公开(公告)号：US20160122005A1

公开(公告)日：2016-05-05

申请号：US14203735

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Razvan Virgil Florea ,  William T. Cousins ,  Thomas G. Tillman ,  David J. Arend ,  John D. Wolter

IPC: B64C21/04 ,  B64C1/16 ,  B64D29/04 ,  B64C39/10

CPC classification number: B64C21/04 ,  B64C1/16 ,  B64C39/10 ,  B64C2039/105 ,  B64C2230/04 ,  B64D27/18 ,  B64D27/20 ,  B64D29/04 ,  B64D33/02 ,  B64D2033/0226 ,  B64D2033/0253 ,  Y02T50/166

Abstract: A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer.

Abstract translation: 混合翼飞机具有嵌入到混合翼飞机的主体中的发动机。 嵌入式发动机具有接收在机舱内的风扇。 飞机的主体在风扇的圆周部分上提供了一个边界层。 系统提供额外的空气，以纠正边界层引起的风扇稳定性问题。

公开(公告)号：US20150284072A1

公开(公告)日：2015-10-08

申请号：US14629558

申请日：2015-02-24

Applicant: United Technologies Corporation

Inventor： Alan B. Minick ,  William T. Cousins

IPC: B64C23/00

CPC classification number: B64C23/005 ,  B64C11/18 ,  B64C2230/12 ,  Y02T50/166

Abstract: A method for controlling a boundary layer over a vehicle surface includes generating an ionic wind using a network of emitters and receivers. An external fluid is propelled with the ionic wind over the vehicle surface. The strength of the ionic wind is controlled to adjust the boundary layer thickness.

Abstract translation: 用于控制车辆表面上的边界层的方法包括使用发射器和接收器的网络产生离子风。 外部流体以离子风在车辆表面上推进。 控制离子风的强度来调节边界层的厚度。

公开(公告)号：US10415505B2

公开(公告)日：2019-09-17

申请号：US14911577

申请日：2014-04-17

Applicant: United Technologies Corporation

Inventor： Razvan Virgil Florea ,  Thomas G. Tillman ,  William T. Cousins

IPC: F02C7/04 ,  F02K3/06 ,  F01D5/14 ,  F01D5/20 ,  F02C7/045 ,  F04D29/52 ,  F04D27/02 ,  F04D29/32 ,  F04D29/54 ,  F02C3/04

Abstract: A gas turbine engine propulsion system and method of assembling such is disclosed. The gas turbine engine propulsion system comprises a gas turbine engine that includes a fan flow path. The fan flow path may extend from the fan inlet to the rear exhaust outlet of the bypass flow path. A portion of the fan flow path, proximal to the fan, is non-axisymmetric. The non-axisymmetric portion may be upstream or downstream of the fan.

公开(公告)号：US11498660B2

公开(公告)日：2022-11-15

申请号：US16167968

申请日：2018-10-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Razvan Virgil Florea ,  William T. Cousins ,  Thomas G. Tillman ,  David J. Arend ,  John D. Wolter

IPC: B64C21/04 ,  B64D29/04 ,  B64C21/02 ,  B64C21/08 ,  B64D27/20 ,  B64C39/10 ,  B64C1/16 ,  B64D33/02

Abstract: A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer.

公开(公告)号：US20190055006A1

公开(公告)日：2019-02-21

申请号：US16167968

申请日：2018-10-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Razvan Virgil Florea ,  William T. Cousins ,  Thomas G. Tillman ,  David J. Arend ,  John D. Wolter

IPC: B64C21/04 ,  B64D33/02 ,  B64D27/20 ,  B64C39/10 ,  B64C1/16 ,  B64D29/04

Abstract: A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer.