公开(公告)号：US09644535B2

公开(公告)日：2017-05-09

申请号：US14325583

申请日：2014-07-08

Applicant: United Technologies Corporation

Inventor： Steven H. Zysman ,  Wesley K. Lord ,  Robert M. Miller ,  Oliver V. Atassi

IPC: F02C7/04 ,  F02C7/045 ,  B64D33/02

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

Abstract: A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.

公开(公告)号：US20140321970A1

公开(公告)日：2014-10-30

申请号：US14325583

申请日：2014-07-08

Applicant: United Technologies Corporation

Inventor： Steven H. Zysman ,  Wesley K. Lord ,  Robert M. Miller ,  Oliver V. Atassi

IPC: F02C9/18

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

Abstract: A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.

Abstract translation: 用于燃气涡轮发动机系统的机舱包括具有压力侧和吸力侧的壳体。 通道在压力侧和吸力侧之间延伸，以允许从压力侧到吸力侧的气流。 通道包括在压力侧具有入口的第一弯曲部分。 线性部分与第一弯曲部分连接。 第二弯曲部分与线性部分连接并且在吸力侧具有出口。 出口的横截面积小于线性部分的横截面面积。

公开(公告)号：US11480104B2

公开(公告)日：2022-10-25

申请号：US14767396

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Yuan J. Qiu ,  Robert M. Miller ,  Wesley K. Lord ,  Gavin Hendricks

IPC: F02C7/04 ,  F02K3/06 ,  F01D5/02 ,  F01D17/10 ,  F01D25/24 ,  F02C3/04 ,  B64D33/02

Abstract: A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.

公开(公告)号：US20160003145A1

公开(公告)日：2016-01-07

申请号：US14767396

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Yuan J. Qiu ,  Robert M. Miller ,  Wesley K. Lord ,  Gavin Hendricks

IPC: F02C7/04 ,  F01D17/10 ,  F01D25/24 ,  F02C3/04 ,  F01D5/02

Abstract: A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.

Abstract translation: 一种燃气涡轮发动机，其包括在其之间径向提供旁通流动路径的风扇机舱和核心机舱。 风扇机舱具有包括喉部的入口。 入口具有入口最前面的点。 风扇布置在旁路流动路径中并可围绕轴线旋转。 风扇具有从入口最前端凹入的前缘，其轴向方向上的入口长度。 旋转器的旋转器长度从最远点到最前沿。 旋转器长度与入口长度的比例等于或大于约0.5。