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    Airfoil cooling channel anti-plugging devices
    21.
    发明公开
    Airfoil cooling channel anti-plugging devices 有权
    Vorrichtungen zur Vermeidung von Verstopfungen vonSchaufelkühlkanälen

    公开(公告)号：EP2022940A2

    公开(公告)日：2009-02-11

    申请号：EP08252488.5

    申请日：2008-07-22

    申请人： United Technologies Corporation

    发明人： Devore, Matthew A. ,  Cunha, Francisco J.

    IPC分类号： F01D5/18

    CPC分类号： F01D5/186 ,  F01D5/187 ,  F01D25/32 ,  F05D2260/204 ,  F05D2260/607 ,  Y10T29/49341

    摘要： A turbine engine component (10), such as a high pressure turbine vane, has an airfoil portion (12) and at least one coolant system embedded (114) within the airfoil portion (12). Each coolant system has an exit (126) through which a cooling fluid flows, which exit has at least one device (158) for preventing deposits from interfering with the flow of cooling fluid from the exit. The at least one device may be at least one depression (158) and/or at least one grill structure (258, Fig. 6 ) formed from elongated ribs.

    摘要翻译： 诸如高压涡轮叶片的涡轮发动机部件（10）具有翼型部分（12）和在翼型部分（12）内嵌入（114）的至少一个冷却剂系统。 每个冷却剂系统具有出口（126），冷却流体通过该出口流出，该出口具有至少一个装置（158），用于防止沉积物干扰来自出口的冷却流体的流动。 至少一个装置可以是由细长肋形成的至少一个凹部（158）和/或至少一个格栅结构（图6中的258）。

    Turbine blade main core modifications for peripheral serpentine microcircuits
    23.
    发明公开
    Turbine blade main core modifications for peripheral serpentine microcircuits 有权
    Gusskernmodifikationen Turbinenschaufelnfürperiphere serpentinenartigeMikrokanäle

    公开(公告)号：EP1936118A2

    公开(公告)日：2008-06-25

    申请号：EP07254654.2

    申请日：2007-11-30

    申请人： United Technologies Corporation

    发明人： Cunha, Francisco J. ,  Scott, Gayman W.

    IPC分类号： F01D5/18

    CPC分类号： B22C9/103 ,  B22C9/04 ,  F01D5/186 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/202 ,  Y02T50/676

    摘要： A turbine engine component, such as a turbine blade, has an airfoil portion (100) having a pressure side wall (106) and a suction side wall (108), a first cooling circuit (110) embedded within the pressure side wall (106), which first cooling circuit (110) has at least two passageways (112,114,116) embedded within the pressure side wall (106), a second cooling circuit (118) embedded within the suction side wall (108), which second cooling circuit (118) has at least two passageways (120,122,124) embedded within the suction side wall (108), at least one cooling fluid supply cavity (140,140') located between the pressure and suction side walls (106,108), each cooling fluid supply cavity (140,140') having at least one projecting portion (144,144',146,146') extending between adjacent ones of the embedded passageways in the first cooling circuit (110) or adjacent ones of the embedded passageways in the second cooling circuit (118), and each projecting portion (144,144',146,146') communicating with at least one film cooling hole (150,152,154,156). A method for forming the turbine blade component is also described.

    摘要翻译： 诸如涡轮叶片的涡轮发动机部件具有具有压力侧壁（106）和吸力侧壁（108）的翼型部分（100），嵌入压力侧壁（106）内的第一冷却回路（110） ），所述第一冷却回路（110）具有嵌入在所述压力侧壁（106）内的至少两个通道（112,114,116）;嵌入所述吸入侧壁（108）内的第二冷却回路（118），所述第二冷却回路 ）具有嵌入在吸入侧壁（108）内的至少两个通道（120,122,124），位于压力侧和吸力侧壁（106,108）之间的至少一个冷却流体供应腔（140,140'），每个冷却流体供应腔（140,140' ）具有在第一冷却回路（110）中相邻的嵌入通道之间延伸的至少一个突出部分（144,144'，146,146'）或第二冷却回路（118）中相邻的嵌入通道中的每一个突出部分 （144,144'，146,146'）通信 具有至少一个薄膜冷却孔（150,152,154,156）。 还描述了用于形成涡轮叶片部件的方法。

    Radially split serpentine cooling microcircuits
    24.
    发明公开
    Radially split serpentine cooling microcircuits 有权
    径向过滤器Mikrokühlkreis

    公开(公告)号：EP1882816A2

    公开(公告)日：2008-01-30

    申请号：EP07014918.2

    申请日：2007-07-30

    申请人： United Technologies Corporation

    发明人： Cunha, Francisco J.

    IPC分类号： F01D5/18

    CPC分类号： F01D5/188 ,  F01D5/186 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/202

    摘要： A turbine engine component (100), such as a turbine blade has an airfoil portion (102) with an airfoil mean line (138), a pressure side (130), and a suction side (132). A first region (134) on the pressure side (130) of the airfoil portion (102) has a first array of cooling microcircuits embedded in a wall forming the pressure side (130). A second region (136) on the pressure side (130) has a second array of cooling microcircuits embedded in the wall. The first region (134) is located on a first side of the mean line (138) and the second region (136) is located on a second side of the mean line (138).

    摘要翻译： 诸如涡轮叶片的涡轮发动机部件（100）具有具有翼型平均线（138），压力侧（130）和吸力侧（132）的翼型部分（102）。 机翼部分（102）的压力侧（130）上的第一区域（134）具有嵌入形成压力侧（130）的壁中的第一阵列的冷却微电路。 压力侧（130）上的第二区域（136）具有嵌入在壁中的冷却微电路的第二阵列。 第一区域（134）位于平均线（138）的第一侧上，而第二区域（136）位于平均线（138）的第二侧。

    Turbine blade main core modifications for peripheral serpentine microcircuits
    29.
    发明公开
    Turbine blade main core modifications for peripheral serpentine microcircuits 有权
    铸造型芯的修改涡轮叶片外围蛇形微通道

    公开(公告)号：EP1936118A3

    公开(公告)日：2011-10-05

    申请号：EP07254654.2

    申请日：2007-11-30

    申请人： United Technologies Corporation

    发明人： Cunha, Francisco J. ,  Scott, Gayman W.

    IPC分类号： F01D5/18 ,  B22C9/10

    CPC分类号： B22C9/103 ,  B22C9/04 ,  F01D5/186 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/202 ,  Y02T50/676

    摘要： A turbine engine component, such as a turbine blade, has an airfoil portion (100) having a pressure side wall (106) and a suction side wall (108), a first cooling circuit (110) embedded within the pressure side wall (106), which first cooling circuit (110) has at least two passageways (112,114,116) embedded within the pressure side wall (106), a second cooling circuit (118) embedded within the suction side wall (108), which second cooling circuit (118) has at least two passageways (120,122,124) embedded within the suction side wall (108), at least one cooling fluid supply cavity (140,140') located between the pressure and suction side walls (106,108), each cooling fluid supply cavity (140,140') having at least one projecting portion (144,144',146,146') extending between adjacent ones of the embedded passageways in the first cooling circuit (110) or adjacent ones of the embedded passageways in the second cooling circuit (118), and each projecting portion (144,144',146,146') communicating with at least one film cooling hole (150,152,154,156). A method for forming the turbine blade component is also described.