公开(公告)号：US20180328383A1

公开(公告)日：2018-11-15

申请号：US15493719

申请日：2017-04-21

申请人： General Electric Company

发明人： Scott Allen Jones

IPC分类号： F04D29/52 ,  F01D25/00 ,  F04D29/02 ,  C23C4/10 ,  C23C4/134 ,  C23C4/08

CPC分类号： F04D29/526 ,  C23C4/02 ,  C23C4/08 ,  C23C4/10 ,  C23C4/134 ,  F01D11/122 ,  F01D25/007 ,  F01D25/24 ,  F04D29/023 ,  F04D29/164 ,  F05D2220/323 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2240/14 ,  F05D2260/95 ,  F05D2300/173 ,  F05D2300/522 ,  F05D2300/611

摘要： Coating systems for components of a gas turbine engine, such as a compressor case, are provided. The coating system can include a dense layer disposed along the inner surface of the compressor case as well as an abradable, top coat disposed along the dense layer. The combination of dense layer and abradable top coat can reduce the occurrence of galvanic corrosion of the coating system and thereby increase the lifetime of the coating system and preserve blade clearances within the compressor. Methods are also provided for applying the coating system onto a compressor case.

公开(公告)号：US20180258784A1

公开(公告)日：2018-09-13

申请号：US15911380

申请日：2018-03-05

申请人： MTU Aero Engines AG

发明人： Steffen SCHLOTHAUER ,  Frank STIEHLER ,  Alexander LADEWIG ,  Christian LIEBL ,  Johannes CASPER ,  Juergen KRAUS ,  Johannes JAKIMOV

IPC分类号： F01D11/12

CPC分类号： F01D11/125 ,  F01D11/127 ,  F04D29/164 ,  F04D29/526 ,  F05D2220/323 ,  F05D2230/31 ,  F05D2240/55 ,  F05D2250/283 ,  F05D2260/30

摘要： A seal carrier (63) for a turbomachine (60) which is assembled from seal carrier segments, is provided. The seal carrier segments each have a seal structure (1a, b) on the radially inward side. These seal structures (1a, b) are either interleaved in the circumferential direction (4) such that a cross-sectional plane containing the longitudinal axis (2) of the turbomachine (60) intersects both the first seal structure (1a) and the second seal structure (1b), or the seal structures (1a, b) rest against each another.

公开(公告)号：US10060444B2

公开(公告)日：2018-08-28

申请号：US15361877

申请日：2016-11-28

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Andrew R. Marshall ,  David Menheere

IPC分类号： F04D29/56 ,  F04D29/54 ,  F04D29/16 ,  F01D17/16 ,  F01D5/14 ,  B33Y10/00 ,  F04D29/02 ,  B33Y80/00 ,  B22F3/105 ,  B22F5/00 ,  B23K15/00 ,  F01D11/12 ,  B23K101/00

CPC分类号： F04D29/563 ,  B22F3/1055 ,  B22F5/009 ,  B23K15/0086 ,  B23K2101/001 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/143 ,  F01D11/12 ,  F01D17/162 ,  F04D29/023 ,  F04D29/164 ,  F04D29/542 ,  F05D2230/31 ,  F05D2300/514 ,  F05D2300/603 ,  F05D2300/608 ,  F05D2300/613 ,  Y10T29/49245

摘要： A variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections on the inner and/or outer shroud protrude into the annular gas path, each projection being at least partially circumferentially disposed between two variable vanes and located adjacent the overhang portion thereof. The projections have an angled planar surface that is substantially parallel to a plane defined by a terminal edge of the overhang portion of the variable vanes when pivoted through a vane pivot arc.

公开(公告)号：US10060439B2

公开(公告)日：2018-08-28

申请号：US15446241

申请日：2017-03-01

申请人： MTU Aero Engines AG

发明人： Georg Zotz

IPC分类号： F01D11/00 ,  F01D11/08 ,  F01D5/18 ,  F01D5/20 ,  F04D29/16 ,  F04D19/00 ,  F04D29/56 ,  F04D29/54 ,  B23K26/342 ,  B33Y10/00 ,  B33Y80/00 ,  B22F3/105 ,  B22F5/04 ,  B23K101/00

CPC分类号： F04D29/164 ,  B22F3/1055 ,  B22F5/04 ,  B22F2998/10 ,  B23K26/342 ,  B23K2101/001 ,  B23P15/04 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/18 ,  F01D5/20 ,  F01D11/00 ,  F01D11/08 ,  F01D11/10 ,  F01D17/14 ,  F01D17/16 ,  F01D17/162 ,  F04D19/00 ,  F04D29/544 ,  F04D29/56 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49336

摘要： A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade.

公开(公告)号：US20180231014A1

公开(公告)日：2018-08-16

申请号：US15430783

申请日：2017-02-13

申请人： United Technologies Corporation

发明人： Pantcho P. Stoyanov ,  Agnieszka M. Wusatowska-Sarnek ,  Thomas D. Kasprow ,  David Ulrich Furrer ,  Sergei F. Burlatsky

IPC分类号： F04D29/16 ,  F04D29/52 ,  C23C24/04 ,  C23C4/12

CPC分类号： F04D29/164 ,  C23C4/12 ,  C23C24/04 ,  C23C28/022 ,  C23C28/027 ,  C23C28/324 ,  C23C28/3455 ,  C23C28/42 ,  F01D5/288 ,  F01D11/122 ,  F04D29/526 ,  F05D2230/31

摘要： A multilayer abradable coating includes at least one first abradable layer; and at least one second abradable layer, wherein the first abradable layer and the second abradable layer have different properties related to erosion resistance.

公开(公告)号：US09957976B2

公开(公告)日：2018-05-01

申请号：US14494103

申请日：2014-09-23

申请人： ROLLS-ROYCE PLC

发明人： Peter Allford

IPC分类号： F04D29/54 ,  F04D29/16 ,  F04D29/52 ,  F04D29/68

CPC分类号： F04D29/547 ,  F04D29/164 ,  F04D29/526 ,  F04D29/685

摘要： There is presented a casing arrangement for a gas turbine engine. The casing arrangement includes a plurality of tip treatment bars extending between a pair of spaced-apart annular supports, with each tip treatment bar being elongate and supported at each end by a respective support such that each end of the bar is received within an opening formed in the respective support. At least the ends of each tip treatment bar are tapered in transverse cross-section so as to have a wedge-shaped profile, and the openings in the supports have a complementary tapered shape for receipt and retention of the bar ends therein.

公开(公告)号：US20180100406A1

公开(公告)日：2018-04-12

申请号：US15291650

申请日：2016-10-12

申请人： United Technologies Corporation

发明人： Nathan K. Galle

IPC分类号： F01D11/08 ,  F01D9/02 ,  F04D29/54 ,  F04D29/16

CPC分类号： F01D11/08 ,  F01D9/02 ,  F01D11/005 ,  F01D25/246 ,  F04D29/164 ,  F04D29/542 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2250/183 ,  F05D2250/75 ,  F05D2300/177 ,  F16J15/0887

摘要： A seal may comprise a first ply including an annular shape and a second ply including a discontinuous annular shape having an axial split. The second ply may be positioned adjacent to a surface of the first ply.

公开(公告)号：US09885368B2

公开(公告)日：2018-02-06

申请号：US13849980

申请日：2013-03-25

申请人： Carrier Corporation

发明人： Ryan K. Dygert ,  Peter R. Bushnell

IPC分类号： F04D27/02 ,  F04D29/52 ,  F04D29/16 ,  F04D29/68 ,  F04D29/32

CPC分类号： F04D29/526 ,  F04D29/164 ,  F04D29/326 ,  F04D29/685

摘要： A fan assembly includes a shrouded fan rotor having fan blades extending from a hub and rotatable about a central axis. A fan shroud extends circumferentially around the fan rotor and secured to the fan blades. The shroud includes a first axially extending annular portion secured to the fan blades, a second axially extending annular portion radially outwardly spaced from the first axially extending annular portion, and a third portion connecting the first and second axially extending annular portions. A casing is located circumferentially around the fan shroud defining a radial clearance between the casing and the fan shroud, and includes casing wedges extending from a radially inboard surface of the casing toward the shroud and defining a radial wedge gap between a first wedge surface and the shroud and an axial wedge gap between a second wedge surface and an upstream end of the fan shroud.

公开(公告)号：US20170350412A1

公开(公告)日：2017-12-07

申请号：US15539858

申请日：2015-12-24

申请人： DENSO CORPORATION

发明人： Tetsuya HIOKI

IPC分类号： F04D29/32 ,  F04D29/58 ,  F04D29/52 ,  F04D29/66 ,  F04D29/16

CPC分类号： F04D29/326 ,  F04D29/164 ,  F04D29/522 ,  F04D29/526 ,  F04D29/5833 ,  F04D29/667

摘要： A blowing device includes an axil fan having a plurality of blades and causing an air to flow through the blowing device, and a fan shroud rotatably supporting the fan. The fan shroud includes a ring portion surrounding a circumference of the fan, and an air guide portion connecting an outer rim of the fan shroud and an inner rim of the ring portion. The fan shroud includes a specific rim portion that is a part of the outer rim of the fan shroud, a distance from the specific rim portion to the inner rim of the ring portion being shorter than other parts of the outer rim. The fan shroud includes a counter flow introduction passage provided in the air guide portion and extending from a position located inward of the specific rim portion. The blowing device is capable of limiting a rotation noise of the fan.

公开(公告)号：US20170314566A1

公开(公告)日：2017-11-02

申请号：US15142208

申请日：2016-04-29

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： CHRISTOPHER W. STROCK

IPC分类号： F04D29/16 ,  F01D5/02 ,  F04D29/32 ,  F04D29/38 ,  F02C3/04

CPC分类号： F04D29/164 ,  F01D5/02 ,  F01D5/288 ,  F01D11/122 ,  F02C3/04 ,  F04D29/321 ,  F04D29/325 ,  F04D29/388 ,  F05D2220/36 ,  F05D2230/90 ,  F05D2240/307 ,  F05D2240/35 ,  F05D2300/2282 ,  F05D2300/2291 ,  F05D2300/48 ,  F05D2300/509 ,  F05D2300/516 ,  F05D2300/6032 ,  Y02T50/672

摘要： An abradable seal comprises an organic matrix composite comprising an additive and an organic component, the additive is configured to prevent adhesion of the organic component onto an abrasive blade tip.