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    Cooled rotor blade with vibration damping device
    1.
    发明专利
    Cooled rotor blade with vibration damping device 未知

    公开(公告)号：AU2004240224A1

    公开(公告)日：2005-08-18

    申请号：AU2004240224

    申请日：2004-12-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND C ,  PROPHETER TRACY A ,  GREGG SHAWN J ,  OTERO EDWIN

    IPC: F01D5/16 ,  F01D5/10 ,  F01D5/18 ,  F01D25/06 ,  F02C7/24

    Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (18), an airfoil (20), and a damper (24). The airfoil (20) has a length, a base (28), a tip (30), a first side wall (36,38), a second side wall (38,36), and at least one cavity (40). The length extends the base (28) and the tip (30). The at least one cavity (40) is disposed between the side walls (36,38), and the channel (42) is defined by a first wall portion (54) and a second wall portion (56). The damper (24), which is selectively received within the channel (42), includes a first bearing surface (80), a second bearing surface (82), a forward surface (76), and an aft surface (78), all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage (92) within the channel (42). The passage (92) has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of the present invention, the damper (24) has an arcuate lengthwise extending centerline (71).

    TURBINE BLADE DAMPER SEAL
    4.
    发明申请
    TURBINE BLADE DAMPER SEAL 审中-公开
    涡轮叶片阻尼器密封

    公开(公告)号：WO2013154657A3

    公开(公告)日：2013-12-05

    申请号：PCT/US2013023132

    申请日：2013-01-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER DANIEL A ,  LANA KYLE CHARLES ,  SANDOVAL JONATHAN PERRY ,  VIRKLER SCOTT DANIEL ,  TARASKEVICH JAIMIE ,  OTERO EDWIN

    IPC: F01D5/26

    CPC classification number: F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  Y02T50/673

    Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

    Abstract translation: 根据本公开的示例性方面，容纳在位于平台和保持架阻尼器密封件之间的涡轮机叶片的空腔中的阻尼器密封件包括中心主体部分，其具有第一端部区域，相对的第二端部 区域和宽度。 阻尼器密封件还包括从中心主体部分的第一端部区域延伸的第一部分，并且第一部分的第一端部区域包括第一向外延伸的突片，其限定第一扩大部分，第一扩大部分具有大于 中心主体部分和从中心主体部分的相对的第二端部区域延伸的第二部分。

    Cooled rotor blade with vibration damping device
    5.
    发明专利
    Cooled rotor blade with vibration damping device 未知

    公开(公告)号：AU2004240224B2

    公开(公告)日：2007-02-08

    申请号：AU2004240224

    申请日：2004-12-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND C ,  GREGG SHAWN J ,  PROPHETER TRACY A ,  OTERO EDWIN

    IPC: F01D5/16 ,  F01D5/10 ,  F01D5/18 ,  F01D25/06

    Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (18), an airfoil (20), and a damper (24). The airfoil (20) has a length, a base (28), a tip (30), a first side wall (36,38), a second side wall (38,36), and at least one cavity (40). The length extends the base (28) and the tip (30). The at least one cavity (40) is disposed between the side walls (36,38), and the channel (42) is defined by a first wall portion (54) and a second wall portion (56). The damper (24), which is selectively received within the channel (42), includes a first bearing surface (80), a second bearing surface (82), a forward surface (76), and an aft surface (78), all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage (92) within the channel (42). The passage (92) has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of the present invention, the damper (24) has an arcuate lengthwise extending centerline (71).

    COOLED ROTOR BLADE WITH VIBRATION DAMPING DEVICE
    6.
    发明专利
    COOLED ROTOR BLADE WITH VIBRATION DAMPING DEVICE 未知

    公开(公告)号：SG113614A1

    公开(公告)日：2005-08-29

    申请号：SG200500637

    申请日：2005-02-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND C ,  OTERO EDWIN ,  GREGG SHAWN J ,  PROPHETER TRACY A

    IPC: F01D5/16 ,  F01D5/10 ,  F01D5/18 ,  F01D25/06

    Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (18), an airfoil (20), and a damper (24). The airfoil (20) has a length, a base (28), a tip (30), a first side wall (36,38), a second side wall (38,36), and at least one cavity (40). The length extends the base (28) and the tip (30). The at least one cavity (40) is disposed between the side walls (36,38), and the channel (42) is defined by a first wall portion (54) and a second wall portion (56). The damper (24), which is selectively received within the channel (42), includes a first bearing surface (80), a second bearing surface (82), a forward surface (76), and an aft surface (78), all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage (92) within the channel (42). The passage (92) has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of the present invention, the damper (24) has an arcuate lengthwise extending centerline (71).

    COOLED ROTOR BLADE WITH VIBRATION DAMPING DEVICE
    7.
    发明专利
    COOLED ROTOR BLADE WITH VIBRATION DAMPING DEVICE 未知

    公开(公告)号：CA2487490A1

    公开(公告)日：2005-08-04

    申请号：CA2487490

    申请日：2004-11-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND C ,  OTERO EDWIN ,  GREGG SHAWN J ,  PROPHETER TRACY A

    IPC: F01D5/16 ,  F01D5/10 ,  F01D5/18 ,  F01D25/06

    Abstract: A rotor blade for a rotor assembly is provided that includes a root, an airfoil, and a damper. The airfoil has a length, a base, a tip, a first side wall, a second side wall and at least one cavity. The length extends the base and the tip. The at least one cavity is disposed between the side walls and the channel is defined by a first wall portion and a second wall portion. The damper, which is selectively received within the channel includes a first bearing surface, a second bearing surface, a forward surfac e and an aft surface, all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage within the channel. The passage has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of t he present invention, the damper has an arcuate lengthwise extending centerline.

    8.
    发明专利
    未知

    公开(公告)号：NO20050623D0

    公开(公告)日：2005-02-04

    申请号：NO20050623

    申请日：2005-02-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND ,  GREGG SHAWN J ,  PROPHETER TRACY ,  OTERO EDWIN

    IPC: F01D5/10 ,  F01D5/16 ,  F01D5/18 ,  F01D25/06 ,  F01D

    Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (18), an airfoil (20), and a damper (24). The airfoil (20) has a length, a base (28), a tip (30), a first side wall (36,38), a second side wall (38,36), and at least one cavity (40). The length extends the base (28) and the tip (30). The at least one cavity (40) is disposed between the side walls (36,38), and the channel (42) is defined by a first wall portion (54) and a second wall portion (56). The damper (24), which is selectively received within the channel (42), includes a first bearing surface (80), a second bearing surface (82), a forward surface (76), and an aft surface (78), all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage (92) within the channel (42). The passage (92) has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of the present invention, the damper (24) has an arcuate lengthwise extending centerline (71).

    AIRFOIL WITH IMPROVED INTERNAL COOLING CHANNEL PEDESTALS
    9.
    发明专利
    AIRFOIL WITH IMPROVED INTERNAL COOLING CHANNEL PEDESTALS 未知

    公开(公告)号：SG11201403624WA

    公开(公告)日：2014-10-30

    申请号：SG11201403624W

    申请日：2013-02-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： OTERO EDWIN

    IPC: F01D25/10 ,  F01D5/18 ,  F02C7/00 ,  F02C7/12

    Abstract: An airfoil for a turbine engine, the airfoil including a first side wall, a second side wall spaced apart from the first side wall, and an internal cooling channel formed between the first side wall and the second side wall. The internal cooling channel includes at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall. The internal cooling channel also includes a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end. At least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end.

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