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公开(公告)号：US11091175B2
公开(公告)日：2021-08-17
申请号：US16719919
申请日：2019-12-18
申请人： The Boeing Company
摘要： A vacuum transport tube vehicle for evacuating a vacuum transport tube has a first end, a second end, and a body comprising a piston head. The vehicle has a blade-actuator assembly, comprising a circumferential blade member sealed to the piston head and having a blade perimeter portion defining a first end outer surface forming an annular gap with an inner surface of the vacuum transport tube. The vehicle further includes a plurality of blade segment actuators arranged circumferentially around the piston perimeter portion and configured to actively adjust a radial position of the blade member at the corresponding blade circumferential locations in a manner accommodating non-uniformities in an inner surface profile of the vacuum transport tube, and maintaining the annular gap at a substantially constant and relatively short gap distance during movement of the vehicle through the vacuum transport tube.
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公开(公告)号：US20190128214A1
公开(公告)日：2019-05-02
申请号：US15801105
申请日：2017-11-01
申请人： The Boeing Company
发明人： John C. Vassberg , Mark DeHaan , Dino Roman
摘要： An ultrashort nacelle configuration employs a fan cowl having an exit plane and a serrated trailing edge. A variable pitch fan is housed within the fan cowl. The variable pitch fan has a reverse thrust position inducing a reverse flow through the exit plane and into the fan cowl. The serrated trailing edge forms a plurality of vortex generators configured to induce vortices in the reverse flow.
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公开(公告)号：US20170203830A1
公开(公告)日：2017-07-20
申请号：US15477940
申请日：2017-04-03
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
CPC分类号： B64C5/10 , B64C3/58 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet is configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing.
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公开(公告)号：US09340281B2
公开(公告)日：2016-05-17
申请号：US14448479
申请日：2014-07-31
申请人： The Boeing Company
CPC分类号： B64C23/06 , B64C1/0009 , B64C19/00 , B64C21/02 , B64C2230/08 , B64C2230/20 , B64C2230/22 , B64C2230/24 , F15D1/0025 , Y02T50/12 , Y02T50/162 , Y02T50/166
摘要： A vortex generator may include a depression in an aerodynamic surface, and a vortex generator leading edge located in the depression. The vortex generator leading edge may include a leading edge upper surface. The leading edge upper surface may be positioned at or below a tangent line defined at a location along the aerodynamic surface upstream of the depression relative to an oncoming local flow.
摘要翻译： 涡流发生器可以包括空气动力学表面中的凹陷和位于凹陷中的涡流发生器前缘。 涡流发生器前缘可以包括前缘上表面。 前缘上表面可以定位在相对于迎面而来的局部流动沿着凹陷上游的空气动力学表面的位置处的切线处或下方。
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公开(公告)号：US20160009372A1
公开(公告)日：2016-01-14
申请号：US14196461
申请日：2014-03-04
申请人： The Boeing Company
摘要： An airfoil may include a leading edge and a shape control mechanism. The leading edge may include a flexible leading edge skin having a first end, a second end, and an arc length defined therebetween. The shape control mechanism may be attached to the flexible leading edge skin at a plurality of support locations and may transition the flexible leading edge skin from a first shape having a first curvature profile to a second shape having a second curvature profile different than the first curvature profile without a change in the arc length.
摘要翻译： 翼型件可以包括前缘和形状控制机构。 前缘可以包括柔性前缘皮肤，其具有第一端部，第二端部和在其间限定的弧形长度。 形状控制机构可以在多个支撑位置处附接到柔性前缘皮肤，并且可以将柔性前缘皮肤从具有第一曲率轮廓的第一形状转变到具有不同于第一曲率的第二曲率轮廓的第二形状 轮廓没有弧长变化。
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公开(公告)号：US10538254B2
公开(公告)日：2020-01-21
申请号：US15476399
申请日：2017-03-31
申请人： The Boeing Company
摘要： A vacuum transport tube vehicle, system, and method for evacuating a vacuum transport tube are provided. The vehicle has a first end having a first end outer surface. An annular gap is formed between the first end outer surface and an inner surface of the vacuum transport tube. The vehicle has a second end having a second end outer diameter, and a body in the form of a piston with a structural framework. The vehicle has an orifice extending from a first inlet portion in the first end to a second outlet portion of the vehicle. The vehicle has a drive assembly coupled to the body, and a power system. The vehicle evacuates the vacuum transport tube by reducing pressure within the tube with each successive vehicle pass through the tube, until a desired pressure is obtained and a vacuum is created in the interior of the tube.
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公开(公告)号：US20200003063A1
公开(公告)日：2020-01-02
申请号：US16022670
申请日：2018-06-28
申请人： The Boeing Company
发明人： John C. Vassberg , Mark Dehaan , Dino L. Roman
摘要： There is provided a turbofan engine for an aircraft. The turbofan engine has a core with a fan cowl and a variable pitch fan (VPF) configured to only rotate in a first rotation direction. The VPF has a plurality of fan blades each configured to over-pitch to an over-pitch position relative to a feathered position. The turbofan engine has outer guide vanes (OGVs) axially disposed downstream of the VPF, and has a rotation control device to prevent the VPF from rotating in a second rotation direction opposite the first rotation direction, during an engine out (EO) condition of the turbofan engine. When the VPF is prevented from rotating during the EO condition, the fan blades are over-pitched to the over-pitch position relative to the feathered position, to achieve no or minimal air flow separation about the OGVs, and to reduce drag of the turbofan engine during the EO condition.
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公开(公告)号：US09637226B2
公开(公告)日：2017-05-02
申请号：US15259509
申请日：2016-09-08
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet is configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing.
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公开(公告)号：US20160068259A1
公开(公告)日：2016-03-10
申请号：US14942988
申请日：2015-11-16
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The upper winglet root chord and the lower winglet root chord may each have a length of no greater than 100 percent of the wing tip chord. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.
摘要翻译： 用于飞机机翼的小翼系统可以包括安装到翼尖的上小翼和下小翼。 上小翼根弦和下小翼根弦可以各自具有不大于翼尖弦的100％的长度。 当机翼受到地面静载荷时，下小翼可能具有静止位置。 下小翼可以被配置为使得在大约1g飞行载荷下翼的向上偏转导致下小翼从静态位置向上和向外移动到飞行位置，导致翼的有效跨度增加 在地面静载荷下相对于机翼跨度的大约1-g飞行载荷。
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