公开(公告)号：EP2900959A4

公开(公告)日：2016-02-10

申请号：EP13842614

申请日：2013-03-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TURNER MATTHEW A ,  SALAMON KEITH T ,  FORD BARRY M

IPC: F01D17/10 ,  F02K3/075

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。