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公开(公告)号：US20140255188A1
公开(公告)日：2014-09-11
申请号：US14099519
申请日：2013-12-06
Inventor： Roy D. Fulayter , Daniel K. Vetters , Bronwyn Power
IPC: F01D5/12
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.
Abstract translation: 公开了一种在顶端和轮毂端具有球形界面形状的燃气涡轮发动机气流元件。 在一个实施例中，气流构件是风扇叶片。 球形界面形状可以是凸的或凹的。 在一种形式中，尖端球形相对于轮毂端轴向向后移动。 尖端可以包括在扩张流动路径中相对较小的前部，其顶端的主要部分处于收缩流动路径中。 这种配置可以发生在位于收缩流动路径中的中间点和后沿。 具有球形端部形状的扫气流构件的重心可以位于气流构件的枢轴上。 可以提供Divot凹陷以允许凹形流动路径形状。
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公开(公告)号：US20180231016A1
公开(公告)日：2018-08-16
申请号：US15338035
申请日：2016-10-28
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power , Jonathan M. Rivers
CPC classification number: F04D29/282 , B23K2101/001 , B63H1/16 , B64C11/001 , B64C11/06 , B64C2201/162 , B64C2201/165 , B64D2027/005 , F01D5/143 , F01D5/225 , F02C9/58 , F02K3/04 , F02K3/072 , F04D29/326 , F04D29/329 , F04D29/34 , F05D2220/323 , F05D2220/326 , F05D2220/327 , F05D2220/36
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：US20180003189A1
公开(公告)日：2018-01-04
申请号：US15197137
申请日：2016-06-29
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power
CPC classification number: F04D29/324 , F01D5/141 , F01D5/145 , F04D29/544 , F05D2250/713 , Y02T50/671 , Y02T50/673
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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公开(公告)号：US09568009B2
公开(公告)日：2017-02-14
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：US11231044B2
公开(公告)日：2022-01-25
申请号：US16176250
申请日：2018-10-31
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power
Abstract: An apparatus comprises a gas turbine engine having a compressor for increasing a total pressure of a working fluid prior to delivery to a combustor for mixing with fuel. The compressor has a plurality of airfoil members that extend between a first flow surface and a second flow surface. The plurality of airfoil members have a first camber shape at a tip portion that provides a cumulative integral according to the relationship 0.4
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Patent Agency Ranking
公开(公告)号：US10294862B2
公开(公告)日：2019-05-21
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
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：US20190072103A1
公开(公告)日：2019-03-07
申请号：US16176250
申请日：2018-10-31
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power
Abstract: An apparatus comprises a gas turbine engine having a compressor for increasing a total pressure of a working fluid prior to delivery to a combustor for mixing with fuel. The compressor has a plurality of airfoil members that extend between a first flow surface and a second flow surface. The plurality of airfoil members have a first camber shape at a tip portion that provides a cumulative integral according to the relationship 0.4
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公开(公告)号：US10145383B2
公开(公告)日：2018-12-04
申请号：US15048611
申请日：2016-02-19
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power
Abstract: An apparatus comprises a gas turbine engine having a compressor. The compressor airfoil member is disposed in the compressor and has a camber angle variation along a chord and a concave pressure side surface at a tip portion of the compressor airfoil member from a leading edge to an intermediate-chord location. This first camber shape results in a normalized camber angle that reaches at least 0.4 in the first 10% of normalized chord, and the normalized camber angle is defined as β ′ = β i - β β i - β e where βi is inlet metal angle, βe is exit metal angle, and β is a camber angle at a given chord location.
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公开(公告)号：US20180119705A1
公开(公告)日：2018-05-03
申请号：US15337936
申请日：2016-10-28
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power , Jonathan M. Rivers
CPC classification number: F04D29/326 , B64C11/001 , B64C11/48 , B64C2201/162 , B64C2201/165 , B64D2027/005 , F01D5/143 , F01D5/225 , F02C9/58 , F02K3/04 , F02K3/072 , F04D19/002 , F04D29/023 , F05D2220/323 , F05D2220/326 , F05D2220/327 , F05D2220/36
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：US20160169243A1
公开(公告)日：2016-06-16
申请号：US15048611
申请日：2016-02-19
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power
CPC classification number: F04D29/324 , F01D5/141 , F04D29/544 , F05D2200/23 , F05D2240/301 , F05D2250/70 , Y02T50/673
Abstract: An apparatus comprises a gas turbine engine having a compressor. The compressor airfoil member is disposed in the compressor and has a camber angle variation along a chord and a concave pressure side surface at a tip portion of the compressor airfoil member from a leading edge to an intermediate-chord location. This first camber shape results in a normalized camber angle that reaches at least 0.4 in the first 10% of normalized chord, and the normalized camber angle is defined as β ′ = β i - β β i - β e where βi is inlet metal angle, βe is exit metal angle, and β is a camber angle at a given chord location.
Abstract translation: 一种装置包括具有压缩机的燃气涡轮发动机。 压缩机翼型构件设置在压缩机中，并且在压缩机翼型构件的顶端处的弦和凹压侧表面具有从前缘到中和弦位置的外倾角变化。 该第一弧形形状导致在标准化弦的前10％中达到至少0.4的归一化外倾角，并且将归一化外倾角定义为＆bgr; '=＆bgr 我 - ＆bgr ＆bgr 我 - ＆bgr e其中＆bgr; i是入口金属角度，e是出口金属角度，＆bgr; 是一个给定和弦位置的外倾角。
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