公开(公告)号：US20180298761A1

公开(公告)日：2018-10-18

申请号：US15948434

申请日：2018-04-09

申请人： MTU Aero Engines AG

发明人： Markus Brettschneider ,  Inga Mahle ,  Fadi Maatouk

IPC分类号： F01D5/14 ,  F01D9/04

摘要： A blade/vane cascade segment of a blade/vane cascade for a turbomachine is disclosed, which comprises a stage with a stage surface as well as a first blade/vane element and a second blade/vane element. The stage surface comprises a first elevation reaching as far as the pressure side of the first blade/vane element and a second elevation reaching as far as the suction side of the second blade/vane element. A furthest downstream point of a boundary of the second elevation has an axial position which differs from the axial position of at least one highest point of the first elevation by a maximum of 10% of an axial cascade span. Furthermore, a blade/vane cascade, a blade/vane channel, a stage, a turbomachine and an aircraft engine are disclosed.

公开(公告)号：US10100655B2

公开(公告)日：2018-10-16

申请号：US14490233

申请日：2014-09-18

申请人： MTU Aero Engines AG

发明人： Christoph Cernay ,  Stephan Prostler ,  Wolfgang Schmidmayr ,  Julian Weber ,  Benjamin Grobkurth ,  Stefan Beichl

IPC分类号： F16J15/44 ,  F01D11/00 ,  F16J15/3288 ,  F02C7/28

摘要： The invention relates to a brush seal, in particular for the sealing of gaps occurring in turbomachines, including a plurality of individual fibers, individual wires or bundles of individual fibers or wires, wherein, in each case, at least two individual fibers or wires, and/or at least two fiber bundles or wire bundles are braided or twisted into a fiber or wire package. In addition, the invention relates to a method for producing a brush seal.

公开(公告)号：US10094230B2

公开(公告)日：2018-10-09

申请号：US14749356

申请日：2015-06-24

申请人： MTU Aero Engines AG

发明人： Julian Weber

IPC分类号： F01D11/00 ,  F16J15/3288

摘要： A brush seal system for sealing a clearance between components of a turbo engine that are movable in relation to one another, in particular of a thermal gas turbine, is disclosed. The brush seal system includes a brush seal housing, which accommodates at least one brush head of a brush seal, where the brush seal housing includes a first component having a cover plate section and a second component having a support plate section. The first component includes an axial flange forming a fish mouth seal on an end opposite the cover plate section. A thermal gas turbine having such a brush seal system is also disclosed.

公开(公告)号：US20180266464A1

公开(公告)日：2018-09-20

申请号：US15919781

申请日：2018-03-13

申请人： MTU Aero Engines AG

发明人： Hermann Klingels ,  Wolfgang Bickmeier

IPC分类号： F16B5/02 ,  F16B37/12 ,  F16B13/06 ,  F01D25/24

CPC分类号： F16B5/0241 ,  F01D25/243 ,  F01D25/26 ,  F05D2260/30 ,  F05D2260/31 ,  F16B13/06 ,  F16B37/122 ,  F16L23/02

摘要： Disclosed is a component with a component section and a flange that is arranged at the component section for connection of the component another element. Arranged at the flange is one or a plurality of oblique flange channels, that is, channels for respectively accommodating a section of a connection element that runs obliquely to a surface portion of the component section that lies opposite to the flange. Further disclosed is a flange connection with at least one component of this kind, another component, and at least one connection element. Disclosed, in addition, is a turbomachine with a housing that is assembled from two or more components by means of such a flange connection.

公开(公告)号：US10066486B2

公开(公告)日：2018-09-04

申请号：US14657422

申请日：2015-03-13

申请人： MTU Aero Engines AG

发明人： Dominik Broszat ,  Nicolas Thouault

IPC分类号： F01D5/10 ,  F01D5/14 ,  F01D9/04 ,  F01D5/02 ,  F01D1/04 ,  F01D5/16 ,  G06F17/50

摘要： A method for designing a turbine having a plurality of stages disposed axially one behind the other in the direction of flow through the turbine, each stage being formed of a stationary row of a plurality of stator vanes and a rotating row of a plurality of rotor blades. The row of rotor blades of at least one of these stages has a plurality of rotor blade clusters each formed of at least two rotor blades (A1, B1; A2, B2) having different airfoil profiles and/or different distances (φA, φB) from adjacent rotor blades following in the direction of rotation. A vane-to-blade-cluster ratio (V/(B/P)) parameter indicates the ratio of the number of stator vanes (V) to the quotient (B/P) of the number of rotor blades (B) of the stage divided by the number of rotor blades per rotor blade cluster (P). Under a predetermined operating condition of the turbine, this vane-to-blade-cluster ratio parameter is above an upper cut-off limit or below a lower cut-off limit for the modes k=−1, k=−2 and/or k=−3, in particular above an upper cut-off limit for the mode k=−1 or between a lower cut-off limit for the mode k=−1 and an upper cut-off limit for the mode k=−2, of a frequency defined by a ratio of the blade-passing frequency to the number of rotor blades per rotor blade cluster or an integral multiple of this ratio.

公开(公告)号：US20180223670A1

公开(公告)日：2018-08-09

申请号：US15886977

申请日：2018-02-02

申请人： MTU Aero Engines AG

发明人： Markus Brettschneider ,  Inga Mahle

IPC分类号： F01D5/14 ,  F01D9/04

CPC分类号： F01D5/145 ,  F01D5/143 ,  F01D9/041 ,  F04D29/321 ,  F04D29/542 ,  F04D29/667 ,  F05D2240/12 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/129 ,  F05D2240/80

摘要： Disclosed is a blade/vane cascade segment of a blade/vane cascade of a turbomachine, which comprises at least two blade/vane elements defining an axial cascade width, and a stage with a stage surface, as well as a stage edge on the inflow side. The stage surface has an elevation extending up to the pressure side of a first blade/vane element and a depression extending up to the suction side of the other blade/vane. At least one highest point of the elevation and at least one lowest point of the depression each lie at least 30% and at most 60% of the axial cascade width downstream of the inflow edges of the blade/vane elements. In this case, the elevation and the depression each come close to the stage edge on the inflow side. Also disclosed are a blade/vane cascade, a stage for a blade/vane cascade segment, a blade/vane channel, and a turbomachine.

公开(公告)号：US10001016B2

公开(公告)日：2018-06-19

申请号：US14795017

申请日：2015-07-09

申请人： MTU Aero Engines AG

发明人： Frank Stiehler ,  Andreas Hartung

IPC分类号： F01D5/16 ,  B23P15/04 ,  F01D5/26

CPC分类号： F01D5/16 ,  B23P15/04 ,  F01D5/26 ,  F05D2230/232

摘要： A turbomachine blade having a main body (10) that includes a plane, first attachment surface (100) having a first rim contour (110), a cover (20; 21, 22) that has a plane, second attachment surface (200) having a second rim contour (210) that is welded to the first attachment surface, and a tuning body configuration having at least one tuning body (30; 31-33) for contacting an inner wall (220) of the cover by impact therewith, a gap (s) being formed between the first and the second rim contour.

公开(公告)号：US09989093B2

公开(公告)日：2018-06-05

申请号：US14821295

申请日：2015-08-07

申请人： MTU Aero Engines AG

发明人： Alexander Boeck

IPC分类号： F01D17/16 ,  F16C33/34 ,  F16C19/46 ,  F16C33/36 ,  F01D25/16 ,  F16C27/04 ,  F16C19/52

CPC分类号： F16C33/34 ,  F01D17/16 ,  F01D17/162 ,  F01D25/16 ,  F05D2240/54 ,  F16C19/46 ,  F16C19/463 ,  F16C19/525 ,  F16C27/04 ,  F16C33/36

摘要： A roller bearing, particularly a needle bearing, for arranging on a pivot pin of a variable guide vane of a turbomachine, is disclosed. The roller bearing includes at least one radially elastic needle which has two opposing end regions and at least one roller region arranged between the end regions and constructed in a cross-sectionally thickened manner. The end regions roll off at associated raceways of a bearing housing of the roller bearing and the roller region is arranged in the region of an associated groove of the bearing housing. A variable guide vane with at least one such roller bearing, a housing of a turbomachine with such a guide vane, as well as a turbomachine, is also disclosed.

公开(公告)号：US09982566B2

公开(公告)日：2018-05-29

申请号：US14329570

申请日：2014-07-11

申请人： MTU Aero Engines AG

发明人： Walter Gieg ,  Petra Kufner ,  Rudolf Stanka

IPC分类号： F01D25/18 ,  F01D11/12 ,  F01D9/02 ,  F01D25/24

CPC分类号： F01D25/183 ,  F01D9/02 ,  F01D11/12 ,  F01D25/246 ,  F05D2230/64 ,  F05D2240/11

摘要： A turbomachine includes a sealing segment ring that is provided between a front guide vane row and a back guide vane row for sealing a radial gap between a casing section and a rotor blade row rotating between the guide vane rows, wherein the sealing segment ring has a plurality of identical sealing segments and at least one of the guide vane rows has a plurality of identical guide vane segments, wherein the sealing segments each have a plurality of engagement sites lying adjacent to one another in the peripheral direction for interaction with securing elements of this guide vane row, wherein the engagement sites and securing elements are distributed uniformly over the periphery and the engagement sites are a multiple of the securing elements, a sealing element, and a guide vane segment.

公开(公告)号：US09982547B2

公开(公告)日：2018-05-29

申请号：US14747026

申请日：2015-06-23

申请人： MTU Aero Engines AG

发明人： Alexander Boeck

IPC分类号： F01D9/02 ,  F04D29/64 ,  F01D11/00 ,  F01D25/28 ,  F01D17/16 ,  F04D29/56 ,  F01D9/04

CPC分类号： F01D9/02 ,  F01D9/04 ,  F01D11/005 ,  F01D17/162 ,  F01D25/28 ,  F04D29/563 ,  F04D29/644 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  Y02T50/671 ,  Y10T29/49323

摘要： A guide mechanism for a gas turbine has a casing supporting on its interior a duct delimited by radially inner and outer duct segments. A variable guide vane located at least partially within the duct can rotate about an axis of rotation to guide flow of a fluid in the duct. The radially inner duct segment is fastened to the guide vane and is retained on the casing element via the guide vane, which is mounted on the casing element via a bushing inserted in the radial direction from outside to inside into a passage opening of the casing element.