公开(公告)号：WO2014099634A3

公开(公告)日：2014-11-27

申请号：PCT/US2013074847

申请日：2013-12-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  WEISSE MICHAEL A ,  ZYSMAN STEVEN H

IPC: F01D5/12 ,  F01D5/22 ,  F01D7/02 ,  F04D29/34 ,  F04D29/38

CPC classification number: F01D5/225 ,  F04D25/028 ,  F04D29/324 ,  F04D29/666 ,  F04D29/668 ,  F05D2220/36 ,  F05D2250/14 ,  Y02T50/671 ,  Y02T50/673

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis. Each of the plurality of fan blades includes a mid-span shroud and a speed change device in communication with the fan.

Abstract translation: 除了别的之外，根据本公开的示例性方面的燃气涡轮发动机包括风扇部分，该风扇部分包括具有多个绕轴线可旋转的风扇叶片的风扇。 多个风扇叶片中的每一个包括中跨度护罩和与风扇连通的变速装置。

公开(公告)号：WO2014077922A3

公开(公告)日：2014-07-31

申请号：PCT/US2013055935

申请日：2013-08-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZYSMAN STEVEN H

IPC: F02C7/04 ,  B64D33/00

CPC classification number: B64D33/00 ,  B64D29/00 ,  B64D33/08 ,  B64D2033/024 ,  F02C7/04 ,  F02C7/12 ,  F02C9/18 ,  Y02T50/675 ,  Y10T137/0536

Abstract: A scoop inlet for use in a gas turbine engine nacelle has a scoop inlet, and a tab extending forwardly of the scoop inlet. The scoop communicates with a downstream flowpath. The tab has at least one opening at a location upstream of the scoop inlet. A nacelle and a gas turbine engine are also disclosed.

Abstract translation: 用于燃气轮机发动机舱的铲斗入口具有铲斗入口和从铲斗入口向前延伸的翼片。 瓢与下游流路相通。 标签在舀勺入口的上游位置至少有一个开口。 还公开了机舱和燃气涡轮发动机。

公开(公告)号：WO2013165523A3

公开(公告)日：2014-01-23

申请号：PCT/US2013026244

申请日：2013-02-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZYSMAN STEVEN H ,  MIGLIARO JR EDWARD F

IPC: F02C7/042 ,  F01D17/00

CPC classification number: F02K1/72 ,  F02K1/763 ,  F05D2250/73 ,  F05D2260/50 ,  Y10T29/49234

Abstract: A gas turbine engine includes an engine core outer casing and a fan nacelle spaced radially outwardly relative to the engine core outer casing to define a bypass duct. A plurality of drag links is used to pivot blocker doors into a flow blocking position in the bypass duct when a thrust reverser is deployed. The plurality of drag links is located within the bypass duct in an area of non-uniform flow defined by a plurality of local airflow angles. Each drag link is individually configured to align with one of the local flow angles.

Abstract translation: 燃气涡轮发动机包括发动机芯外壳和相对于发动机芯外壳径向向外间隔开的风扇机舱，以限定旁路管道。 当部署推力反向器时，多个牵引连杆用于将阻挡门枢转到旁通管道中的阻流位置。 多个牵引连杆位于旁通管道内的由多个局部气流角限定的不均匀流动区域内。 每个拖动链接单独配置为与一个局部流动角度对齐。

公开(公告)号：WO2008045051A3

公开(公告)日：2009-06-18

申请号：PCT/US2006039797

申请日：2006-10-12

Applicant: UNITED TECHNOLOGIES CORP ,  ZYSMAN STEVEN H ,  LORD WESLEY K ,  MILLER ROBERT M ,  ATASSI OLIVER V

Inventor： ZYSMAN STEVEN H ,  LORD WESLEY K ,  MILLER ROBERT M ,  ATASSI OLIVER V

IPC: F02C7/04

CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0226 ,  F02C7/045 ,  F05D2250/324 ,  F05D2250/71 ,  F05D2270/17 ,  Y10T137/0536

Abstract: A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle.

Abstract translation: 燃气涡轮发动机系统包括具有压力侧和吸力侧的机舱。 通道在压力侧和吸力侧之间延伸，允许从压力侧到吸力侧的气流。 通道在机舱上接收湍流气流，以在通道后面的机舱上方产生层流气流，从而减少机舱上的阻力。