公开(公告)号：EP3274578A1

公开(公告)日：2018-01-31

申请号：EP16719444.8

申请日：2016-03-25

申请人： SAFRAN AIRCRAFT ENGINES

发明人： MARDJONO, Jacky ,  CHANEZ, Philippe ,  GONZALEZ, Jérémy ,  KOENIG, Maxime ,  VERSAEVEL, Marc ,  ZAGANELLI, Franck ,  YESILCIMEN, Henri

IPC分类号： F02K1/34 ,  F02K1/38

CPC分类号： F02K1/34 ,  F02K3/06 ,  F05D2220/323 ,  F05D2260/96 ,  F05D2270/306 ,  Y02T50/671

摘要： The invention relates to a device for reducing the jet noise of a turbine engine, comprising an outer cowl (16) provided inside a wall (20) defining on the outside an annular section (22) for the flow of a secondary stream from the turbine engine, said wall of the outer cowl comprising a plurality of microjet circuits (28) each comprising means (30) for sampling gas flows in the flow section of the secondary stream which open into a single supply pipe (32), which in turn opens onto a trailing edge of the outer cowl via at least one ejection grating (34) capable of dividing the sampled stream of gas into a plurality of streams of gas having cross-sections with dimensions smaller than a cross-section (
D ) of the supply pipe.

公开(公告)号：EP3225786A3

公开(公告)日：2018-01-17

申请号：EP17153922.4

申请日：2017-01-31

申请人： General Electric Company

发明人： BISHOP, Michael Jason ,  KELKAR, Rajendra Madhukar ,  YUEN, Alex ,  WOODFIELD, Andrew Philip

IPC分类号： F01D11/24 ,  F01D5/32 ,  F01D5/30

CPC分类号： F04D29/34 ,  B22F3/04 ,  B22F3/1055 ,  B22F3/15 ,  B22F3/225 ,  B22F5/009 ,  B33Y80/00 ,  F01D5/3007 ,  F01D5/3015 ,  F01D5/32 ,  F01D5/323 ,  F01D5/326 ,  F02K3/06 ,  F04D29/322 ,  F04D29/329 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/31 ,  F05D2250/283 ,  F05D2260/30 ,  F05D2300/133 ,  Y02P10/295 ,  Y02T50/671 ,  Y02T50/673

摘要： A load absorbing system that may include a rotor blade retention system (52) is provided. The load absorbing system may include a block (56), a first retainer plate (62A), and a deformable core (54). The block (56) may be selectively positioned alongside a dovetail groove (50). The block (56) may have a first face (66) directed away from the blade root (44) and an axially-spaced second face (68) directed toward the blade root (44). The first retainer plate (62A) may be attached to the second face (68) of the block (56) and axially positioned between the block (56) and the axially-directed surface of the blade root (44). The deformable core (54) may be positioned between the block (56) and the first retainer plate (62A).

公开(公告)号：EP2985366B1

公开(公告)日：2018-01-17

申请号：EP15180607.2

申请日：2015-08-11

申请人： Rolls-Royce Corporation

发明人： Wade, A. Vest

IPC分类号： C25D1/02 ,  C25D1/08 ,  C25D5/56 ,  F01D5/28 ,  F01D11/00

CPC分类号： F01D11/008 ,  C25D1/02 ,  C25D1/08 ,  C25D5/56 ,  F01D5/288 ,  F01D25/28 ,  F05D2220/30 ,  F05D2220/32 ,  F05D2220/3212 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/20 ,  F05D2230/30 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/24 ,  F05D2250/191 ,  F05D2300/177 ,  F05D2300/43 ,  F05D2300/611 ,  Y02T50/671

摘要： According to the present disclosure, an fan annulus filler for use in a fan assembly of a gas turbine engine may include an annulus filler body formed of a polymer. The annulus filler body may include a surface coated with a nanocrystalline coating to form a flow surface.

公开(公告)号：EP3266991A1

公开(公告)日：2018-01-10

申请号：EP17179515.6

申请日：2017-07-04

申请人： Hamilton Sundstrand Corporation

发明人： HARDER, Benjamin T. ,  SLAYTER, Matthew Allen ,  MCMASTERS, Brian ,  NGUYEN, James Vandung ,  WILSON, Dwayne Leon ,  FOX, Paul F. ,  DAVIS, Richard Alan ,  HERGERT, Richard R. ,  ROBERTS, Jeffrey Todd ,  BROWN, Jeff A. ,  WALKER, Daniel Richard

IPC分类号： F01D21/12 ,  F01D25/34 ,  F02C7/277 ,  F02C7/32 ,  F02C7/36 ,  F16H1/46

CPC分类号： F02C7/275 ,  F01D21/12 ,  F01D25/34 ,  F02C7/277 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2260/40311 ,  F05D2260/85 ,  F16H1/46

摘要： According to an aspect, a system for a gas turbine engine (54) includes a reduction gear train (122) operable to drive rotation of a starter gear train (132) that interfaces to an accessory gearbox (70) of the gas turbine engine. The reduction gear train includes a starter interface gear that engages the starter gear train, a core-turning clutch (124) operably connected to the starter interface gear, and a plurality of stacked planetary gear systems (150) operably connected to the core-turning clutch and a core-turning input (128). The system also includes a mounting pad including an interface to couple a core-turning motor (110) to the core-turning input of the reduction gear train.

摘要翻译： 根据一个方面，一种用于燃气涡轮发动机（54）的系统包括减速齿轮系（122），所述减速齿轮系可操作以驱动与所述燃气涡轮发动机的辅助齿轮箱（70）交接的起动机齿轮系（132）的旋转。 减速齿轮系包括接合起动机齿轮系的起动机接口齿轮，可操作地连接到起动机接口齿轮的芯体转动式离合器（124），以及可操作地连接到芯体转动的多个堆叠的行星齿轮系统（150） 离合器和核心转动输入（128）。 该系统还包括安装垫，该安装垫包括用于将核心转动马达（110）连接到减速齿轮系的核心转动输入端的接口。

公开(公告)号：EP3108118A4

公开(公告)日：2018-01-03

申请号：EP15793127

申请日：2015-02-19

申请人： UNITED TECH CORPORATION

发明人： GALLAGHER EDWARD J ,  MONZON BYRON R ,  LIU LING ,  LI LINDA S ,  WHITLOW DARRYL ,  FORD BARRY M

IPC分类号： F01D5/14 ,  F04D29/38

CPC分类号： F04D29/384 ,  F01D5/141 ,  F02C3/04 ,  F02K3/06 ,  F04D29/325 ,  F04D29/388 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/301 ,  F05D2240/303 ,  F05D2240/35 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

摘要： A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a maximum chord length projection that is not in an axial view.

公开(公告)号：EP3108110A4

公开(公告)日：2018-01-03

申请号：EP15752013

申请日：2015-02-19

申请人： UNITED TECH CORPORATION

发明人： GALLAGHER EDWARD J ,  MONZON BYRON R ,  LIU LING ,  LI LINDA S ,  WHITLOW DARRYL ,  FORD BARRY M

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  F01D5/02 ,  F02C3/107 ,  F02K3/00 ,  F05D2200/222 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2240/301 ,  F05D2250/713 ,  F05D2260/40311 ,  Y02T50/672 ,  Y02T50/673

摘要： An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starting at the 0% span position is either zero or positive. The first critical point is in the range of 5-15% span.

公开(公告)号：EP3077288B1

公开(公告)日：2018-01-03

申请号：EP14821745.8

申请日：2014-11-25

申请人： Safran Aircraft Engines

发明人： LEON, Alexandre ,  PAVILLET, Julien ,  SAYN-URPAR, Julien

IPC分类号： B64D29/00

CPC分类号： B64C1/1453 ,  B64D29/00 ,  F01D25/32 ,  F02C7/30 ,  F05D2220/323 ,  G01L7/00 ,  Y10T137/2012

公开(公告)号：EP3071801B1

公开(公告)日：2018-01-03

申请号：EP14809490.7

申请日：2014-11-18

申请人： SAFRAN AIRCRAFT ENGINES

发明人： NOEL, Frédéric ,  DEBRAY, Benoit, Argémiro, Matthieu ,  DE SOUSA, Mario, César ,  GHOSAROSSIAN-PRILLIEUX, Grégory ,  POMMIER, Nicolas

IPC分类号： F01D25/16 ,  F02C7/06

CPC分类号： F01D25/162 ,  F01D25/18 ,  F02C7/06 ,  F05D2220/323 ,  F05D2230/232 ,  F05D2240/50 ,  F16C33/76 ,  F16C35/045 ,  F16C35/067

公开(公告)号：EP3260668A1

公开(公告)日：2017-12-27

申请号：EP17176492.1

申请日：2017-06-16

申请人： United Technologies Corporation

发明人： SUCIU, Gabriel L. ,  McCUNE, Michael E.

IPC分类号： F01D25/20 ,  F02C7/06

CPC分类号： F01D25/20 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2260/98

摘要： A system (68) for a turbine engine (20) includes a first bearing (50, 51, 66), a second bearing (52), a first rotating assembly, a second rotating assembly, a first lubrication circuit (82) and a second lubrication circuit (84). The first rotating assembly includes a first component (44, 46, 47) rotatably supported by the first bearing (50, 51, 66). The second rotating assembly includes a second component (48) rotatably supported by the second bearing (52). The first lubrication circuit includes a first pump (90) and the first bearing (50, 51, 66). The first pump (90) is driven by the first rotating assembly and configured to pump lubricant to the first bearing (50, 51, 66). The second lubrication circuit (84) includes a second pump (102) and the second bearing (52). The second pump (102) is configured to pump lubricant to the second bearing (52). The second lubrication circuit (84) is configured discrete from the first lubrication circuit (82).

摘要翻译： 用于涡轮发动机（20）的系统（68）包括第一轴承（50,51,66），第二轴承（52），第一旋转组件，第二旋转组件，第一润滑回路（82）和 第二润滑回路（84）。 第一旋转组件包括由第一轴承（50,51,66）可旋转地支撑的第一部件（44,46,47）。 第二旋转组件包括由第二轴承（52）可旋转地支撑的第二部件（48）。 第一润滑回路包括第一泵（90）和第一轴承（50,51,66）。 第一泵（90）由第一旋转组件驱动并构造成将润滑剂泵送到第一轴承（50,51,66）。 第二润滑回路（84）包括第二泵（102）和第二轴承（52）。 第二泵（102）构造成将润滑剂泵送到第二轴承（52）。 第二润滑回路（84）与第一润滑回路（82）分离地构造。

公开(公告)号：EP3259125A1

公开(公告)日：2017-12-27

申请号：EP15729270.7

申请日：2015-02-18

申请人： Middle River Aircraft Systems ,  General Electric Company

发明人： ROACH, Andrew Michael ,  CEDAR, Richard David ,  DAVIES, Steven Thomas ,  DEPUY, Timothy Richard ,  HOWARTH, Graham Frank ,  MARTINEZ, Michael Moses

IPC分类号： B32B3/26 ,  F02K1/82 ,  F02C7/045 ,  G10K11/168 ,  G10K11/172 ,  B32B3/12 ,  B64D33/02

CPC分类号： F02C7/045 ,  B32B3/12 ,  B32B3/266 ,  B32B2255/00 ,  B32B2307/102 ,  B32B2605/18 ,  B64D2033/0206 ,  F05D2220/323 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2260/963 ,  F05D2300/603 ,  G10K11/168 ,  G10K11/172 ,  Y02T50/672

摘要： An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perforated sheet supported by the support layer such that perforations are in overlying relationship with the open faces to form paired perforations and cavities that define acoustic resonator cells, and a coating applied to the perforated sheet.