU Aero Engines AG

Inventor： Martin Metscher ,  Jan Haegert

IPC: F01D25/28 ,  F02C7/20 ,  F01D25/24

Abstract: A supporting device (10) for a casing (12) of a turbomachine (100), for bracing against forces acting on the casing (12) that occur during operation of the turbomachine (100), having at least one hub element (40), and at least one supporting element (20) for holding the hub element (40) on the casing (12). The supporting device (10) includes at least one rotary joint (30) which is used to rotatably connect the hub element (40) to the supporting element (20). Other aspects of the present invention relate to a casing (12) for a turbomachine (100), and to a turbomachine (100).

公开(公告)号：US20180171812A1

公开(公告)日：2018-06-21

申请号：US15845638

申请日：2017-12-18

Applicant: MTU Aero Engines AG

Inventor： Jan Haegert

IPC: F01D11/00 ,  F16J15/06

CPC classification number: F01D11/003 ,  F01D9/065 ,  F01D25/183 ,  F05D2240/55 ,  F05D2240/58 ,  F05D2260/98 ,  F16J15/067

Abstract: A sealing assembly for a turbomachine is provided, in particular for a gas turbine, having an annular groove G, in which at least one sealing ring (2) is located to seal a gap (S), at least one spiral ring (3) being located in the annular groove to axially support the sealing ring (2) against a first end face (11) of the annular groove.