公开(公告)号：US20160194968A1

公开(公告)日：2016-07-07

申请号：US14911889

申请日：2014-08-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael Joseph Murphy ,  Oleg Petrenko

IPC: F01D9/02 ,  F02C7/36 ,  F02C3/04 ,  F01D25/24 ,  F02K3/04

Abstract: A turbofan engine includes a fan section. A core engine section drives the fan section. An outer nacelle surrounds the fan section and defines a radially outer surface of a fan duct. An inner nacelle surrounds the core engine section and defines a radially inner surface of the fan duct. A nozzle is disposed at a terminal end of the outer nacelle that defines an exit area for bypass air flow through the fan duct. The nozzle includes a convergent portion forward of a divergent portion and a turning angle for the divergent portion greater than about 12 degrees. A nacelle assembly and method are also disclosed.

Abstract translation: 涡扇发动机包括风扇部分。 核心引擎部分驱动风扇部分。 外部机舱围绕风扇部分并且限定了风扇导管的径向外表面。 内部机舱围绕核心发动机部分并且限定风扇管道的径向内表面。 喷嘴设置在外部机舱的终端处，其限定用于旁路气流通过风扇管道的出口区域。 喷嘴包括发散部分前方的收敛部分和大于约12度的发散部分的转动角度。 还公开了一种机舱组件和方法。

公开(公告)号：US20140237990A1

公开(公告)日：2014-08-28

申请号：US13834123

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Oliver V. Atassi ,  Oleg Petrenko

IPC: F02K1/82

CPC classification number: F02K1/15 ,  F02C3/04 ,  F02C7/36 ,  F02K1/06 ,  F02K1/82 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2260/81 ,  F05D2300/173 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nacelle is arranged around the fan, and a bypass passage extends between the fan nacelle and the core engine. A variable area fan nozzle (VAFN) extends at least partially around the central axis and defines an exit area of the bypass passage. The VAFN is selectively movable to vary the exit area. The VAFN includes a body that defines an airfoil cross-section shape. The VAFN includes a wall that has a mechanical property distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN.

Abstract translation: 燃气涡轮发动机包括至少具有压缩机部分，燃烧器部分和沿中心轴线布置的涡轮部分的核心发动机。 风扇被联接以由涡轮部分驱动。 风扇周围布置有风扇机舱，并且旁通通道在风扇机舱和核心发动机之间延伸。 可变区域风扇喷嘴（VAFN）至少部分地围绕中心轴延伸并且限定旁路通道的出口区域。 VAFN选择性地可移动以改变出口区域。 VAFN包括限定翼型横截面形状的主体。 VAFN包括具有根据VAFN的颤振特性的计算机模拟振动分布的机械特性分布的壁。