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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：US10253784B2
公开(公告)日：2019-04-09
申请号：US15065247
申请日：2016-03-09
Applicant: Rolls-Royce Corporation
Inventor： Roy D. Fulayter
Abstract: A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk. The fan disk is adapted for rotation about a central axis. The fan blades are coupled to the fan disk for rotation therewith about the central axis.
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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：US20160265547A1
公开(公告)日：2016-09-15
申请号：US15065247
申请日：2016-03-09
Applicant: Rolls-Royce Corporation
Inventor： Roy D. Fulayter
CPC classification number: F04D29/362 , B64C11/325 , B64C11/48 , B64D27/10 , F01D7/00 , F02K1/66 , F04D19/02 , F04D29/323 , F04D29/325 , F05D2220/36 , F05D2260/4031 , F05D2260/53 , F05D2260/74 , F05D2260/79
Abstract: A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk. The fan disk is adapted for rotation about a central axis. The fan blades are coupled to the fan disk for rotation therewith about the central axis.
Abstract translation: 公开了一种用于燃气涡轮发动机的风扇。 风扇包括风扇盘和耦合到风扇盘的多个风扇叶片。 风扇盘适于围绕中心轴线旋转。 风扇叶片联接到风扇盘，用于围绕中心轴线旋转。
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Patent Agency Ranking
公开(公告)号：US20160194961A1
公开(公告)日：2016-07-07
申请号：US14845478
申请日：2015-09-04
Applicant: Rolls-Royce Corporation
Inventor： Roy D. Fulayter , Daniel Hoyniak
CPC classification number: F01D5/10 , F01D5/12 , F01D5/34 , F01D25/04 , F04D29/321 , F04D29/324 , F04D29/668 , F05D2220/32 , F05D2260/407 , F05D2260/96 , G10K11/002 , Y02T50/672
Abstract: A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.
Abstract translation: 用于减振的叶片组件包括围绕叶片的中心轴线周向延伸的圆盘部分，与圆盘一体地联接的多个叶片，以及包括阻尼环和耦合到阻尼器的多个压电元件的压电阻尼环 环。 盘部分包括构造成接收压电阻尼环的凹槽。 由于在叶片组件旋转期间施加到压电阻尼环的离心力的结果是，可以在多个压电元件中的一个或多个压电元件处产生机械能，其被转换成电能并传递到另一个或多个 多个压电元件。 因此，一个或多个已经接收电的压电元件可以将电转换成机械能以提供减振。
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公开(公告)号：US20150322803A1
公开(公告)日：2015-11-12
申请号：US14698299
申请日：2015-04-28
Applicant: Rolls-Royce Corporation
Inventor： Roy D. Fulayter , Jonathan M. Rivers , Matthew Jordan , Daniel E. Molnar
CPC classification number: F01D5/26 , F01D5/027 , F01D5/10 , F01D5/146 , F01D5/16 , F05D2220/32 , F05D2260/96 , Y02T50/671 , Y02T50/673
Abstract: A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor.
Abstract translation: 用于燃气涡轮发动机的转子包括中央轮和从中心轮向外延伸的多个叶片。 叶片不均匀以减少在包括转子的燃气涡轮发动机的运行期间引起的颤动和强制响应效应。
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公开(公告)号：US10273903B2
公开(公告)日：2019-04-30
申请号：US15076113
申请日：2016-03-21
Inventor： Roy D. Fulayter , Crawford F. Smith, III
Abstract: A nacelle for a gas turbine jet engine for an aircraft includes plasma actuators that act as flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse or perpendicular to direction of travel of the engine.
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公开(公告)号：US20180209345A1
公开(公告)日：2018-07-26
申请号：US15867309
申请日：2018-01-10
Applicant: Rolls-Royce Corporation
Inventor： Roy D. Fulayter , Michael G. Meyer
Abstract: A gas turbine engine assembly includes a static component and a rotatable component configured to rotate about a central axis of the gas turbine engine assembly relative to the static component. The gas turbine engine assembly further includes a vibration-dampening system configured to dampen vibration of the gas turbine engine assembly.
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公开(公告)号：US20160238034A1
公开(公告)日：2016-08-18
申请号：US15042569
申请日：2016-02-12
Applicant: Rolls-Royce Corporation
Inventor： Roy D. Fulayter , Jonathan M. Rivers
CPC classification number: F04D29/668 , F01D5/16 , F01D5/3015 , F04D29/325 , F05D2220/36 , F05D2230/60 , F05D2260/961
Abstract: A fan assembly for use in a gas turbine engine includes a fan wheel and a plurality of blades extending radially from the fan wheel away from a central axis of the fan assembly. Each of the blades includes a root coupled with the fan wheel and an airfoil extending radially outwardly from the root. The blades are adapted to rotate about the central axis to push air.
Abstract translation: 用于燃气涡轮发动机的风扇组件包括风扇叶轮和从风扇叶片径向延伸远离风扇组件的中心轴线的多个叶片。 每个叶片包括与风扇叶轮联接的根部和从根部径向向外延伸的翼型件。 叶片适于围绕中心轴线旋转以推动空气。
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