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11. 发明授权

US09745994B2 Airfoil shape for a compressor 有权
公开(公告)号：US09745994B2
公开(公告)日：2017-08-29
申请号：US14845360
申请日：2015-09-04
申请人： GENERAL ELECTRIC COMPANY
发明人： Marc Edward Blohm , Svitlana Kalmyk
IPC分类号： F01D5/14 , F04D29/32
CPC分类号： F04D29/324 , F01D5/141 , F05B2240/301 , F05D2240/301
摘要： An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

12. 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.

13. 发明申请

US20170175538A1 COOLING SYSTEMS AND INTERNALLY-COOLED ENGINE PARTS HAVING AN IMPINGEMENT CAVITY WITH AN UNDULATING INTERNAL SURFACE 审中-公开
公开(公告)号：US20170175538A1
公开(公告)日：2017-06-22
申请号：US14974418
申请日：2015-12-18
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SCOTT D. LEWIS , KYLE C. LANA
IPC分类号： F01D5/18 , F23R3/00 , F01D11/08 , F01D25/12 , F01D5/14 , F01D9/04
CPC分类号： F01D5/187 , F01D5/145 , F01D5/147 , F01D9/041 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2240/12 , F05D2240/24 , F05D2240/301 , F05D2240/35 , F05D2240/81 , F05D2250/611 , F05D2260/201 , F05D2260/22141 , F23R3/002 , Y02T50/676
摘要： An airfoil is provided. The airfoil comprises a crossover and an impingement cavity in fluid communication with the crossover and having an internal surface. At least a portion of the internal surface comprises an undulating internal surface. A plurality of trip strips may be disposed on the at least a portion of the internal surface to define the undulating internal surface. A gas turbine engine and an internally-cooled engine part are also provided.

14. 发明申请

US20170159461A1 STACKING OF ROTOR BLADES ON CENTROIDS 审中-公开
公开(公告)号：US20170159461A1
公开(公告)日：2017-06-08
申请号：US15364892
申请日：2016-11-30
申请人： MTU Aero Engines AG
发明人： Carsten Schoenhoff , Martin Pernleitner , Klaus Wittig , Manfred Dopfer , Marcus Woehler , Wilfrid Schuette , Christoph Bichlmaier , Rudolf Stanka , Norman Cleesattel
IPC分类号： F01D5/30 , F01D5/02 , F02C7/36 , F01D5/22
CPC分类号： F01D5/30 , F01D5/02 , F01D5/141 , F01D5/225 , F02C7/36 , F05D2220/323 , F05D2240/24 , F05D2240/301 , F05D2240/307 , F05D2250/231 , F05D2250/232 , F05D2300/606 , Y02T50/673
摘要： A rotor blade for a gas turbine, in particular an aircraft gas turbine, having a blade root element and a stream deflection portion adjoining the blade root element (12) in the longitudinal direction of the blade (RR); respective centroids (24) of blade cross-sectional areas of the stream deflection portion residing on a common stacking axis (26). It is provided that, starting from a first centroid (24) of a first blade cross-sectional area adjoining the blade root element (12), the stacking axis (26) extend within a cone (28) whose apex resides within the first centroid (24), and whose cone height (KH) extends orthogonally to the plane of the blade cross-sectional area; the angle (β) of the cone (28) being greater than 0° and smaller than or equal to 4°; preferably greater than or equal to 0.5° and smaller than or equal to 2°.

15. 发明授权

US09546661B2 Rotor machine intended to function as a pump or an agitator and an impeller for such a rotor machine 有权
标题翻译：用作这种转子机器的泵或搅拌器和叶轮的转子机
公开(公告)号：US09546661B2
公开(公告)日：2017-01-17
申请号：US14116116
申请日：2012-05-08
申请人： Ola Eriksson , Daniel Marjavaara
发明人： Ola Eriksson , Daniel Marjavaara
IPC分类号： F04D29/42 , F04D1/04 , F04D29/24 , F04D29/22
CPC分类号： F04D1/04 , F04D29/2216 , F04D29/2255 , F04D29/242 , F05D2240/301 , F05D2250/51 , F05D2250/52
摘要： The invention concerns a rotor machine and an impeller, of which the rotor machine is intended to function as a liquid pump or as an agitator in a fluid such as a liquid or a colloid, whereby the rotor machine has a pump casing (1) with an impeller (2) mounted in bearings in a manner that allows rotation around an axis (X), and in which the rotor machine has three principal flow pathways, comprising: —an axial inlet opening (4) with a defined area of opening (Ain) —a radially oriented outlet opening (5) with a defined area of opening (Aut), and —a series of radially extending blades (3) that, distributed around the circumference of the impeller, form between them a number of flow channels (22:1-22:n). In order to achieve an improved working capacity, the area of opening (Ain) of the inlet opening (4), the area of opening (Aut) of the outlet opening and the total effective area of opening of the flow channels (22:1-22:n) that extends through the impeller are so mutually designed that the three principal passages of the rotor machine are filled and emptied of the said fluid in an essentially equal manner.
摘要翻译：本发明涉及转子机器和叶轮，其中转子机器旨在用作液体泵或作为流体例如液体或胶体中的搅拌器，由此转子机器具有泵壳体（1），其具有以允许围绕轴线（X）旋转的方式安装在轴承中的叶轮（2），并且其中转子机器具有三个主要流动路径，其包括： - 具有限定的开口面积的轴向入口（4） Ain） - 具有限定的开口面积（Aut）的径向定向的出口开口（5），以及一系列径向延伸的叶片（3），其分布在叶轮周围，在它们之间形成多个流动通道（22：1-22：n）。为了实现改进的工作能力，入口开口（4）的开口面积（Ain），出口开口面积（Aut）和流道开口总有效面积（22：1） -22：n）相互设计，使得转子机器的三个主要通道以基本上相等的方式被填充并排出所述流体。

16. 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。

17. 发明授权

US09458720B2 Airfoil and platform assembly for supersonic flow 有权
标题翻译：用于超音速流动的翼型和平台组件
公开(公告)号：US09458720B2
公开(公告)日：2016-10-04
申请号：US13984722
申请日：2012-02-06
申请人： Damien Cellier , Vincent Paul Gabriel Perrot , Jean-Francois Rios
发明人： Damien Cellier , Vincent Paul Gabriel Perrot , Jean-Francois Rios
IPC分类号： F01D5/14 , F01D5/02 , G06F17/50
CPC分类号： F01D5/02 , F01D5/143 , F01D5/145 , F05D2240/301 , F05D2240/80 , F05D2250/713 , G06F17/5009 , Y02T50/673
摘要： An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve.
摘要翻译：包括翼型件和平台的组件可以安装翼型件，平台的表面在翼型件的前缘和后缘之间呈现圆周凹陷，凹陷的最深部分位于翼型。骨架曲线表示作为沿着车轴的位置的函数的翼型的骨架角的变化的曲线，线性骨架曲线表示作为沿着轴的轴线的位置的函数的角度的变化的曲线该曲线是将代表骨架角度的点分别连接在翼缘的轴向范围的10％和90％处的直线。在平台附近，骨架曲线呈现位于线性骨架曲线之上的隆起部分。

18. 发明授权

US09291059B2 Airfoil for a compressor blade 有权
标题翻译：翼型用于压缩机叶片
公开(公告)号：US09291059B2
公开(公告)日：2016-03-22
申请号：US12646561
申请日：2009-12-23
申请人： Marco Micheli , Gabriel Dunkel , Luis Frederico Puerta , Wolfgang Kappis
发明人： Marco Micheli , Gabriel Dunkel , Luis Frederico Puerta , Wolfgang Kappis
IPC分类号： F01D5/14 , F04D29/32
CPC分类号： F01D5/141 , F04D29/324 , F05D2240/301 , F05D2250/70
摘要： The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD), stagger angle (γ) and camber angle (Δβ). The stagger angle (γ) and camber angle (Δβ) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.
摘要翻译：本公开提供了一种用于压缩机叶片的改进的第一级翼型件，其具有独特的弦长（CD），交错角（γ）和外倾角（＆Dgr; bgr）。交错角（γ）和外倾角（＆Dgr;＆bgr）提供改进的空气动力学，而弦长（CD）提供降低的翼型重量。

19. 发明授权

US09279334B2 Gas turbine engine 有权
标题翻译：燃气轮机
公开(公告)号：US09279334B2
公开(公告)日：2016-03-08
申请号：US13542674
申请日：2012-07-06
申请人： Shawn P. Lawlor , William Byron Roberts, II
发明人： Shawn P. Lawlor , William Byron Roberts, II
IPC分类号： F01D9/00 , F02C9/16 , F02C3/04 , F02C7/00 , F01D1/10 , F01D1/02 , F01D1/16 , F01D9/04 , F02C9/18 , F02C3/00 , F02C3/06 , F02C3/14 , F04D21/00
CPC分类号： F01D9/00 , F01D1/026 , F01D1/10 , F01D1/16 , F01D5/02 , F01D9/047 , F02C3/00 , F02C3/04 , F02C3/06 , F02C3/14 , F02C7/00 , F02C7/22 , F02C9/16 , F02C9/18 , F04D21/00 , F05D2220/3216 , F05D2220/3218 , F05D2220/3219 , F05D2240/128 , F05D2240/30 , F05D2240/301 , F05D2240/302 , F05D2240/35 , Y02E20/14
摘要： A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.
摘要翻译：具有压缩机转子的燃气涡轮发动机具有压缩机脉冲叶片，其将超声波条件下的气体输送到定子。定子包括一个或多个空气动力学管道，每个空气动力学管道具有会聚部分和发散部分，用于将选定气体减速至亚音速条件并将含有气体的高压氧化剂输送到火焰持有器。火焰保持器可以被设置为被捕获的涡流燃烧器，用于燃烧燃料以产生热的加压燃烧气体。热的加压燃烧气体在从空气动力学管道流出到涡轮机之前被阻塞。通过将燃烧气体膨胀通过脉冲叶片在涡轮机中恢复工作。通过平衡压缩机脉冲叶片和涡轮脉冲叶片上的轴向载荷，可以最小化或避免非对称推力。

20. 发明授权

US09279329B2 Transonic blade 有权
标题翻译：跨音速刀片
公开(公告)号：US09279329B2
公开(公告)日：2016-03-08
申请号：US13879084
申请日：2010-10-18
申请人： Chihiro Myoren , Yasuo Takahashi , Shinya Marushima
发明人： Chihiro Myoren , Yasuo Takahashi , Shinya Marushima
IPC分类号： F04D29/38 , F01D5/14 , F04D21/00 , F04D29/32
CPC分类号： F01D5/147 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F05D2210/30 , F05D2240/301 , F05D2240/302 , Y02T50/673
摘要： The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction.
摘要翻译：本发明提供一种跨音速刀片，其同时实现设计点的减震和在轴流式旋转机器中以跨音速或更高的流场工作的叶片的失速余量的改善。刀片的每个翼展位置处的横截面表面平行于将前缘与刀片的后缘连接的交错线移动。堆垛线向工作流体的上游侧移动。堆叠线将叶片横截面的各重心位置从翼面方向位置的连接到旋转机械的旋转轴或外周侧壳体的轮毂横截面的顶端横截面位于最远离轮毂横截面的翼展方向的位置上。

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