公开(公告)号：US20140117152A1

公开(公告)日：2014-05-01

申请号：US13662879

申请日：2012-10-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph B. Staubach ,  Adam Joseph Suydam

IPC: B64D27/14 ,  F02K3/02

CPC classification number: B64D27/14 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles, with each of the nacelles receiving a fan rotor. The fan rotor is fixed to rotate with a tip turbine mounted at a radially outer location of the fan rotor, with the tip turbine being in the path of gases from the manifold. An aircraft is also disclosed.

Abstract translation: 燃气涡轮发动机具有并入涡轮机的核心发动机和位于涡轮机下游的歧管。 歧管将涡轮下游的气体输送到至少两个机舱中，其中每个机舱都接收风扇转子。 风扇转子被固定以与安装在风扇转子的径向外部位置处的尖端涡轮一起旋转，其中尖端涡轮机处于来自歧管的气体的路径中。 还披露了一架飞机。

公开(公告)号：US09822731B2

公开(公告)日：2017-11-21

申请号：US14671158

申请日：2015-03-27

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Adam Joseph Suydam ,  Christopher G. Hugill

IPC: F02K3/075 ,  F02K3/11 ,  F02K1/00 ,  F02K3/00 ,  B64D31/06 ,  F02K1/17 ,  F02C9/28 ,  F02C9/54

CPC classification number: F02K1/17 ,  F02C9/28 ,  F02C9/54 ,  F02K3/11

Abstract: A method to reduce aerodynamic drag of a engine exhaust/engine nozzle includes collecting data that is indicative of an instant flight condition, entering the data into a decision algorithm that, based on the data, outputs at least first and second drag control parameters corresponding, respectively, to an angle of one or more variable area turbines of a turbine engine and a position of a variable area exhaust nozzle of the turbine engine, and adjusting the angle of the one or more variable area turbines and the position of the variable area exhaust nozzle according to, respectively, the first and second drag control parameters to reduce aerodynamic drag of an engine exhaust/engine nozzle of the turbine engine.

公开(公告)号：US20160280385A1

公开(公告)日：2016-09-29

申请号：US14671158

申请日：2015-03-27

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Adam Joseph Suydam ,  Christopher G. Hugill

IPC: B64D31/06

CPC classification number: F02K1/17 ,  F02C9/28 ,  F02C9/54 ,  F02K3/11

Abstract: A method to reduce aerodynamic drag of a engine exhaust/engine nozzle includes collecting data that is indicative of an instant flight condition, entering the data into a decision algorithm that, based on the data, outputs at least first and second drag control parameters corresponding, respectively, to an angle of one or more variable area turbines of a turbine engine and a position of a variable area exhaust nozzle of the turbine engine, and adjusting the angle of the one or more variable area turbines and the position of the variable area exhaust nozzle according to, respectively, the first and second drag control parameters to reduce aerodynamic drag of an engine exhaust/engine nozzle of the turbine engine.

Abstract translation: 一种减少发动机排气/发动机喷嘴的气动阻力的方法包括：收集指示瞬时飞行状态的数据，将数据输入到基于该数据的至少第一和第二拖动控制参数对应的判定算法， 分别与涡轮发动机的一个或多个可变区域涡轮机的角度以及涡轮发动机的可变区域排气喷嘴的位置的角度，并且调节一个或多个可变区域涡轮机的角度和可变区域排气口的位置 喷嘴分别根据第一和第二拖动控制参数，以减少涡轮发动机的发动机排气/发动机喷嘴的气动阻力。