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：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.