专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US09856884B2 Valve for gas turbine engine 有权
公开(公告)号：US09856884B2
公开(公告)日：2018-01-02
申请号：US14318482
申请日：2014-06-27
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Douglas David Dierksmeier , Daniel Kent Vetters
IPC分类号： F01D9/06 , F01D11/24 , F02C9/18 , F04D27/02
CPC分类号： F04D27/0238 , F01D9/06 , F01D11/24 , F02C9/18 , F05D2270/101 , F05D2270/17
摘要： A gas turbine engine is disclosed having an air injection system useful to supply a relatively pressurized air to a flow path of a compressor. The air injection system includes a port cover operable to open and close a port through which the air can flow to the compressor from a relatively pressurized source. The port cover extends circumferentially around the gas turbine engine and can include a portion that is anchored and an opposite portion coupled to an actuator. Movement of the actuator causes the port cover to open and close the port. Biasing members can be used to urge the port cover into one of an open and closed position against the movement of the actuator.

2. 发明申请

US20170260903A1 AIR INLET DUCT FOR AN AIRCRAFT TURBINE ENGINE 审中-公开
公开(公告)号：US20170260903A1
公开(公告)日：2017-09-14
申请号：US15455532
申请日：2017-03-10
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Romeo Brogna , Romain Jean-Claude Ferrier
IPC分类号： F02C7/04 , F02C6/20 , F02C3/04
CPC分类号： F02C7/04 , F02C3/04 , F02C6/206 , F02C7/057 , F02K3/072 , F05D2220/325 , F05D2270/17
摘要： Air inlet duct of a turbine engine, in particular an aircraft turbine engine comprising a gas generator, which extends axially between the air inlet and the gas generator and has a first axial wall part and a second wall part which is angularly offset with respect to the first part, which duct is capable of causing, in a shedding region, shedding of the boundary layer formed by an air flow along the wall of the duct; and a device for controlling said shedding of the boundary layer, characterised in that the control device comprises an air-blowing pipe which opens via at least one air-injection opening which is directly upstream of the shedding region, the blowing pipe being connected to an air intake positioned upstream of said air-injection opening or in the shedding region and comprising an air compressor means between the air intake and the air-injection opening.

3. 发明授权

US09574452B2 Noise-reduced turbomachine 有权
标题翻译：减噪涡轮机
公开(公告)号：US09574452B2
公开(公告)日：2017-02-21
申请号：US13704073
申请日：2011-06-14
申请人： Marco Rose , Lars Willer
发明人： Marco Rose , Lars Willer
IPC分类号： F01D9/04 , F04D29/54 , F04D27/02 , F01D5/14 , F02C9/18 , F01D9/02 , F02C7/045 , F01D5/18 , F04D29/68
CPC分类号： F01D9/041 , F01D5/145 , F01D5/18 , F01D9/02 , F02C7/045 , F02C9/18 , F04D27/023 , F04D29/544 , F04D29/682 , F05D2240/12 , F05D2240/122 , F05D2240/304 , F05D2260/96 , F05D2270/17 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbomachine has an annular main flow duct through which passes a flow, and in which is arranged at least one stator provided with stator vanes. The stator vanes each have at least one recess issuing into a flow duct inside the stator vanes and the flow duct issues into a bypass duct of the turbomachine via at least one outflow duct provided with a shut-off element.
摘要翻译：涡轮机具有环形主流道，通过该流动通道流动，其中布置有至少一个设有定子叶片的定子。定子叶片各自具有至少一个凹槽，该凹槽发出到定子叶片内的流动管道中，并且流动管道经由设置有切断元件的至少一个流出管道发出到涡轮机的旁路管道。

4. 发明申请

US20160061217A1 COMPRESSOR AIRFOIL 有权
标题翻译：压缩机AIRFOIL
公开(公告)号：US20160061217A1
公开(公告)日：2016-03-03
申请号：US14469961
申请日：2014-08-27
申请人： Pratt & Whitney Canada Corp.
发明人： Hien DUONG , Jason NICHOLS
IPC分类号： F04D29/38 , F04D19/02 , F04D19/00
CPC分类号： F04D29/384 , F01D5/141 , F01D5/145 , F04D19/00 , F04D19/02 , F04D29/324 , F05D2240/303 , F05D2270/17
摘要： A compressor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip of the airfoil. A leading edge sweep angle is defined relative to a tangent to the airfoil and flow velocity vector at a point on the leading edge. A leading edge dihedral angle is defined relative to the tangent to the airfoil and a vertical at the point on the leading edge. A ratio of the leading edge sweep angle to the leading edge dihedral angle being smaller than 1. A method of forming such airfoil is also presented.
摘要翻译：提出了一种燃气轮机的压缩机翼型。相反的压力和吸力侧在弦向相反的前缘和后缘连接在一起。压力和吸力侧沿翼面的根部延伸到翼型的尖端。前缘扫掠角相对于翼型的切线和前缘上的点处的流速矢量来定义。前缘二面角相对于翼型件的切线和前缘上的点处的垂直线限定。前缘扫掠角与前缘二面角的比值小于1.还提出了形成这种翼型的方法。

5. 发明申请

US20150292344A1 INGESTION BLOCKING ENDWALL FEATURE 审中-公开
标题翻译：射击阻塞终点功能
公开(公告)号：US20150292344A1
公开(公告)日：2015-10-15
申请号：US14680382
申请日：2015-04-07
申请人： United Technologies Corporation
发明人： Conway Chuong , Jeffrey J. Lienau , William Yeager
IPC分类号： F01D11/00
CPC分类号： F01D11/00 , F01D5/143 , F01D5/145 , F05D2240/80 , F05D2250/11 , F05D2270/17 , Y02T50/673
摘要： An endwall of a gas turbine engine section comprises a flow path surface and a wall. The flow path surfaces defines an inner diameter of a main flow path through the gas turbine engine section, and terminates in an aft waterfall step. The wall extends substantially radially inward from the waterfall step, and defines a blockage feature that impedes airflow from the main flow path to a secondary air cavity situated inward of the waterfall step.
摘要翻译：燃气涡轮发动机部分的端壁包括流动路径表面和壁。流路表面限定通过燃气涡轮发动机部分的主流路的内径，并且终止于后瀑布步骤。壁从瀑布步骤基本上径向向内延伸，并且限定了妨碍从主流路到位于瀑布步骤内侧的二次空气腔的气流的阻塞特征。

6. 发明申请

US20150240646A1 GROUP OF BLADE ROWS 审中-公开
公开(公告)号：US20150240646A1
公开(公告)日：2015-08-27
申请号：US14626594
申请日：2015-02-19
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Volker GUEMMER
IPC分类号： F01D5/14 , F04D29/54 , F04D19/00
CPC分类号： F01D5/142 , F01D5/06 , F01D5/146 , F01D9/041 , F04D19/002 , F04D29/324 , F04D29/544 , F05D2240/40 , F05D2270/17 , Y02T50/673
摘要： The present invention relates to a blade row group arrangeable in a main flow path of a fluid-flow machine and including N adjacent member blade rows firmly arranged relative to one another in both the meridional direction (m) and the circumferential direction (u), with the number N of the member blade rows being greater than/equal to 2 and (i) designating the running index with values between 1 and N. Here, a front member blade row with front blades (i) having a leading edge and a trailing edge as well as a rear member blade row with rear blades (i+1) having a leading edge and a trailing edge are provided.

7. 发明授权

US08844264B2 Gas turbine engine with ejector 有权
标题翻译：带喷射器的燃气轮机
公开(公告)号：US08844264B2
公开(公告)日：2014-09-30
申请号：US13191038
申请日：2011-07-26
申请人： Syed Jalaluddin Khalid
发明人： Syed Jalaluddin Khalid
IPC分类号： F02K3/02 , F02K1/36 , B64C7/02 , F02K3/077 , B64D33/02
CPC分类号： B64C7/02 , B64D2033/0226 , F02K1/36 , F02K3/077 , F05D2260/601 , F05D2270/17
摘要： Disclosed is a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet noise and decrease thrust specific fuel consumption. A boundary layer withdrawn through the boundary layer bleed slots is entrained with an exhaust flow of a gas turbine engine. In another embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with a flow stream internal to the gas turbine engine, such as a fan stream of a turbofan. A moveable shroud can be used to open and close a passage of an ejector which can be used to assist in withdrawing a boundary layer or entrain an ambient air. A lobed mixer can be used in some embodiments to effect mixing between the boundary layer and a primary fluid of the ejector.
摘要翻译：公开了一种边界层喷射器，从飞机的外表面流体连接边界层排放槽，以减少飞机/机舱/塔架阻力，减少喷气噪声并降低推力比燃料消耗。通过边界层排出槽排出的边界层与燃气涡轮发动机的排气夹带。在另一个实施例中，通过边界层排出槽排出的边界层与燃气涡轮发动机内部的流动流（例如涡扇风扇的风扇流）一起被夹带。可移动的护罩可以用于打开和关闭喷射器的通道，喷射器可用于帮助排出边界层或夹带环境空气。在一些实施例中，可以使用裂片混合器来实现边界层和喷射器的初级流体之间的混合。

8. 发明申请

US20140248154A1 BLADE OF A ROW OF ROTOR BLADES OR STATOR BLADES FOR USE IN A TURBOMACHINE 有权
标题翻译：用于涡轮机的转子刀片或定子刀片的刀片
公开(公告)号：US20140248154A1
公开(公告)日：2014-09-04
申请号：US14348845
申请日：2012-09-28
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Volker Guemmer
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F01D5/141 , F01D5/145 , F04D29/324 , F04D29/544 , F04D29/681 , F05D2270/17 , Y02T50/673
摘要： The present invention relates to a blade of a row of rotor blades or stator blades for use in a turbomachine, with the blade being designed with a substantially convex suction side and a substantially concave pressure side as well as with a leading edge, onto which the flow passes, and a trailing edge, away from which the flow passes. The blade has at least one contour recess provided on at least one of the blade sides including the suction side and the pressure side, wherein the contour recess includes a step edge, a contour corner and a flank face provided between the step edge and the contour corner. The contour recess extends over at least a part of the profile depth and/or the profile height of the blade.
摘要翻译：本发明涉及一种用于涡轮机的一排转子叶片或定子叶片的叶片，叶片被设计成具有基本上凸的吸力侧和基本凹陷的压力侧以及前缘，流动通道和后缘，远离流动通过的后缘。叶片具有设置在包括吸力侧和压力侧的至少一个叶片侧面上的至少一个轮廓凹部，其中轮廓凹槽包括台阶边缘，轮廓角部和设置在台阶边缘和轮廓之间的侧面角。轮廓凹槽在轮廓深度的至少一部分和/或叶片的轮廓高度上延伸。

9. 发明授权

US08814529B2 Blade for a turbo device with a vortex-generator 有权
标题翻译：具有涡流发生器的涡轮增压器的叶片
公开(公告)号：US08814529B2
公开(公告)日：2014-08-26
申请号：US13054768
申请日：2009-07-17
申请人： Andreas Fiala , Jochen Gier
发明人： Andreas Fiala , Jochen Gier
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F05D2250/182 , F05D2250/184 , F05D2270/17 , Y02T50/673
摘要： A blade construction for a turbo device, preferably a blade array of a low-pressure turbine, is disclosed. On the inlet-side profile surface of the blade a vortex generator is arranged downstream from the speed maximum. The vortex generator is formed by a surface undulation with at least one wave, the wave tail of which runs in the form of a wave trough and/or a wave peak in the blade vertical direction.
摘要翻译：公开了一种用于涡轮装置的叶片结构，优选地是低压涡轮机的叶片阵列。在叶片的入口侧轮廓表面上，涡流发生器布置在最大速度的下游。涡流发生器由具有至少一个波的表面起伏形成，其波尾以波谷的形式和/或叶片垂直方向上的波峰的形式延伸。

10. 发明授权

US08662825B2 Cooled aerofoil blade or vane 有权
标题翻译：冷却翼型叶片或叶片
公开(公告)号：US08662825B2
公开(公告)日：2014-03-04
申请号：US12861560
申请日：2010-08-23
申请人： Peter T. Ireland , Howoong Namgoong
发明人： Peter T. Ireland , Howoong Namgoong
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2250/324 , F05D2270/17
摘要： An aerofoil blade or vane suitable for the turbine of a gas turbine engine includes an extending aerofoil portion having facing wall parts interconnected by a divider member to partially define first and second cooling fluid passage portions. The first and second passage portions are interconnected in a series fluid flow relationship by a bend passage portion. The first passage portion directs cooling fluid to the bend portion and the second passage portion exhausts cooling fluid from the bend portion. The divider member provides a localised contraction of the downstream end of the first passage portion to accelerate the cooling fluid flow before it enters the bend passage portion. The divider member provides a localised progressive series narrowing and opening of the upstream end of the second passage portion in the general direction of cooling fluid flow.
摘要翻译：适合于燃气涡轮发动机的涡轮机的机翼叶片或叶片包括延伸的机翼部分，其具有通过分隔件互连的面对的壁部分，以部分地限定第一和第二冷却流体通道部分。第一和第二通道部分由弯曲通道部分以串联流体流动关系相互连接。第一通道部分将冷却流体引导到弯曲部分，第二通道部分从弯曲部分排出冷却流体。分隔构件提供第一通道部分的下游端的局部收缩，以在其进入弯曲通道部分之前加速冷却流体流动。分隔构件提供沿着冷却流体流动的大致方向的第二通道部分的上游端的局部渐进式系列变窄和打开。

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