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公开(公告)号：US11060527B2
公开(公告)日：2021-07-13
申请号：US15337936
申请日：2016-10-28
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power , Jonathan M. Rivers
IPC: F04D29/32 , F02K3/072 , F02C9/58 , F01D5/14 , F02K3/04 , F01D5/22 , B64C11/00 , B64C11/48 , F04D19/00 , F04D29/02 , B64D27/00
Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about −5 degrees and about 45 degrees. Passive leading edge slats are attached to the ring airfoil and are configured to open and close using springs.
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公开(公告)号：US10539024B2
公开(公告)日：2020-01-21
申请号：US15644159
申请日：2017-07-07
Inventor： Roy D. Fulayter , Daniel K. Vetters , Bronwyn Power
Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.
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公开(公告)号：US20170306762A1
公开(公告)日：2017-10-26
申请号：US15644159
申请日：2017-07-07
Inventor： Roy D. Fulayter , Daniel K. Vetters , Bronwyn Power
CPC classification number: F01D5/12 , F01D7/00 , F01D17/162 , F04D29/323 , F04D29/563 , F05D2220/36 , Y02T50/671
Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.
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公开(公告)号：US20150128604A1
公开(公告)日：2015-05-14
申请号：US14092356
申请日：2013-11-27
Applicant: ROLLS-ROYCE CORPORATION
Inventor： Bronwyn Power , Roy D. Fulayter , Jonathan M. Rivers
CPC classification number: F04D19/028 , F01D5/143 , F01D5/20 , F02C3/00 , F02C9/16 , F05D2250/231 , F05D2250/232 , F05D2250/293 , F05D2250/70 , Y02T50/673
Abstract: A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side. The cylindrical upstream side can extend from a leading edge of the bladed component, or a point upstream of it, to a location between the leading edge and trailing edge of the component. The conical downstream side can extend past the trailing edge of the bladed component. The bladed component can be a fan blade or a compressor blade.
Abstract translation: 公开了一种在叶片部件的位置处的燃气轮机的流路面，其中，流路面包括圆筒状的上游侧和锥形的下游侧。 叶片部件位于圆柱形上游侧和锥形下游侧的交叉处。 圆柱形上游侧可以从叶片部件的前边缘或其上游的点延伸到部件的前缘和后缘之间的位置。 锥形下游侧可延伸穿过叶片部件的后缘。 叶片组件可以是风扇叶片或压缩机叶片。
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公开(公告)号：US10935041B2
公开(公告)日：2021-03-02
申请号：US15197137
申请日：2016-06-29
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power
Abstract: In accordance with some embodiments of the present disclosure, a pressure recovery axial compressor blade is provided. The blade may comprise a high pressure surface and a low pressure surface connected at a leading edge and a trailing edge of the blade. Both the high and low pressure surfaces extend span wise from a first end to a second end. At least one of the high and low pressure surfaces has a finite discontinuity in curvature at an intermediate position along the chord of the blade.
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Patent Agency Ranking
公开(公告)号：US20170145917A1
公开(公告)日：2017-05-25
申请号：US14949208
申请日：2015-11-23
Applicant: Rolls-Royce Corporation
Inventor： Roy David Fulayter , Aaron Joseph King , Bronwyn Power , Greg Hebert
CPC classification number: F02C7/042 , F01D1/04 , F01D5/143 , F01D5/20 , F01D5/225 , F05D2250/00 , F05D2250/712 , Y02T50/673
Abstract: A turbine engine casing flow-path segment that is locally diffusing, followed by a flow-path segment contracting in the vicinity of a fan blade. This contraction accelerates the fluid flow axially forward of the fan blade leading edge at the tip and converges with the linear flow-path aft of the fan blade leading edge but forward of the fan blade trailing edge. More diffused fluid flow results in increased flow capacity of the fan, and increased fan efficiency.
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公开(公告)号：US10605257B2
公开(公告)日：2020-03-31
申请号：US15338035
申请日：2016-10-28
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power , Jonathan M. Rivers
IPC: B64C11/00 , F01D5/22 , F04D29/32 , F02K3/04 , F02K3/072 , B63H1/16 , B64D27/00 , F04D29/28 , F02C9/58 , F01D5/14 , B64C11/06 , F04D29/34 , B23K101/00
Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about −5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.
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公开(公告)号：US10309236B2
公开(公告)日：2019-06-04
申请号：US14144697
申请日：2013-12-31
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power
Abstract: A gas turbine engine strut has a forebody positioned upstream of a point of maximum thickness and an aft body positioned downstream of the point of maximum thickness. The aft body has a discontinuity in a curvature distribution which provides for a “subsonic shock.” The discontinuity in curvature distribution can include in inflection point that marks a transition from a curvature associated with an upstream portion of the aft body to a second curvature associated with a downstream portion of the aft body. In some forms, the aft body can additionally include boundary layer aspiration. The gas turbine engine strut can be symmetrical about a centerline.
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公开(公告)号：US09708914B2
公开(公告)日：2017-07-18
申请号：US14099519
申请日：2013-12-06
Inventor： Roy D Fulayter , Daniel K Vetters , Bronwyn Power
CPC classification number: F01D5/12 , F01D17/162 , F04D29/323 , F04D29/563 , F05D2220/36 , Y02T50/671
Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.
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公开(公告)号：US20150016983A1
公开(公告)日：2015-01-15
申请号：US14144697
申请日：2013-12-31
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power
IPC: F01D9/02
CPC classification number: F01D9/02 , F01D25/28 , F05D2240/124 , F05D2250/70 , F05D2250/713
Abstract: A gas turbine engine strut is disclosed as having a will forebody positioned upstream of a point of maximum thickness and an aft body positioned downstream of the point of maximum thickness. The aft body includes a discontinuity in a curvature distribution which provides for a “subsonic shock.” The discontinuity in curvature distribution can include in inflection point that marks a transition from a curvature associated with an upstream portion of the aft body to a second curvature associated with a downstream portion of the aft body. In some forms, the aft body can additionally include boundary layer aspiration. The gas turbine engine strut can be symmetrical about a centerline.
Abstract translation: 公开了一种燃气涡轮发动机支柱，其具有将位于最大厚度点上游的预定位置和位于最大厚度点下游的后部主体。 后身体包括提供“亚音速冲击”的曲率分布中的不连续性。曲率分布的不连续性可以包括标记从与后身的上游部分相关联的曲率到与第二曲率相关联的曲率的转变的拐点 具有后身的下游部分。 在一些形式中，后身体还可以包括边界层抽吸。 燃气涡轮发动机支柱可以关于中心线对称。
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