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    GAS TURBINE ENGINE AIRFOIL
    2.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 审中-公开

    公开(公告)号：US20200149544A1

    公开(公告)日：2020-05-14

    申请号：US16740817

    申请日：2020-01-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Edward J. Gallagher ,  Lisa I. Brilliant ,  Joseph C. Straccia ,  Stanley J. Balamucki ,  Mark A. Stephens ,  Kate Hudon

    IPC: F04D29/32 ,  F04D29/38 ,  F02K3/06 ,  F02C7/36 ,  F02C3/04 ,  F02K3/072 ,  F01D17/16 ,  F01D5/14

    Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle within the range of 80% span to 100% span. The camber angle is less than 20° within the entire range of 40% span to 100% span.

    Gas turbine engine airfoil frequency design
    6.
    发明授权
    Gas turbine engine airfoil frequency design 有权

    公开(公告)号：US10767488B1

    公开(公告)日：2020-09-08

    申请号：US15871197

    申请日：2018-01-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William R. Edwards ,  Stephen W. Milks ,  Steven J. Feigleson ,  Mark A. Stephens ,  Joseph C. Straccia

    IPC: F01D5/16 ,  F01D9/04 ,  F01D5/14 ,  F02C3/06

    Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and is joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.18-3.48 inch (80.7-88.4 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.17-1.47 inch (29.6-37.3 mm). The airfoil element includes at least two of a first mode with a frequency of 333±10% Hz, a second mode with a frequency of 1554±10% Hz, a third mode with a frequency of 2356±10% Hz, a fourth mode with a frequency of 2830±10% Hz, a fifth mode with a frequency of 4075±10% Hz and a sixth mode with a frequency of 5239±10% Hz.

    Gas turbine engine airfoil frequency design
    7.
    发明授权
    Gas turbine engine airfoil frequency design 有权

    公开(公告)号：US10760429B1

    公开(公告)日：2020-09-01

    申请号：US15868312

    申请日：2018-01-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Xuedong Zhou ,  Evan K. Fink ,  Joseph C. Straccia ,  Joseph Wieser ,  Konstantinos Panagiotis Giannakopoulos

    IPC: F01D5/00 ,  F01D5/16 ,  F01D5/34 ,  F01D9/04 ,  F02C3/06

    Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.45-3.75 inch (87.6-95.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.55-1.85 inch (39.4-47.0 mm). The airfoil element includes at least two of a first mode with a frequency of 424±10% Hz, a second mode with a frequency of 1401±10% Hz, a third mode with a frequency of 1770±10% Hz, a fourth mode with a frequency of 3336±10% Hz, a fifth mode with a frequency of 3378±10% Hz and a sixth mode with a frequency of 4141±10% Hz.

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