Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the fourth stage of a turbine
    1.
    发明授权
    Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the fourth stage of a turbine 有权
    用于涡轮叶片的优化的空气动力学特性,特别是用于涡轮机第四级的喷嘴

    公开(公告)号:US08734113B2

    公开(公告)日:2014-05-27

    申请号:US13171561

    申请日:2011-06-29

    IPC分类号: F01D9/02 F01D9/04

    摘要: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

    摘要翻译: 当冷和处于非涂覆状态时,空气动力学特性与由表1中给出的笛卡尔坐标X,Y,Z'确定的标称轮廓基本相同,其中坐标Z'是商D / H,其中D 是从位于标称轮廓底部的第一参考平面P0考虑的点的距离,H是从第一参考平面测量到第二参考平面P1的所述剖面的高度。 测量D和H相对于涡轮机的轴线径向地获得,而X坐标是在涡轮的轴向方向上测量的。

    Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the fourth stage of a turbine
    2.
    发明授权
    Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the fourth stage of a turbine 有权
    优化用于涡轮机叶片的空气动力学特性,特别是用于涡轮机第四级的旋转轮

    公开(公告)号:US08647069B2

    公开(公告)日:2014-02-11

    申请号:US13171758

    申请日:2011-06-29

    IPC分类号: F01D5/14 B64C27/46

    摘要: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

    摘要翻译: 当冷和处于非涂覆状态时,空气动力学特性与由表1中给出的笛卡尔坐标X,Y,Z'确定的标称轮廓基本相同,其中坐标Z'是商D / H,其中D 是从位于标称轮廓底部的第一参考平面P0考虑的点的距离,H是从第一参考平面测量到第二参考平面P1的所述剖面的高度。 测量D和H相对于涡轮机的轴线径向地获得,而X坐标是在涡轮的轴向方向上测量的。

    Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the second stage of a turbine
    3.
    发明授权
    Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the second stage of a turbine 有权
    涡轮机叶片的优化的空气动力学特性,特别是用于涡轮机第二级的转轮

    公开(公告)号:US08757983B2

    公开(公告)日:2014-06-24

    申请号:US13171586

    申请日:2011-06-29

    IPC分类号: F01D5/14

    摘要: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

    摘要翻译: 当冷和处于非涂覆状态时,空气动力学特性与由表1中给出的笛卡尔坐标X,Y,Z'确定的标称轮廓基本相同,其中坐标Z'是商D / H,其中D 是从位于标称轮廓底部的第一参考平面P0考虑的点的距离,H是从第一参考平面测量到第二参考平面P1的所述剖面的高度。 测量D和H相对于涡轮机的轴线径向地获得,而X坐标是在涡轮的轴向方向上测量的。

    DEVICE AND METHOD FOR MEASURING THE LEAKAGE RATE FROM REFERENCE PRESSURE LINES ONBOARD AN AIRCRAFT
    4.
    发明申请
    DEVICE AND METHOD FOR MEASURING THE LEAKAGE RATE FROM REFERENCE PRESSURE LINES ONBOARD AN AIRCRAFT 有权
    用于测量飞机上参考压力线的泄漏速率的装置和方法

    公开(公告)号:US20140053635A1

    公开(公告)日:2014-02-27

    申请号:US13878056

    申请日:2011-10-04

    IPC分类号: G01M3/26

    摘要: A device for testing pneumatic circuits and for measuring the leakage rate from reference pressure lines onboard an aircraft, connected to a plenum chamber. The device includes a multi-pressure system, comprising several sensors each connected to a reference pressure line, first solenoid valves arranged on the input channels to this multi-pressure system, and connected to the reference pressure lines through first connectors, second solenoid valves arranged on the reference pressure lines, a pressure controller module that is connected to all the first solenoid valves through a second connector, an electronic board that controls the solenoid valves and calibration of the multi-pressure system, a control device. The invention also relates to a method making use of this device.

    摘要翻译: 一种用于测试气动回路并测量与连接到增压室的飞机上的参考压力管线的泄漏速率的装置。 该装置包括多压力系统,其包括多个传感器,每个传感器各自连接到参考压力管线,第一电磁阀布置在输入通道上并连接到该多压力系统,并通过第一连接器连接到参考压力管线,第二电磁阀设置 在参考压力线上,通过第二连接器连接到所有第一电磁阀的压力控制器模块,控制电磁阀的电子板和多压力系统的校准,控制装置。 本发明还涉及利用该装置的方法。

    Assist circuits for SRAM testing
    5.
    发明授权
    Assist circuits for SRAM testing 有权
    辅助电路进行SRAM测试

    公开(公告)号:US09418759B2

    公开(公告)日:2016-08-16

    申请号:US14270555

    申请日:2014-05-06

    摘要: Assist circuits for SRAM memory tests allow voltage scaling in low-power SRAMs. Word line level reduction (WLR) and negative bit line (NBL) boost assist techniques improve read stability and write margin of SRAM core-cells, respectively, when the memory operates at a lowered supply voltage. Assist circuits are activated at particular points in the memory cell circuit. The assist circuits are selectively activated for modifying the voltage along particular circuit elements to identify the potential defects that might be otherwise masked until substantially large. A March test invokes elements for activating the assist circuits to identify defects and indicate functional fault models (FFMs) associated with the defects.

    摘要翻译: 用于SRAM存储器测试的辅助电路允许在低功耗SRAM中进行电压调节。 当存储器工作在降低的电源电压时,字线电平降低(WLR)和负位线(NBL)升压辅助技术分别提高SRAM核心单元的读取稳定性和写入裕度。 辅助电路在存储单元电路中的特定点被激活。 辅助电路被选择性地激活以修改沿着特定电路元件的电压,以识别直到基本上大的可能被掩蔽的潜在缺陷。 March测试调用激活辅助电路以识别缺陷的元件,并指出与故障相关的功能故障模型(FFM)。

    ASSIST CIRCUITS FOR SRAM TESTING
    6.
    发明申请
    ASSIST CIRCUITS FOR SRAM TESTING 有权
    辅助电路用于SRAM测试

    公开(公告)号:US20150325313A1

    公开(公告)日:2015-11-12

    申请号:US14270555

    申请日:2014-05-06

    IPC分类号: G11C29/04 G11C11/419

    摘要: Assist circuits for SRAM memory tests allow voltage scaling in low-power SRAMs. Word line level reduction (WLR) and negative bit line (NBL) boost assist techniques improve read stability and write margin of SRAM core-cells, respectively, when the memory operates at a lowered supply voltage. Assist circuits are activated at particular points in the memory cell circuit. The assist circuits are selectively activated for modifying the voltage along particular circuit elements to identify the potential defects that might be otherwise masked until substantially large. A March test invokes elements for activating the assist circuits to identify defects and indicate functional fault models (FFMs) associated with the defects.

    摘要翻译: 用于SRAM存储器测试的辅助电路允许在低功耗SRAM中进行电压调节。 当存储器工作在降低的电源电压时,字线电平降低(WLR)和负位线(NBL)升压辅助技术分别提高SRAM核心单元的读取稳定性和写入裕度。 辅助电路在存储单元电路中的特定点被激活。 辅助电路被选择性地激活以修改沿着特定电路元件的电压,以识别直到基本上大的可能被掩蔽的潜在缺陷。 March测试调用激活辅助电路以识别缺陷的元件,并指出与缺陷相关的功能故障模型(FFM)。

    Laminated fabric with uniform pattern of adhesive securement and
garments made therefrom
    8.
    发明授权
    Laminated fabric with uniform pattern of adhesive securement and garments made therefrom 失效
    具有均匀图案的粘合剂固定和由其制成的衣服的层压织物

    公开(公告)号:US5916829A

    公开(公告)日:1999-06-29

    申请号:US616080

    申请日:1996-03-14

    摘要: A fabric laminate (10) comprises first and second stretch fabrics (11 and 12) having an intermediate adhesive securement layer (13) between them. The adhesive securement layer (13) is in the form of a regularly repeated pattern which comprises an array of aligned adhesive elements (14) arranged in successive generally horizontally and vertically extending rows. The array of adhesive elements (14) is capable of offering resistance to elongation as the laminate (10) is subjected to distortion, with the pattern having a differential elongation characterized as offering different magnitudes of resistance to elongation when the fabric laminate (10) is subjected to distortion in selected different directions. The adhesive securement layer (13) is predeterminedly oriented in accordance with its differential elongation and the stretch characteristics of fabrics (11,12) such that the resistance to elongation offered by the laminate (10) is determined by the pattern and orientation of the individual adhesive elements (14) in conjunction with the stretch characteristics of the fabrics (11,12). The laminate (10) may be employed to reinforce items of clothing, particularly underwear and the like.

    摘要翻译: 织物层压板(10)包括在它们之间具有中间粘合剂固定层(13)的第一和第二弹性织物(11和12)。 粘合剂固定层(13)是规则重复图案的形式,其包括排列成连续大致水平和垂直延伸的行的排列的粘合元件阵列(14)。 粘合剂元件(14)的阵列能够在叠层(10)受到变形时提供抗延伸性,其中图案具有差异伸长率,其特征在于当织物层压体(10)为 在选定的不同方向进行变形。 粘合固定层(13)根据其不同的伸长率和织物(11,12)的拉伸特性被预定取向,使得由层压体(10)提供的抗拉伸性由单独的图案和取向决定 粘合元件(14)与织物(11,12)的拉伸特性相结合。 层压材料(10)可用于加强衣物,特别是内衣等。

    Device and method for measuring the leakage rate from reference pressure lines onboard an aircraft
    9.
    发明授权
    Device and method for measuring the leakage rate from reference pressure lines onboard an aircraft 有权
    用于测量飞机上参考压力线的泄漏速率的装置和方法

    公开(公告)号:US09316561B2

    公开(公告)日:2016-04-19

    申请号:US13878056

    申请日:2011-10-04

    摘要: A device for testing pneumatic circuits and for measuring the leakage rate from reference pressure lines onboard an aircraft, connected to a plenum chamber. The device includes a multi-pressure system, comprising several sensors each connected to a reference pressure line, first solenoid valves arranged on the input channels to this multi-pressure system, and connected to the reference pressure lines through first connectors, second solenoid valves arranged on the reference pressure lines, a pressure controller module that is connected to all the first solenoid valves through a second connector, an electronic board that controls the solenoid valves and calibration of the multi-pressure system, a control device. The invention also relates to a method making use of this device.

    摘要翻译: 一种用于测试气动回路并测量与连接到增压室的飞机上的参考压力管线的泄漏速率的装置。 该装置包括多压力系统,其包括多个传感器,每个传感器各自连接到参考压力管线,第一电磁阀布置在输入通道上并连接到该多压力系统,并通过第一连接器连接到参考压力管线,第二电磁阀设置 在参考压力线上,通过第二连接器连接到所有第一电磁阀的压力控制器模块,控制电磁阀的电子板和多压力系统的校准,控制装置。 本发明还涉及利用该装置的方法。