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：US20150044052A1

公开(公告)日：2015-02-12

申请号：US14079688

申请日：2013-11-14

Applicant: United Technologies Corporation

Inventor： Edwin M. Worth ,  Thomas G. Tillman ,  Frederick M. Schwarz

IPC: F01D5/18 ,  F01D5/22

CPC classification number: F01D5/18 ,  F01D5/141 ,  F01D5/145 ,  F01D5/147 ,  F01D5/225 ,  F01D5/28 ,  F02C7/36 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/31 ,  F05D2250/181 ,  F05D2250/311 ,  F05D2250/321 ,  F05D2250/322 ,  F05D2250/62 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/516 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49336

Abstract: A fan blade comprises a main body having an airfoil extending between a leading edge and a trailing edge. The fan blade has at least one of a channel closed by a cover, and an end cap covering at least one of the leading and trailing edges. At least one of a cover and an end cap has a pair of opposed ends. A step is defined extending from at least one of a suction wall and a pressure wall of the airfoil, to an outer surface of the one of a cover and an end cap at one of the opposed ends, and the step being less than or equal to about 0.010 inch (0.0254 centimeter) in dimension.

Abstract translation: 风扇叶片包括具有在前缘和后缘之间延伸的翼型件的主体。 风扇叶片具有由盖封闭的通道和覆盖前缘和后缘中的至少一个的端盖中的至少一个。 盖和端盖中的至少一个具有一对相对的端部。 从机翼的吸力壁和压力壁中的至少一个到相对端中的一个的盖和端盖中的一个的外表面延伸的步骤被限定，该步骤小于或等于 到约0.010英寸（0.0254厘米）的尺寸。

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.

公开(公告)号：US20150226156A1

公开(公告)日：2015-08-13

申请号：US14295566

申请日：2014-06-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas G. Tillman ,  Wesley K. Lord

IPC: F02K1/12 ,  F02K3/00

CPC classification number: F02K1/52 ,  B64D29/04 ,  F02K1/002 ,  F02K1/12 ,  F02K3/06 ,  F05D2220/36 ,  F05D2250/73

Abstract: A fan section for an engine has a fan which rotates about an axis, the fan has an inlet for ingesting ambient air, and a non-axisymmetric nozzle for providing the fan with non-uniform back pressure.

Abstract translation: 用于发动机的风扇部分具有围绕轴线旋转的风扇，风扇具有用于摄取环境空气的入口和用于为风扇提供不均匀背压的非轴对称喷嘴。

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.