公开(公告)号：EP3483059A1

公开(公告)日：2019-05-15

申请号：EP18202178.2

申请日：2018-10-23

Applicant: Bell Helicopter Textron Inc.

Inventor： GRONINGA, Kirk L. ,  STAMPS, Frank B. ,  ROBERTSON, Daniel B. ,  LOUIS, Matthew E.

IPC: B64C15/12 ,  B64C27/28 ,  B64C29/00 ,  B64C39/06 ,  B64C39/08

Abstract: In one embodiment, a tiltrotor aircraft (100, 200, 300, 400, 500) may comprise a fuselage (102, 202, 302, 402, 502); a biplane wing (120, 220, 320, 420, 520, 530) coupled to the fuselage (102, 202, 302, 402, 502), wherein the biplane wing (120, 220, 320, 420, 520, 530) comprises an upper wing structure (121a-b, 221a-b, 231a-b, 241a-b, 251a-b, 321, 331, 341, 421a-b) and a lower wing structure (122a-b, 222a-b, 232a-b, 242a-b, 252a-b, 322, 332, 342, 422a-b); a plurality of tiltrotors (110a-b, 210a-b, 410a-b) coupled to the biplane wing (120, 220, 320, 420, 520, 530); and at least one engine to power the plurality of tiltrotors (110a-b, 210a-b, 410a-b).

公开(公告)号：EP3406521A1

公开(公告)日：2018-11-28

申请号：EP17185863.2

申请日：2017-08-11

Applicant: Bell Helicopter Textron Inc.

Inventor： CARR, Matthew R. ,  LOUIS, Matthew E. ,  GRONINGA, Kirk L. ,  ROBERTSON, Daniel B. ,  STAMPS, Frank B. ,  BRAND, Albert G. ,  SINUSAS, Eric A.

IPC: B64C27/82

CPC classification number: B64C27/82 ,  B64C2027/8245 ,  B64C2027/8254 ,  F04D17/16 ,  F04D29/462

Abstract: In one embodiment, a rotorcraft (100) comprises a fuselage (110), a tail boom (202), a rotor system (120), and a centrifugal blower system (200). The centrifugal blower system (200) comprises a centrifugal blower (204) configured to generate thrust using an airflow, wherein the centrifugal blower (204) is located within the tail boom (202). The centrifugal blower system (200) also comprises a plurality of ducts configured to control the thrust generated by the centrifugal blower (204), wherein the plurality of ducts is located on a portion of the tail boom (202) surrounding the centrifugal blower (204), and wherein the plurality of ducts comprises one or more adjustable ducts configured to vary a size of an associated duct opening.

公开(公告)号：EP3406521B1

公开(公告)日：2019-06-19

申请号：EP17185863.2

申请日：2017-08-11

Applicant: Bell Helicopter Textron Inc.

Inventor： CARR, Matthew R. ,  LOUIS, Matthew E. ,  GRONINGA, Kirk L. ,  ROBERTSON, Daniel B. ,  STAMPS, Frank B. ,  BRAND, Albert G. ,  SINUSAS, Eric A.

IPC: B64C27/82

公开(公告)号：EP3281865A1

公开(公告)日：2018-02-14

申请号：EP17185544.8

申请日：2017-08-09

Applicant: Bell Helicopter Textron Inc.

Inventor： GRONINGA, Kirk L. ,  ROBERTSON, Daniel B. ,  LOUIS, Matthew E.

IPC: B64C23/02 ,  B64C29/00 ,  B64C39/00

CPC classification number: B64C29/0033 ,  B64C3/32 ,  B64C15/12 ,  B64C23/02 ,  B64C39/005 ,  B64D27/24 ,  B64D2027/026 ,  F04D17/04 ,  F04D29/282 ,  F04D29/287

Abstract: A variable thrust cross-flow fan system (30) for an aircraft (10) including a rotatable wing member (60) having a first housing member (60a); an actuator assembly (71) operably coupled to the first housing member (60a); and a variable thrust cross-flow fan assembly (70) including a first and second driver plates (204, 206) having a plurality of blades (210a-g) rotatably mounted therebetween. The plurality of blades (210a-g) has a circular path of travel when rotating and includes a control assembly coupled to the plurality of blades (210a-g) to generate a variable thrust force. The control assembly includes a control cam (230) that is substantially non-rotatable relative to the first and second driver plates (204, 206) and a hinge member (831) that is fixedly connected to the control cam (230) and to the first housing member (60a) at a hinge axis. Rotation of the first housing member (60a) by the actuator assembly (71) imparts rotation of the control cam (230) about the hinge axis, thereby changing the direction of the variable thrust force.

Abstract translation: 1。一种用于飞机（10）的可变推力横流风扇系统（30），所述飞机（10）包括具有第一壳体构件（60a）的可旋转翼构件（60） 致动器组件（71），其可操作地联接到所述第一壳体构件（60a）;致动器组件 以及包括第一和第二驱动器板（204,206）的可变推力横流风扇组件（70），所述第一和第二驱动器板具有可旋转地安装在其间的多个叶片（210a-g）。 多个叶片（210a-g）在旋转时具有圆形的行进路径，并且包括联接到多个叶片（210a-g）以产生可变推力的控制组件。 控制组件包括相对于第一和第二驱动器板（204,206）基本上不可旋转的控制凸轮（230）和固定地连接到控制凸轮（230）和铰链构件（831）的铰链构件 第一壳体构件（60a）处于铰链轴线处。 通过致动器组件（71）的第一壳体构件（60a）的旋转引起控制凸轮（230）围绕铰链轴线旋转，从而改变可变推力的方向。

公开(公告)号：EP3281865B1

公开(公告)日：2018-10-17

申请号：EP17185544.8

申请日：2017-08-09

Applicant: Bell Helicopter Textron Inc.

Inventor： GRONINGA, Kirk L. ,  ROBERTSON, Daniel B. ,  LOUIS, Matthew E.

IPC: B64C3/32 ,  B64C15/12 ,  B64D27/24 ,  F04D17/04 ,  F04D29/28 ,  B64D27/02 ,  B64C23/02 ,  B64C29/00 ,  B64C39/00

CPC classification number: B64C29/0033 ,  B64C3/32 ,  B64C15/12 ,  B64C23/02 ,  B64C39/005 ,  B64D27/24 ,  B64D2027/026 ,  F04D17/04 ,  F04D29/282 ,  F04D29/287

Abstract: A variable thrust cross-flow fan system (30) for an aircraft (10) including a rotatable wing member (60) having a first housing member (60a); an actuator assembly (71) operably coupled to the first housing member (60a); and a variable thrust cross-flow fan assembly (70) including a first and second driver plates (204, 206) having a plurality of blades (210a-g) rotatably mounted therebetween. The plurality of blades (210a-g) has a circular path of travel when rotating and includes a control assembly coupled to the plurality of blades (210a-g) to generate a variable thrust force. The control assembly includes a control cam (230) that is substantially non-rotatable relative to the first and second driver plates (204, 206) and a hinge member (831) that is fixedly connected to the control cam (230) and to the first housing member (60a) at a hinge axis. Rotation of the first housing member (60a) by the actuator assembly (71) imparts rotation of the control cam (230) about the hinge axis, thereby changing the direction of the variable thrust force.

公开(公告)号：EP3281863A1

公开(公告)日：2018-02-14

申请号：EP17185578.6

申请日：2017-08-09

Applicant: Bell Helicopter Textron Inc.

Inventor： GRONINGA, Kirk L. ,  ROBERTSON, Daniel B. ,  LOUIS, Matthew E.

IPC: B64C11/00 ,  B64C27/82 ,  B64C29/00 ,  B64C39/00 ,  B64C23/02 ,  B64C23/08

CPC classification number: B64C27/82 ,  B64C11/006 ,  B64C23/02 ,  B64C27/06 ,  B64C39/006 ,  B64C2027/8218 ,  B64C2027/8227 ,  B64C2027/8254 ,  F04D17/04 ,  F04D25/166 ,  F04D27/002 ,  F04D29/4226

Abstract: In one aspect, there is provided an aircraft (10), including a fuselage (12) having a longitudinal axis extending from a front portion through an aft portion (14); first and second tail members (36, 38) extending from the aft portion (14); a first cross-flow fan system (32) rotatably mounted to the first tail member; and a second cross-flow fan system (34) rotatably mounted to the second tail member. The first and second cross-flow fan systems are configured to provide a forward thrust vector and an anti-torque vector on the aircraft. The first and second cross-flow fan systems can have a rotational axis (R1, R2) oriented generally vertically. In another aspect, there is an aircraft including a fuselage having a front portion and a tail portion; and a cross-flow fan system supported by the tail portion. Embodiments include a cross-flow fan system retrofittable onto an aircraft and methods for retrofitting an aircraft with a cross-flow fan system.

Abstract translation: 在一个方面中，提供了一种飞机（10），其包括机身（12），所述机身具有从前部通过后部（14）延伸的纵向轴线; 从所述后部（14）延伸的第一和第二尾部构件（36,38）; 第一横流风扇系统（32），其可旋转地安装到第一尾部构件; 和可旋转地安装到第二尾部构件的第二横流风扇系统（34）。 第一横流风扇系统和第二横流风扇系统构造成在飞机上提供前向推力矢量和反转矩矢量。 第一横流风扇系统和第二横流风扇系统可以具有大致竖直定向的旋转轴线（R1，R2）。 另一方面，有一种飞机，其包括具有前部和尾部的机身; 以及由尾部支撑的横流风扇系统。 实施例包括可改装到飞机上的横流式风扇系统以及用横流式风扇系统改装飞机的方法。