公开(公告)号：US09909503B2

公开(公告)日：2018-03-06

申请号：US14428379

申请日：2013-02-22

Applicant: United Technologies Corporation

Inventor： Keith T. Salamon ,  Matthew A. Turner ,  Christopher M. Quinn

IPC: F02C7/28 ,  F02C3/10 ,  F01D9/02 ,  F01D11/00

CPC classification number: F02C7/28 ,  F01D9/02 ,  F01D11/001 ,  F02C3/10 ,  F05D2220/36

Abstract: A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.

公开(公告)号：US20150275757A1

公开(公告)日：2015-10-01

申请号：US14430709

申请日：2013-03-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew A. Turner ,  Keith T. Salamon ,  Barry M. Ford

IPC: F02C7/04 ,  F02C7/18 ,  B64D33/02

CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0226 ,  F01D17/105 ,  F02C7/18 ,  F02K3/075 ,  F05D2240/12 ,  F05D2250/52 ,  F05D2260/606 ,  Y10T137/0536

Abstract: A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an engine axis and core engine disposed within a core nacelle for driving the fan. A bypass passage is defined between the core nacelle and an outer or fan nacelle. A duct mounted within the core nacelle defines a bleed air flow path for directing bleed air from the core engine into the bypass passage. The bleed air duct includes a plurality of airfoils disposed at a defined chord angle for directing bleed airflow into the bypass passage to minimize disruption to bypass airflow.

Abstract translation: 所公开的燃气涡轮发动机包括：风扇，包括可围绕发动机轴线旋转的多个风扇叶片和设置在用于驱动风扇的核心机舱内的核心发动机。 在核心机舱和外部或风扇机舱之间限定旁路通道。 安装在核心机舱内的管道限定了用于将排气从核心发动机引导到旁路通道中的排气流动路径。 排气管道包括以限定的弦角设置的多个翼型件，用于将排气流引导到旁路通道中以最小化对旁路气流的破坏。

公开(公告)号：US20150226130A1

公开(公告)日：2015-08-13

申请号：US14428379

申请日：2013-02-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Keith T. Salamon ,  Matthew A. Turner ,  Christopher M. Quinn

IPC: F02C7/28 ,  F01D9/02 ,  F02C3/10

CPC classification number: F02C7/28 ,  F01D9/02 ,  F01D11/001 ,  F02C3/10 ,  F05D2220/36

Abstract: A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.

Abstract translation: 燃气涡轮发动机包括核心发动机，联接成由发动机驱动的风扇，围绕铁芯发动机的第一壳体结构和围绕风扇的第二壳体结构。 第一壳体结构和第二壳体结构在其间限定旁路通道。 叶片结构包括在第一壳体结构和第二壳体结构之间径向延伸的翼型件。 密封件构造成控制旁通通道和核心发动机之间的泄漏。