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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：US20170107999A1
公开(公告)日：2017-04-20
申请号：US14886904
申请日：2015-10-19
Applicant: ROLLS-ROYCE CORPORATION
Inventor： Bradley T. Fanton , Roy David Fulayter
CPC classification number: B23P15/006 , F01D5/3007 , F01D5/3092 , F04D29/322 , F05D2300/1721 , Y02T50/672
Abstract: According to one aspect, a rotating structure comprises a hub having a mounting slot defined by a cavity surface and a body having an anchor structure disposed in the mounting slot. A wear member is disposed between the anchor structure and the cavity surface and the wear member has at least first and second portions of first and second material characteristics, respectively.
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Patent Agency Ranking
公开(公告)号：US20140241890A1
公开(公告)日：2014-08-28
申请号：US14133140
申请日：2013-12-18
Applicant: Rolls-Royce Corporation
Inventor： Roy David Fulayter , Jonathan Michael Rivers
CPC classification number: F01D5/3061 , B23K20/12 , B23P15/02 , F01D5/005 , F01D5/34 , F05D2230/239 , Y10T29/49318 , Y10T29/49336
Abstract: In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface.
Abstract translation: 在一些示例中，装置可以包括燃气涡轮发动机部件，其包括叶片，形成气流表面的平台，刀片从一侧延伸出来，以及设置在平台的非气流侧的运动焊接接收表面，以及 具有运动焊接盘部分的盘，用于接收燃气涡轮发动机部件的运动焊接接收表面，并且当盘和燃气涡轮发动机部件联接时形成运动焊接耦合，其中，在耦合之前，燃气涡轮发动机部件进一步 包括设置在所述平台的非气流侧的叶片杆，并且其中形成有所述运动焊接接收表面。
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公开(公告)号：US10099323B2
公开(公告)日：2018-10-16
申请号：US14886904
申请日：2015-10-19
Applicant: ROLLS-ROYCE CORPORATION
Inventor： Bradley T. Fanton , Roy David Fulayter
Abstract: According to one aspect, a rotating structure comprises a hub having a mounting slot defined by a cavity surface and a body having an anchor structure disposed in the mounting slot. A wear member is disposed between the anchor structure and the cavity surface and the wear member has at least first and second portions of first and second material characteristics, respectively.
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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：US09896948B2
公开(公告)日：2018-02-20
申请号：US14133140
申请日：2013-12-18
Applicant: Rolls-Royce Corporation
Inventor： Roy David Fulayter , Jonathan Michael Rivers
CPC classification number: F01D5/3061 , B23K20/12 , B23P15/02 , F01D5/005 , F01D5/34 , F05D2230/239 , Y10T29/49318 , Y10T29/49336
Abstract: In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface.
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公开(公告)号：US20140314548A1
公开(公告)日：2014-10-23
申请号：US14319702
申请日：2014-06-30
Applicant: Rolls-Royce Corporation
Inventor： Jonathan Michael Rivers , Roy David Fulayter
CPC classification number: F01D17/105 , F01D9/042 , F02K3/075 , F05D2260/961 , Y02T50/672 , Y10T29/49316
Abstract: One embodiment of the present invention is a unique vane system. Another embodiment is a unique gas turbine engine. Another embodiment is a unique method for manufacturing a bypass vane stage. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbine engines and vane systems for turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
Abstract translation: 本发明的一个实施例是独特的叶片系统。 另一个实施例是独特的燃气涡轮发动机。 另一实施例是用于制造旁路叶片级的独特方法。 其他实施例包括用于涡轮发动机的涡轮发动机和叶片系统的装置，系统，装置，硬件，方法和组合。 本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。
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