公开(公告)号：US20150135678A1

公开(公告)日：2015-05-21

申请号：US14609800

申请日：2015-01-30

Applicant: United Technologies Corporation

Inventor： Jonathan Gilson ,  Dennis Cicon ,  Oliver V. Atassi

IPC: F02K1/09 ,  F02K1/00 ,  F02K1/82

CPC classification number: F02K1/09 ,  F02K1/002 ,  F02K1/827 ,  F05D2260/96

Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path. A variable area fan nozzle is in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section. The second fan nacelle section is axially movable relative to the first fan nacelle section to define an auxiliary port at a non-closed position to vary a fan nozzle exit area and adjust fan bypass airflow. The second fan nacelle section includes an acoustic system that has an acoustic impedance located on a radially outer surface.

Abstract translation: 用于高旁路燃气涡轮发动机的机舱组件包括围绕发动机中心线轴线限定的核心机舱。 风扇机舱至少部分地安装在核心机舱周围以限定风扇旁路流动路径。 可变区域风扇喷嘴与风扇旁路流路连通。 可变区域风扇喷嘴具有第一风扇机舱部分和第二风扇机舱部分。 第二风扇机舱部分可相对于第一风扇机舱部分轴向移动，以在非闭合位置限定辅助端口以改变风扇喷嘴出口区域并调节风扇旁路气流。 第二风扇机舱部分包括具有位于径向外表面上的声阻抗的声学系统。

公开(公告)号：US20140366554A1

公开(公告)日：2014-12-18

申请号：US14472849

申请日：2014-08-29

Applicant: United Technologies Corporation

Inventor： Jonathan Gilson ,  Andre M. Hall ,  Oliver V. Atassi ,  Ramons A. Reba

IPC: F02K1/09 ,  F02K3/075

CPC classification number: F02K1/09 ,  F02K1/827 ,  F02K3/06 ,  F02K3/075 ,  Y02T50/672

Abstract: A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path, and a variable area fan nozzle in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section downstream of the first fan nacelle section. The first fan nacelle section and the second fan nacelle section are axially movable relative to one another to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The auxiliary port is defined between the first fan nacelle section and the second fan nacelle section. The first fan nacelle section comprises a first acoustic system which provides an acoustic impedance configured to attenuate a noise characterized by a leading edge of the second fan nacelle section. The first acoustic system is defined at least in part within a trailing edge region of the first fan nacelle section. A method of reducing a total effective perceived noise level of a gas turbine engine with a variable area fan nozzle is also disclosed.

Abstract translation: 根据本公开的示例性方面的机舱组件尤其包括至少部分地围绕核心发动机限定的核心机舱，至少部分地围绕所述核心机舱安装的风扇机舱，以限定风扇旁路流动路径，以及 与风扇旁路流路连通的可变区域风扇喷嘴。 可变区域风扇喷嘴具有第一风扇机舱部分和第一风扇机舱部分下游的第二风扇机舱部分。 第一风扇机舱部分和第二风扇机舱部分可相对于彼此轴向移动以限定辅助端口以改变风扇喷嘴出口区域并调节风扇旁路气流。 辅助端口定义在第一风扇机舱部分和第二风扇机舱部分之间。 第一风扇机舱部分包括第一声学系统，其提供被配置为衰减由第二风扇机舱部分的前缘表征的噪声的声阻抗。 第一声​​学系统至少部分地限定在第一风扇机舱部分的后缘区域内。 还公开了一种用可变面积风扇喷嘴降低燃气涡轮发动机的总有效感知噪声水平的方法。

公开(公告)号：US10371173B2

公开(公告)日：2019-08-06

申请号：US14706259

申请日：2015-05-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michaela M. Logue ,  Oliver V. Atassi

IPC: F01D25/04 ,  F04D29/66 ,  F02K1/08 ,  F02K1/82 ,  F02K3/06 ,  F02C7/045 ,  F04D29/52 ,  F04D29/54 ,  F01D25/16

Abstract: A gas turbine engine is provided having a fan case and a translating sleeve positioned downstream from the fan case. A flow channel extends between the fan case and the translating sleeve. The flow channel includes an inner diameter and an outer diameter. A structural guide vane is positioned within the flow channel and extends from the inner diameter to the outer diameter. A liner is positioned between an aft end of the fan case and an aft end of the translating sleeve to reduce vibratory stress on the structural guide vane.

公开(公告)号：US10287987B2

公开(公告)日：2019-05-14

申请号：US14204983

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： Constantine Baltas ,  Oliver V. Atassi

IPC: F02C7/24 ,  F02K1/09 ,  F02K3/06

Abstract: A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region. A thickness of the leading edge region is based on a thickness of a wake in the airflow produced by the first airflow structure when the airflow passes between the first airflow structure and the second airflow structure.

公开(公告)号：US20140348630A1

公开(公告)日：2014-11-27

申请号：US14204983

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： Constantine Baltas ,  Oliver V. Atassi

IPC: F02C7/24 ,  F01D9/02

CPC classification number: F02C7/24 ,  F02K1/09 ,  F02K3/06 ,  F05D2260/96

Abstract: A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region. A thickness of the leading edge region is based on a thickness of a wake in the airflow produced by the first airflow structure when the airflow passes between the first airflow structure and the second airflow structure.

Abstract translation: 燃气涡轮发动机包括第一气流结构和设置在第一气流结构后面的第二气流结构。 第二气流结构包括前缘区域。 前缘区域的厚度基于当第一气流结构和第二气流结构之间的气流通过时由第一气流结构产生的气流中的尾流的厚度。

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。