Compressor blade for a gas turbine engine

    公开(公告)号:US10215189B2

    公开(公告)日:2019-02-26

    申请号:US15208047

    申请日:2016-07-12

    Abstract: 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, the scalable table selected from the group of tables consisting of 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.

    AIRFOIL SHAPE FOR A COMPRESSOR
    3.
    发明申请

    公开(公告)号:US20170067479A1

    公开(公告)日:2017-03-09

    申请号:US14845421

    申请日:2015-09-04

    CPC classification number: F04D29/324

    Abstract: 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.

    COMPRESSOR BLADE FOR A GAS TURBINE ENGINE
    5.
    发明申请

    公开(公告)号:US20180017076A1

    公开(公告)日:2018-01-18

    申请号:US15208047

    申请日:2016-07-12

    Abstract: 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, the scalable table selected from the group of tables consisting of 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.

    COMPRESSOR BLADE FOR A GAS TURBINE ENGINE
    6.
    发明申请

    公开(公告)号:US20180017070A1

    公开(公告)日:2018-01-18

    申请号:US15208019

    申请日:2016-07-12

    CPC classification number: F04D29/324 F05B2220/302 F05B2240/301 F05B2250/70

    Abstract: 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, the scalable table selected from the group of tables consisting of 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.

    Compressor blade for a gas turbine engine

    公开(公告)号:US10197066B2

    公开(公告)日:2019-02-05

    申请号:US15208019

    申请日:2016-07-12

    Abstract: 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, the scalable table selected from the group of tables consisting of 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.

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