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    GAS TURBINE ENGINE AIRFOIL
    21.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 审中-公开

    公开(公告)号：US20200149545A1

    公开(公告)日：2020-05-14

    申请号：US16741918

    申请日：2020-01-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: F04D29/38 ,  F04D29/32 ,  F02K3/06 ,  F02C7/36 ,  F02C3/04 ,  F01D25/24 ,  F01D17/16 ,  F01D5/14 ,  F04D29/54

    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 provided in the compressor section outside the high pressure compressor section 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 stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle has a positive slope from 20% span to 100% span.

    GAS TURBINE ENGINE AIRFOIL
    22.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 审中-公开

    公开(公告)号：US20200096005A1

    公开(公告)日：2020-03-26

    申请号：US16681187

    申请日：2019-11-12

    Applicant: United Technologies Corporation

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

    IPC: F04D29/38 ,  F01D5/14 ,  F01D9/04 ,  F02C3/04 ,  F04D29/32 ,  F04D29/54 ,  F04D29/56

    Abstract: A gas turbine engine includes a combustor section, a compressor section, and a turbine section. A high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. A low pressure compressor is counter-rotating relative to the fan blades and downstream from the fan section. The airfoil outside of the compressor section is rotatable relative to an engine static structure. The airfoil includes pressure and suction sides extending from a 0% span position to a 100% span position. A relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span. The leading edge angle is defined by a tangential plane normal to an engine axis and a line tangent to a camber mean line at the leading edge.

    Gas turbine engine airfoil frequency design
    28.
    发明授权
    Gas turbine engine airfoil frequency design 有权

    公开(公告)号：US10815826B1

    公开(公告)日：2020-10-27

    申请号：US15868424

    申请日：2018-01-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William R. Edwards ,  Steven J. Feigleson ,  Kate Hudon

    IPC: F01D9/02 ,  F01D25/04 ,  F02C3/06 ,  F04D29/54 ,  F04D29/66 ,  F02K3/06 ,  F01D5/16 ,  F01D5/14 ,  F01D5/34

    Abstract: An airfoil extends in a radial direction a span in a range 3.97-4.27 inch (100.9-108.6 mm). A chord length extends in a chordwise direction from a leading edge to a trailing edge at 50% span in a range 1.28-1.58 inch (32.4-40.0 mm). The airfoil includes at least two of a first mode with a frequency of 243±10% Hz, a second mode with a frequency of 374±10% Hz, a third mode with a frequency of 741±10% Hz, a fourth mode with a frequency of 1198±10% Hz, a fifth mode with a frequency of 1663±10% Hz, a sixth mode with a frequency of 2411±10% Hz, a seventh mode with a frequency of 3734±10% Hz, an eighth mode with a frequency of 6738±10% Hz and a ninth mode with a frequency of 8977±10% Hz.

    Gas turbine engine airfoil frequency design
    29.
    发明授权
    Gas turbine engine airfoil frequency design 有权

    公开(公告)号：US10787910B1

    公开(公告)日：2020-09-29

    申请号：US15868465

    申请日：2018-01-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William R. Edwards ,  Steven J. Feigleson ,  Kate Hudon

    IPC: F01D9/02 ,  F01D5/16 ,  F01D5/00 ,  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 2.59-2.89 inch (65.7-73.3 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 1.35-1.65 inch (34.4-42.0 mm). The airfoil element includes at least two of a first mode with a frequency of 2241±10% Hz, a second mode with a frequency of 3598±10% Hz and a third mode with a frequency of 6212±10% Hz.

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