专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

91. 发明授权

US09745850B2 Blade cascade and continuous-flow machine 有权
公开(公告)号：US09745850B2
公开(公告)日：2017-08-29
申请号：US14286584
申请日：2014-05-23
申请人： MTU Aero Engines AG
发明人： Yavuz Guendogdu , Jochen Gier , Karl Engel
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F01D5/146 , F05D2240/301 , F05D2240/305 , F05D2240/306 , Y02T50/673
摘要： A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed.

92. 发明申请

US20170159462A1 FAN BLADE APPARATUS 审中-公开
公开(公告)号：US20170159462A1
公开(公告)日：2017-06-08
申请号：US15346334
申请日：2016-11-08
申请人： ROLLS-ROYCE plc
发明人： John WHURR , Martyn RICHARDS
IPC分类号： F01D7/00 , F02K3/06 , F04D29/38
CPC分类号： F01D7/00 , B64C11/32 , F01D5/146 , F02K3/06 , F04D29/323 , F04D29/388 , F05D2220/36 , F05D2240/30 , F05D2260/70 , Y02T50/673
摘要： A gas turbine engine fan blade apparatus is disclosed comprising a reverse pitch rotatable mounting and an aerofoil part. The aerofoil part comprises radially inner and radially outer portions that are separated by an interface extending from a leading edge of the aerofoil part to a trailing edge of the aerofoil part. The reverse pitch rotatable mounting locates the radially inner and radially outer portions with respect to one another. The reverse pitch rotatable mounting and separation at the interface permit relative pitch change rotation between the radially inner and radially outer portions such that one of the radially inner and radially outer portions is rotatable to a reverse pitch configuration by comparison with the other portion.

93. 发明申请

US20170159445A1 MISTUNED CONCENTRIC AIRFOIL ASSEMBLY AND METHOD OF MISTUNING SAME 审中-公开
公开(公告)号：US20170159445A1
公开(公告)日：2017-06-08
申请号：US14618478
申请日：2015-02-10
申请人： United Technologies Corporation
发明人： Richard K. Hayford , Steven J. Ford
IPC分类号： F01D5/14 , F01D5/22 , F01D25/06 , F01D5/02
CPC分类号： F01D5/146 , F01D5/022 , F01D5/225 , F01D25/06 , F05D2260/961 , Y02T50/673
摘要： An example method of reducing a vibratory response of airfoils that support a shroud includes circumferentially misaligning some of the airfoils in a radially inner array of airfoils with all airfoils of a radially outer array of airfoils, and circumferentially aligning at least one of the airfoils in the radially inner array of airfoils with all airfoils of the radially outer array of airfoils.

94. 发明申请

US20170114796A1 COMPRESSOR INCORPORATING SPLITTERS 审中-公开
公开(公告)号：US20170114796A1
公开(公告)日：2017-04-27
申请号：US14923005
申请日：2015-10-26
申请人： General Electric Company
发明人： Anthony Louis DiPietro, JR. , Gregory John Kajfasz
IPC分类号： F04D29/54 , F04D29/32 , F04D19/00
CPC分类号： F04D29/544 , F01D5/143 , F01D5/146 , F01D9/041 , F04D19/00 , F04D29/324
摘要： A compressor apparatus includes: an inner flowpath surface; an outer flowpath surface; an array of stator airfoils extending between the inner and outer flowpath surfaces; and an array of airfoil-shaped splitter vanes extending from at least one of the inner and outer flowpath surfaces, the splitter vanes alternating with the stator airfoils, wherein at least one of a chord dimension of the splitter vanes at the roots thereof and a span dimension of the splitter vanes is less than a corresponding dimension of the stator airfoils.

95. 发明授权

US09488191B2 Gas turbine diffuser strut including coanda flow injection 有权
标题翻译：燃气涡轮增压器支柱，包括连续流注射
公开(公告)号：US09488191B2
公开(公告)日：2016-11-08
申请号：US14067173
申请日：2013-10-30
申请人： Pawel Matys
发明人： Pawel Matys
IPC分类号： F01D25/30 , F01D5/14 , F04D29/54
CPC分类号： F04D29/542 , F01D5/146 , F01D25/305 , F05D2270/173
摘要： An exhaust diffuser comprising an inner boundary and an outer boundary forming an annular gas path, and a plurality of strut structures extending radially within the gas path. Each of the strut structures include pressure and suction side walls, and a plurality of radially spaced flow injectors are formed in at least one of the pressure and suction side walls for injecting a fluid flow into the gas path adjacent to the strut structure. At least two fluid supply conduits provide a fluid flow to respective radially spaced flow injectors, and a flow control device is associated with each of the conduits to independently control a fluid flow from a fluid source to each of the radially spaced flow injectors.
摘要翻译：一种排气扩散器，包括形成环形气体路径的内边界和外边界，以及在气体路径内径向延伸的多个支柱结构。每个支柱结构包括压力和吸力侧壁，并且多个径向间隔开的流动喷射器形成在至少一个压力和吸力侧壁中，用于将流体流注入到与支柱结构相邻的气体路径中。至少两个流体供应管道向相应的径向间隔开的流动喷射器提供流体流动，并且流量控制装置与每个导管相关联，以独立地控制从流体源到每个径向间隔开的流动喷射器的流体流动。

96. 发明授权

US09488064B2 Turbomachine with variable-pitch vortex generator 有权
标题翻译：涡轮机与可变螺距涡流发生器
公开(公告)号：US09488064B2
公开(公告)日：2016-11-08
申请号：US13935827
申请日：2013-07-05
申请人： SNECMA
发明人： Vincent Paul Gabriel Perrot , Agnes Claire Marie Pesteil
IPC分类号： F01D17/14 , F04D29/68 , F04D29/56
CPC分类号： F01D17/148 , F01D5/143 , F01D5/146 , F01D9/041 , F01D17/162 , F04D29/563 , F04D29/681 , F05D2240/126 , F05D2240/127 , Y02T50/671 , Y02T50/673
摘要： A turbomachine including at least one bladed disk and vortex generators positioned upstream of the blading of the disk is provided. The vortex generators are of variable pitch.
摘要翻译：提供了包括至少一个叶片盘和位于盘的叶片上游的涡流发生器的涡轮机。涡流发生器具有可变节距。

97. 发明授权

US09470097B2 Airfoil with leading edge reinforcement 有权
标题翻译：翼型加筋
公开(公告)号：US09470097B2
公开(公告)日：2016-10-18
申请号：US14094313
申请日：2013-12-02
申请人： Rolls-Royce Corporation
发明人： Benedict N. Hodgson , Jonathan M. Rivers
IPC分类号： F01D5/28 , B23K1/00 , B23K31/02 , F01D5/14 , F01D21/04 , F04D29/32 , F04D29/54
CPC分类号： F01D5/282 , B23K1/0008 , B23K31/02 , F01D5/14 , F01D5/146 , F01D5/286 , F01D5/288 , F01D21/045 , F04D29/324 , F04D29/542 , F05D2230/237 , F05D2240/303 , Y02T50/672 , Y02T50/673
摘要： A leading edge member for a composite vane of a gas turbine engine. The leading edge member includes a first leg and a second leg. The first leg includes a proximal end joined to a proximal end of the second leg.
摘要翻译：一种用于燃气涡轮发动机的复合叶片的前缘构件。前缘构件包括第一腿部和第二腿部。第一腿包括连接到第二腿的近端的近端。

98. 发明授权

US09470091B2 Blade group arrangement as well as turbomachine 有权
标题翻译：刀片组安排以及涡轮机
公开(公告)号：US09470091B2
公开(公告)日：2016-10-18
申请号：US13760580
申请日：2013-02-06
申请人： MTU Aero Engines GmbH
发明人： Sergio Elorza Gomez , Alexander Hergt , Ulrich Siller , Tim Schneider
IPC分类号： F01D1/24 , F01D5/02 , F01D5/14 , F01D9/04 , F04D29/32 , F04D29/54 , F04D29/56
CPC分类号： F01D5/022 , F01D5/146 , F01D9/041 , F04D29/324 , F04D29/542 , F04D29/544 , F04D29/563 , F05D2240/301 , Y02T50/673
摘要： A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade.
摘要翻译：用于涡轮机的叶片组装置以形成叶片排组，由此前叶片和后叶片各自形成具有至少1.2的收缩比的重叠区域，并且还涉及具有这样的叶片组的涡轮机前叶片和后叶片之间的收缩比。

99. 发明授权

US09453423B2 Turbomachine 有权
标题翻译：涡轮机
公开(公告)号：US09453423B2
公开(公告)日：2016-09-27
申请号：US13760598
申请日：2013-02-06
申请人： MTU Aero Engines GmbH
发明人： Sergio Elorza Gomez , Tim Schneider
IPC分类号： F01D5/14 , F04D29/54 , F01D9/00 , F01D9/04
CPC分类号： F01D9/00 , F01D5/146 , F01D9/041 , F04D29/544 , F05D2240/40 , F05D2270/17 , Y02T50/673
摘要： A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides.
摘要翻译：公开了一种涡轮机，具有至少一个叶片排组，其位于主流动路径中，并且在主流动方向上具有至少两个相邻的叶片排，每个叶片排具有多个叶片，所述叶片的后边缘上游叶片排的叶片和下游叶片排的叶片的前缘在周向方向上位于从主流路中心沿至少一个主流限制的方向开始变化的边缘距离处，边缘双边边缘距离增加或减小。

100. 发明授权

US09422864B2 Staggered double row, slotted airfoil design for gas turbine exhaust frame 有权
标题翻译：用于燃气轮机排气框架的交错双列，开槽翼型设计
公开(公告)号：US09422864B2
公开(公告)日：2016-08-23
申请号：US13723047
申请日：2012-12-20
申请人： General Electric Company
发明人： Kunal Upendra Sakekar , Moorthi Subramaniyan , Srinivasarao Pakkala
IPC分类号： F01D9/02 , F02C7/00 , F01D9/04 , F01D5/14 , F01D25/30
CPC分类号： F02C7/00 , F01D5/145 , F01D5/146 , F01D9/041 , F01D25/30 , F05D2240/12
摘要： A gas turbine exhaust frame includes an inner barrel and an outer barrel establishing an annular exhaust gas flow path therebetween. A plurality of airfoils extend radially between the inner barrel and the radially, outer barrel, the plurality of struts arranged in first and second axially-spaced and circumferentially-staggered rows.
摘要翻译：燃气轮机排气框架包括内筒和外筒，其在它们之间建立环形废气流动路径。多个翼型件在内筒和径向外筒之间径向延伸，多个支柱布置在第一和第二轴向间隔和周向交错的行中。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式