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公开(公告)号：US20150122952A1
公开(公告)日：2015-05-07
申请号：US14185045
申请日：2014-02-20
CPC分类号： F02C7/04 , B64D27/20 , B64D33/02 , B64D2033/0286 , F05D2220/36 , F05D2250/14 , Y10T137/0536
摘要： A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.
摘要翻译： 燃气涡轮发动机具有形成为具有在一半中具有第一椭圆的形状的入口管道和在后半部分中的第二椭圆形状的入口管道。 下半部具有比第一椭圆小的上游端。 入口管道具有限定第二椭圆的表面，其从第一椭圆开始弯曲，使得第二椭圆在中间位置较大。 在进入风扇的入口管道的下游端，第二个椭圆较大。
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公开(公告)号：US20160144972A1
公开(公告)日：2016-05-26
申请号：US14295578
申请日：2014-06-04
CPC分类号： B64D33/02 , B64C39/10 , B64C2039/105 , B64D2033/0226 , B64D2033/0253 , B64D2033/0273 , Y02T50/12
摘要： An inlet for a propulsion system has an upper wall and a lower wall and a throat extending between the upper wall and the lower wall. The lower wall has a bump edge located immediately after the throat.
摘要翻译： 用于推进系统的入口具有上壁和下壁以及在上壁和下壁之间延伸的喉部。 下壁具有位于喉咙之后的凸起边缘。
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公开(公告)号：US20160122005A1
公开(公告)日：2016-05-05
申请号：US14203735
申请日：2014-03-11
发明人： Razvan Virgil Florea , William T. Cousins , Thomas G. Tillman , David J. Arend , John D. Wolter
CPC分类号： B64C21/04 , B64C1/16 , B64C39/10 , B64C2039/105 , B64C2230/04 , B64D27/18 , B64D27/20 , B64D29/04 , B64D33/02 , B64D2033/0226 , B64D2033/0253 , Y02T50/166
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US10415505B2
公开(公告)日：2019-09-17
申请号：US14911577
申请日：2014-04-17
IPC分类号： F02C7/04 , F02K3/06 , F01D5/14 , F01D5/20 , F02C7/045 , F04D29/52 , F04D27/02 , F04D29/32 , F04D29/54 , F02C3/04
摘要： 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.
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公开(公告)号：US09291101B2
公开(公告)日：2016-03-22
申请号：US14185045
申请日：2014-02-20
CPC分类号： F02C7/04 , B64D27/20 , B64D33/02 , B64D2033/0286 , F05D2220/36 , F05D2250/14 , Y10T137/0536
摘要： A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.
摘要翻译： 燃气涡轮发动机具有形成为具有在一半中具有第一椭圆的形状的入口管道和在后半部分中的第二椭圆形状的入口管道。 下半部具有比第一椭圆小的上游端。 入口管道具有限定第二椭圆的表面，其从第一椭圆开始弯曲，使得第二椭圆在中间位置较大。 在进入风扇的入口管道的下游端，第二个椭圆较大。
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公开(公告)号：US20150354501A1
公开(公告)日：2015-12-10
申请号：US14296769
申请日：2014-06-05
IPC分类号： F02K1/82
CPC分类号： G06K7/0004 , F02K1/82 , G06K5/00 , G06K7/0013 , G06K7/084 , G06K9/036
摘要： An exit nozzle section for an engine has an outer wall and an inner wall, and a plurality of exit guide vanes extending between the outer wall and the inner wall. Different ones of the exit guide vanes having different cambers in different regions of the exit nozzle section.
摘要翻译： 用于发动机的出口喷嘴部分具有外壁和内壁以及在外壁和内壁之间延伸的多个出口导向叶片。 不同的出口导向叶片在出口喷嘴部分的不同区域具有不同的弯度。
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公开(公告)号：US11498660B2
公开(公告)日：2022-11-15
申请号：US16167968
申请日：2018-10-23
发明人： Razvan Virgil Florea , William T. Cousins , Thomas G. Tillman , David J. Arend , John D. Wolter
IPC分类号： B64C21/04 , B64D29/04 , B64C21/02 , B64C21/08 , B64D27/20 , B64C39/10 , B64C1/16 , B64D33/02
摘要： 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.
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公开(公告)号：US20190055006A1
公开(公告)日：2019-02-21
申请号：US16167968
申请日：2018-10-23
发明人： Razvan Virgil Florea , William T. Cousins , Thomas G. Tillman , David J. Arend , John D. Wolter
摘要： 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.
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公开(公告)号：US20160003048A1
公开(公告)日：2016-01-07
申请号：US14761738
申请日：2013-12-18
摘要： In accordance with one aspect of the disclosure, an airfoil is disclosed. The airfoil may include a platform and a blade extending from the platform. The blade may have a root proximate the platform and a tip radially outward from the platform. The root may have a greater thickness than a cross-section at about a quarter-span of the blade or greater.
摘要翻译： 根据本公开的一个方面，公开了一种翼型件。 翼型件可以包括从平台延伸的平台和叶片。 叶片可以具有靠近平台的根部和从平台径向向外的尖端。 根部可以具有比叶片大约四分之一跨度处的横截面更大的厚度或更大的厚度。
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