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    PMC LAMINATE EMBEDDED HYPOTUBE LATTICE
    2.
    发明申请
    PMC LAMINATE EMBEDDED HYPOTUBE LATTICE 审中-公开
    PMC LAMINATE嵌入式HYPOTUBE LATTICE

    公开(公告)号：WO2014014550A1

    公开(公告)日：2014-01-23

    申请号：PCT/US2013/039637

    申请日：2013-05-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： STILLIN, Nicholas D. ,  GLASPEY, James ,  SMITH, Scott A.

    IPC: F01D5/12 ,  F01D5/14 ,  F02C7/00 ,  F02C3/00

    CPC classification number: F01D5/282 ,  F01D21/003 ,  F05D2270/301

    Abstract: A gas turbine engine component such as a laminate airfoil having a static pressure transducer and having a plurality of structural fiber layers bonded with a polymer matrix composite. The transducer includes a lattice formed from a plurality of hypotubes aligned in a first direction and a plurality of reinforcing wires aligned substantially perpendicular to the hypotubes. The lattice is placed between at least some of the structural fiber layers prior to thermally processing into a cured polymer matrix laminate composite.

    Abstract translation: 一种燃气涡轮发动机部件，例如具有静压传感器并具有多个与聚合物基质复合材料结合的结构纤维层的层压翼型件。 换能器包括由沿第一方向排列的多个海波形成的格子和基本上垂直于海波管排列的多个增强线。 在热处理成固化的聚合物基质层压复合材料之前，将晶格放置在至少一些结构纤维层之间。

    HYBRID AIRFOIL FOR GAS TURBINE ENGINES
    4.
    发明公开
    HYBRID AIRFOIL FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：EP3643881A3

    公开(公告)日：2020-06-24

    申请号：EP19203641.6

    申请日：2019-10-16

    Applicant: United Technologies Corporation

    Inventor： HUSBAND, Jason ,  GLASPEY, James

    IPC: F01D5/30 ,  F01D5/28 ,  F01D5/14

    Abstract: An airfoil (66, 166, 266) for a gas turbine engine includes an airfoil section (66A, 166A, 266A) that extends from a root section (66B, 266B). The airfoil section (66A, 166A, 266A) extends between a leading edge (LE) and a trailing edge (TE) in a chordwise direction (C) and extends between a tip portion (66C, 266C) and the root section (66B, 266B) in a radial direction (R). The airfoil section (66A, 166A, 266A) defines a pressure side (P) and a suction side (S) separated in a thickness direction (T). The airfoil section (66A, 166A, 266A) includes a metallic sheath (72, 172, 272) that receives a composite core (74, 174, 274). The core (74, 174, 274) includes first and second ligaments (76A, 76B) received in respective internal channels (72C, 72D, 172C, 172D) defined by the sheath (72, 172, 272) such that the first and second ligaments (76A, 76B) are spaced apart along the root section (66B, 266B) with respect to the chordwise direction (C). Each one of the first and second ligaments (76A, 76B) includes at least one interface portion (78, 178, 278) in the root section (66B, 266B), and at least one interface portion (78, 178, 278) of the first ligament (76A, 76B) and the at least one interface portion (78, 178, 278) of the second ligament (76A, 76B) define respective sets of bores (85) aligned to receive a common retention pin (68, 168).

    CONICAL FAN HUB AND METHOD FOR REDUCING BLADE OFF LOADS
    5.
    发明公开
    CONICAL FAN HUB AND METHOD FOR REDUCING BLADE OFF LOADS 审中-公开

    公开(公告)号：EP3450688A1

    公开(公告)日：2019-03-06

    申请号：EP18191569.5

    申请日：2018-08-29

    Applicant: United Technologies Corporation

    Inventor： HUSBAND, Jason ,  GLASPEY, James

    IPC: F01D5/30

    Abstract: A conical hub (90) for a fan (42) of a gas turbine engine (20) is provided. The conical hub (90) having: a plurality of attachment features (94) located on an outer circumferential surface (93) of the conical hub (90), wherein at least some of the plurality attachment features (94) are axially aligned with each other and at least some of the plurality of attachment features (94) are off set from each other, and wherein each of the plurality of attachment features (94) have an opening (100) configured to receive a portion of a pin (98); and the outer circumferential surface (93) of the conical hub (90) increases in diameter with respect to an axis of the conical hub (90) in a forward to aft direction of the conical hub (90).

    ROTOR ASSEMBLY WITH ACTIVE DAMPING FOR GAS TURBINE ENGINES
    6.
    发明公开
    ROTOR ASSEMBLY WITH ACTIVE DAMPING FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：EP3643880A3

    公开(公告)日：2020-08-12

    申请号：EP19203692.9

    申请日：2019-10-16

    Applicant: United Technologies Corporation

    Inventor： HUSBAND, Jason ,  GLASPEY, James ,  WELCH, David A.

    IPC: F01D5/14 ,  F01D5/28 ,  F01D5/30 ,  F01D5/10

    Abstract: An airfoil (66, 166, 266, 366, 466, 566, 566', 666, 766) for a gas turbine engine (20) includes an airfoil section (66A, 166A, 266A, 366A, 466A, 566A, 666A, 766A) that extends from a root section (66B, 266B, 366B, 466B, 566B, 666B, 766B). The airfoil section (66A... 766A) extends between a leading edge (LE) and a trailing edge (TE) in a chordwise direction (C) and extends between a tip portion (66C, 266C, 466C, 766C) and the root section (66B...766B) in a radial direction (R). The airfoil section (66A... 766A) defines a pressure side (P) and a suction side (S) separated in a thickness direction (T), and the airfoil section (66A...766A) includes a metallic sheath (72, 172, 272, 372, 472, 572, 672) that defines an internal cavity receiving a composite core (74, 174, 274, 474, 574, 774). The root section (66B...766B) defines at least one bore (85, 485) dimensioned to receive a retention pin (68, 168, 368, 468, 568, 668). At least one damping element (487, 487', 587, 587', 687, 787) is received in the internal cavity and that selectively causes the airfoil section (66A...766A) to stiffen.

    HYBRID AIRFOIL FOR GAS TURBINE ENGINES
    8.
    发明公开
    HYBRID AIRFOIL FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：EP3643881A2

    公开(公告)日：2020-04-29

    申请号：EP19203641.6

    申请日：2019-10-16

    Applicant: United Technologies Corporation

    Inventor： HUSBAND, Jason ,  GLASPEY, James

    IPC: F01D5/30 ,  F01D5/28 ,  F01D5/14

    Abstract: An airfoil (66, 166, 266) for a gas turbine engine includes an airfoil section (66A, 166A, 266A) that extends from a root section (66B, 266B). The airfoil section (66A, 166A, 266A) extends between a leading edge (LE) and a trailing edge (TE) in a chordwise direction (C) and extends between a tip portion (66C, 266C) and the root section (66B, 266B) in a radial direction (R). The airfoil section (66A, 166A, 266A) defines a pressure side (P) and a suction side (S) separated in a thickness direction (T). The airfoil section (66A, 166A, 266A) includes a metallic sheath (72, 172, 272) that receives a composite core (74, 174, 274). The core (74, 174, 274) includes first and second ligaments (76A, 76B) received in respective internal channels (72C, 72D, 172C, 172D) defined by the sheath (72, 172, 272) such that the first and second ligaments (76A, 76B) are spaced apart along the root section (66B, 266B) with respect to the chordwise direction (C). Each one of the first and second ligaments (76A, 76B) includes at least one interface portion (78, 178, 278) in the root section (66B, 266B), and at least one interface portion (78, 178, 278) of the first ligament (76A, 76B) and the at least one interface portion (78, 178, 278) of the second ligament (76A, 76B) define respective sets of bores (85) aligned to receive a common retention pin (68, 168).

    PINNED AIRFOIL FOR GAS TURBINE ENGINES
    10.
    发明公开
    PINNED AIRFOIL FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：EP3643878A2

    公开(公告)日：2020-04-29

    申请号：EP19203572.3

    申请日：2019-10-16

    Applicant: United Technologies Corporation

    Inventor： HUSBAND, Jason ,  GLASPEY, James

    IPC: F01D5/14 ,  F01D5/28 ,  F01D5/30

    Abstract: An airfoil (66, 166, 266, 366, 466, 566) for a gas turbine engine (20) includes an airfoil section (66A, 166A, 266A, 466A, 566A) that extends from a root section (66B, 266B, 466B, 566B). The airfoil section (66A...566A) extends between a leading edge (LE) and a trailing edge (TE) in a chordwise direction (C) and extends between a tip portion (66C, 266C) and the root section (66B, 266B, 466B, 566B) in a radial direction (R), and the airfoil section (66A...566A) defines a pressure side (P) and a suction side (S) separated in a thickness direction (T). The airfoil section (66A...566A) includes a metallic sheath (72, 172, 272, 472, 572) that receives a composite core (74, 174, 274), and the core (74, 174, 274) includes first and second ligaments (76A, 76B) received in respective internal channels (72C, 72D, 172C, 172D) defined by the sheath (72...572) such that the first and second ligaments (76...476) are spaced apart along the root section (66B, 266B, 466B, 566B) with respect to the chordwise direction (C). The first and second ligaments define respective sets of bores (85), and the respective sets of bores (85) are aligned to receive a common set of retention pins (468).

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