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21. 发明申请

US20160032728A1 GAS TURBINE ENGINE AIRFOIL 审中-公开
标题翻译：气体涡轮发动机气翼
公开(公告)号：US20160032728A1
公开(公告)日：2016-02-04
申请号：US14836577
申请日：2015-08-26
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC分类号： F01D5/14 , F01D5/02 , F02C3/107
CPC分类号： F01D5/141 , F01D5/02 , F02C3/107 , F02K3/00 , F05D2200/222 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/30 , F05D2240/301 , F05D2250/713 , F05D2260/40311 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starts at the 0% span position is either zero or positive. The first critical point is less than 15% span.
摘要翻译：涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型末端处的100％跨度位置。翼型件具有切向堆积偏移和跨度位置之间的关系，其是包括至少一个正斜率和负斜率的至少三阶多项式曲线。正斜坡倾斜到吸力侧，负斜坡朝向压力侧倾斜。在0％跨度位置开始的初始斜率为零或正。第一个关键点是小于15％的跨度。

22. 发明申请

US20150361797A1 GAS TURBINE ENGINE AIRFOIL 审中-公开
标题翻译：气体涡轮发动机气翼
公开(公告)号：US20150361797A1
公开(公告)日：2015-12-17
申请号：US14837183
申请日：2015-08-27
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC分类号： F01D5/14 , F02C3/107
CPC分类号： F01D5/141 , F02C3/107 , F02K3/00 , F02K3/06 , F04D29/384 , F05D2200/222 , F05D2220/323 , F05D2220/36 , F05D2240/301 , F05D2250/713 , Y02T50/672 , Y02T50/673
摘要： An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans aftward and the negative slope leans forward relative to an engine axis. The positive slope crosses an initial axial stacking offset corresponding to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is less than 2.0.
摘要翻译：用于涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。翼型件具有层叠偏移和跨度位置之间的关系，其是包括至少一个正斜率和负斜率的至少三阶多项式曲线。正斜坡向后倾斜，负斜坡相对于发动机轴向前倾斜。正斜率跨过与过零位置的0％跨度位置对应的初始轴向堆积偏移。第一轴向堆叠偏移X1从过零位置提供到曲线上的负最大值。第二轴向堆叠偏移X2从过零点提供到曲线上的最大值。第二轴向叠置偏移量X2 / X1的比率小于2.0。

23. 发明申请

US20150233252A1 GAS TURBINE ENGINE AIRFOIL 有权
标题翻译：气体涡轮发动机气翼
公开(公告)号：US20150233252A1
公开(公告)日：2015-08-20
申请号：US14626167
申请日：2015-02-19
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC分类号： F01D5/14 , F02K3/00
CPC分类号： F01D5/141 , F01D5/02 , F02C3/107 , F02K3/00 , F05D2200/222 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/30 , F05D2240/301 , F05D2250/713 , F05D2260/40311 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starting at the 0% span position is either zero or positive. The first critical point is in the range of 5-15% span.
摘要翻译：涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型末端处的100％跨度位置。翼型件具有切向堆积偏移和跨度位置之间的关系，其是包括至少一个正斜率和负斜率的至少三阶多项式曲线。正斜坡倾斜到吸力侧，负斜坡朝向压力侧倾斜。从0％跨度位置开始的初始斜率为零或正。第一个关键点在5-15％范围内。

24. 发明申请

US20150204196A1 Gas Turbine 有权
标题翻译：燃气轮机
公开(公告)号：US20150204196A1
公开(公告)日：2015-07-23
申请号：US14413826
申请日：2012-09-12
申请人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
发明人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
IPC分类号： F01D5/14 , F02C3/04
CPC分类号： F01D5/143 , F01D5/082 , F01D5/145 , F01D5/187 , F01D5/20 , F02C3/04 , F05D2240/301 , F05D2240/55
摘要： The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade. In a gas turbine rotor blade 4 including a wing shape section 12 formed of a negative pressure surface 12d extending from a front edge 12a to a rear edge 12b, a pressure surface 12c opposing the negative pressure surface 12d and extending from the front edge 12a to the rear edge 12b, and a tip surface 13 surrounded by the top end of the negative pressure surface 12d and the top end of the pressure surface 12c, and an end wall section 10 connected to the bottom end of the negative pressure surface 12d and the bottom end of the pressure surface 12c, the rotor blade has a convex shape in positions constituting the negative pressure surface 12d side and the front edge 12a side of the end wall section 10, and the rotor blade has a concave shape in positions constituting the pressure surface 12c side and the front edge 12a side of the end wall section 10.
摘要翻译：本发明的目的在于，即使从转子叶片的端壁部的前端部混入冷却制冷剂，也能够抑制燃气轮机的转子叶片前端附近的二次电流涡流的发展。在包括由从前缘12a延伸到后边缘12b的负压面12d形成的翼形部12的燃气轮机转子叶片4中，与负压面12d相对并从前缘12a延伸到后缘12b和由负压面12d的顶端和压力表面12c的顶端包围的前端表面13以及连接到负压表面12d的底端的端壁部10和压力表面12c的底端，转子叶片在构成负压表面12d侧的位置和端壁部分10的前缘12a侧的位置具有凸形，并且转子叶片在构成压力的位置具有凹形表面12c侧和端壁部10的前缘12a侧。

25. 发明授权

US09003812B2 Supporting structure for a gas turbine engine 有权
标题翻译：燃气轮机的支撑结构
公开(公告)号：US09003812B2
公开(公告)日：2015-04-14
申请号：US13319114
申请日：2009-05-08
申请人： Roger Sjöqvist
发明人： Roger Sjöqvist
IPC分类号： F02C7/20 , F03B11/02 , F01D25/28 , F03B1/04 , F01D9/04 , F01D25/24
CPC分类号： F01D25/28 , F01D9/04 , F01D25/24 , F02C7/20 , F05D2240/301 , Y02T50/673
摘要： A supporting structure for a gas turbine engine includes at least one annular member, and a plurality of circumferentially spaced elements that extend in a radial direction of the annular member and that are connected to the annular member. At least one of the circumferentially spaced elements has an airfoil shape in cross section. The annular member includes at least two substantially flat panel segments that are arranged side by side in a circumferential direction of the annular member. The panel segments are connected to each other in a connection region that extends along facing end parts of the two panel segments. The airfoil shaped element is connected to the annular member at the connection region. A mean camber line of the airfoil shaped element at least along a portion of its length is inclined in relation to an axial direction of the annular member, and the connection region at least along a portion of its length is inclined in relation to the axial direction of the annular member. The inclined portion of the connection region is directed substantially in parallel to the inclined portion of the mean camber line of the airfoil shaped element. A gas turbine engine including a supporting structure of the above type is also provided.
摘要翻译：用于燃气涡轮发动机的支撑结构包括至少一个环形构件和沿环形构件的径向方向延伸并且连接到环形构件的多个周向间隔开的元件。周向隔开的元件中的至少一个在横截面上具有翼型形状。环形构件包括在环形构件的圆周方向上并排布置的至少两个基本上平坦的面板段。面板段在两个面板段的相对端部分延伸的连接区域中彼此连接。翼型元件在连接区域处连接到环形构件。至少沿其长度的一部分，翼型元件的平均弧线相对于环形构件的轴向方向倾斜，并且至少沿着其长度的一部分的连接区域相对于轴向方向倾斜的环形构件。连接区域的倾斜部分基本上平行于翼型元件的平均弧线的倾斜部分。还提供了一种包括上述类型的支撑结构的燃气涡轮发动机。

26. 发明授权

US08944773B2 Rotor blade with bonded cover 有权
标题翻译：转子叶片带保护盖
公开(公告)号：US08944773B2
公开(公告)日：2015-02-03
申请号：US13286371
申请日：2011-11-01
申请人： Michael A. Weisse
发明人： Michael A. Weisse
IPC分类号： F01D5/14 , F04D29/38 , F01D5/18 , B63H1/26 , B63H7/02 , B23P15/04 , F04D29/32
CPC分类号： F01D5/147 , B23P15/04 , F01D5/16 , F04D29/324 , F05D2230/23 , F05D2240/301 , F05D2250/61 , Y02T50/672 , Y02T50/673
摘要： An airfoil comprises an airfoil body with an internal cavity and inner and outer covers. The airfoil body defines a first major surface of the airfoil, and a rib extends along the internal cavity. The inner cover is bonded to the airfoil body over the internal cavity, and includes a coupling element extending along the internal cavity in cooperative engagement with the rib. The outer cover is bonded to the airfoil body over the inner cover, and defines a second major surface of the airfoil.
摘要翻译：翼型件包括具有内部空腔的机翼本体和内外盖。机翼本体限定翼型件的第一主表面，并且肋沿着内部空腔延伸。所述内盖在所述内部空腔上结合到所述翼型件主体，并且包括沿着所述内部空腔延伸以与所述肋协作接合的联接元件。外盖在内盖上结合到机翼本体，并且限定翼型的第二主表面。

27. 发明授权

US08602740B2 Turbine vane airfoil 有权
标题翻译：涡轮叶片翼型
公开(公告)号：US08602740B2
公开(公告)日：2013-12-10
申请号：US12877703
申请日：2010-09-08
申请人： Jason L. O'Hearn , Timothy Charles Nash
发明人： Jason L. O'Hearn , Timothy Charles Nash
IPC分类号： F01D9/02 , F01D5/14
CPC分类号： F01D5/141 , F01D5/143 , F01D9/041 , F05D2240/12 , F05D2240/301 , F05D2240/80 , F05D2250/74 , Y02T50/67 , Y02T50/672 , Y02T50/673
摘要： An airfoil comprises an external surface formed in substantial conformance with a plurality of cross sections. Each of the cross sections has an axial chord and an offset at a corresponding fractional span as set forth in Table 1. Each of the cross sections is described by a set of Cartesian coordinates defined at the corresponding fractional span as set forth in Table 3.
摘要翻译：翼型件包括基本上符合多个横截面形成的外表面。每个横截面具有如表1所示的相应分数跨度的轴向弦和偏移。每个横截面由如表3所示的相应分数跨度定义的一组笛卡尔坐标来描述。

28. 发明申请

US20130259668A1 Transonic Blade 有权
标题翻译：跨音速刀片
公开(公告)号：US20130259668A1
公开(公告)日：2013-10-03
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： F01D5/14
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超音速或更高速度流动的叶片中的失速余量的改善。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。

29. 发明授权

US08511979B2 High pressure turbine vane airfoil profile 有权
标题翻译：高压涡轮叶片翼型
公开(公告)号：US08511979B2
公开(公告)日：2013-08-20
申请号：US12749779
申请日：2010-03-30
申请人： Remo Marini
发明人： Remo Marini
IPC分类号： F01D9/02
CPC分类号： F01D5/141 , F01D5/288 , F05D2230/90 , F05D2240/301 , F05D2250/74 , F05D2260/95 , F05D2300/611
摘要： A two-stage high pressure turbine includes a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
摘要翻译：两级高压涡轮机包括具有基本上根据表2所示的X，Y和Z的笛卡尔坐标值的至少中间部分的轮廓的翼型的第二级叶片.X和Y值是当通过适当的连续曲线平稳地连接时，在每个距离Z处限定翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的翼型形状。

30. 发明授权

US08506256B1 Thin walled turbine blade and process for making the blade 有权
标题翻译：薄壁涡轮叶片和制造叶片的工艺
公开(公告)号：US08506256B1
公开(公告)日：2013-08-13
申请号：US13622551
申请日：2012-09-19
申请人： Florida Turbine Technologies, Inc.
发明人： Joseph D Brostmeyer , William L Plank
IPC分类号： F01D25/14
CPC分类号： F01D5/147 , F01D5/18 , F05D2230/10 , F05D2230/14 , F05D2230/21 , F05D2240/301 , Y10T29/49341
摘要： A thin wall turbine blade used in a gas turbine engine, in which the blade is cast in conventional grain from a super alloy using the lost wax process as a single piece, and then the blade walls are machined to remove enough material to leave a thin wall. The blade is cast with a wall thickness greater than the designed for thin wall in order that any core shifting during the casting process will be accounted for in the machining process. prior to machining, a scanning process is used to measure the actual wall thickness on all portions of the blade wall in order to determine how much material must be removed to leave the blade wall with the proper thinness.
摘要翻译：用于燃气涡轮发动机中的薄壁涡轮机叶片，其中叶片以常规晶粒从超级合金铸造，使用失蜡法作为单件，然后将叶片壁加工以除去足够的材料以留下薄的壁。刀片的浇铸厚度大于为薄壁设计的壁厚，以便在铸造过程中的任何芯移动将在加工过程中得到考虑。在加工之前，使用扫描过程来测量叶片壁的所有部分上的实际壁厚，以便确定必须移除多少材料以使叶片壁具有合适的薄度。

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