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    ROTOR ASSEMBLY WITH ACTIVE DAMPING FOR GAS TURBINE ENGINES
    4.
    发明公开
    ROTOR ASSEMBLY WITH ACTIVE DAMPING FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：EP3643880A2

    公开(公告)日：2020-04-29

    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

    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.

    ROTOR ASSEMBLY WITH ACTIVE DAMPING FOR GAS TURBINE ENGINES
    7.
    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.

    SHORT INLET WITH INTEGRATED LINER ANTI-ICING
    9.
    发明公开
    SHORT INLET WITH INTEGRATED LINER ANTI-ICING 审中-公开
    带集成衬里防粘的短入口

    公开(公告)号：EP3236047A1

    公开(公告)日：2017-10-25

    申请号：EP17166941.9

    申请日：2017-04-18

    Applicant: United Technologies Corporation

    Inventor： WELCH, David A.

    IPC: F02C7/045 ,  F02C7/047

    CPC classification number: F02C7/047 ,  F02C7/045 ,  F02C7/24 ,  F02C7/30 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/60 ,  F05D2260/96

    Abstract: A nacelle (62) for a gas turbine engine (20), the nacelle (62) includes an inlet (66) axially forward of a fan section (22). The inlet (66) includes an interior surface (80). A leading edge (72) includes an inlet cavity (70). A first conduit (74) communicates airflow to the inlet cavity (70) for preventing accretion of ice on the leading edge (72). An inlet duct (78) is open to the interior surface (80) aft of the inlet cavity (70). A second conduit (76) is in fluid communication with the first conduit (74) and the inlet duct (78). The second conduit (76) communicates airflow to the inlet duct (78) for generating film heating airflow over the interior surface (80) for preventing ice accretion. A gas turbine engine (20) is also disclosed.

    Abstract translation: 一种用于燃气涡轮发动机（20）的机舱（62），机舱（62）包括轴向位于风扇部分（22）前方的入口（66）。 入口（66）包括内表面（80）。 前缘（72）包括入口腔（70）。 第一导管（74）将气流传送到入口腔（70）以防止前缘（72）上的冰积聚。 入口管道（78）通向入口腔室（70）后部的内表面（80）。 第二导管（76）与第一导管（74）和入口导管（78）流体连通。 第二导管（76）将气流传送到入口导管（78），以在内表面（80）上产生膜加热气流以防止积冰。 燃气涡轮发动机（20）也被公开。

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