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    VARIABLE AREA VANE ENDWALL TREATMENTS
    1.
    发明申请
    VARIABLE AREA VANE ENDWALL TREATMENTS 审中-公开
    可变面积叶片端壁治疗

    公开(公告)号：WO2015099869A3

    公开(公告)日：2015-09-24

    申请号：PCT/US2014061333

    申请日：2014-10-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TEIXEIRA JOHN D ,  GROVER ERIC A ,  SURACE RAYMOND

    IPC: F01D9/02 ,  F01D17/16

    CPC classification number: F01D17/162 ,  F01D5/143 ,  F05D2250/241 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

    Abstract: A gas turbine engine component includes an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one body supported between the outer and inner endwalls for rotation about an axis. The body includes an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap. The outer and inner diameter surfaces and the outer and inner diameter endwalls are configured such that the first and second gaps remain generally constant in size as the body rotates about the axis.

    Abstract translation: 燃气涡轮发动机部件包括外径端壁，在外径端壁径向向内间隔开的内径端壁以及支撑在外端壁和内端壁之间用于围绕轴线旋转的至少一个主体。 所述主体包括外径表面，所述外径表面与所述外径端壁间隔开第一间隙和与所述内径端壁间隔第二间隙的内径表面。 外径和内径表面以及外径和内径端壁被构造成使得当主体围绕轴线旋转时第一和第二间隙的尺寸通常保持恒定。

    VARIABLE AREA TURBINE ARRANGEMENT FOR A GAS TURBINE ENGINE
    2.
    发明申请
    VARIABLE AREA TURBINE ARRANGEMENT FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的可变区涡轮机装置

    公开(公告)号：WO2015069334A3

    公开(公告)日：2015-07-23

    申请号：PCT/US2014049536

    申请日：2014-08-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND

    IPC: F01D17/16 ,  F01D9/02 ,  F02C7/042 ,  F02C7/057

    CPC classification number: F01D17/162 ,  F01D9/06 ,  F05D2220/32

    Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a first turbine section having at least a first variable vane row and a second turbine section downstream from the first turbine section and having at least a second variable vane row. A transition duct is disposed between the first turbine section and the second turbine section.

    Abstract translation: 根据本公开的示例性方面的可变区域涡轮机布置包括第一涡轮部分，其具有至少第一可变叶片排和在第一涡轮部分下游的第二涡轮部分，并且具有至少第二变量 叶片排。 过渡管道设置在第一涡轮部分和第二涡轮部分之间。

    5.
    发明专利
    未知

    公开(公告)号：NO20051543L

    公开(公告)日：2005-11-28

    申请号：NO20051543

    申请日：2005-03-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND ,  PROPHETER TRACY

    IPC: F01D5/16 ,  F01D5/18 ,  F01D5/26 ,  F16F15/12 ,  F01D5/10 ,  F01D5/00

    Abstract: A rotor blade damper (48) is provided that includes a body (58) having a base (60), a tip (62), a first contact surface (64), a second contact surface (66), a trailing edge surface (68), and a leading edge surface (70). The trailing edge and the leading edge surfaces (68,70) extend between the contact surfaces (64,66). The first contact surface (64), second contact surface (66), trailing edge surface (68), and leading edge surface (70) all extend lengthwise between the base (60) and the tip (62). The body (58) includes at least one cooling aperture (82) disposed adjacent the base (60), that has a diameter that is approximately equal to or greater than the width of the trailing edge surface (68) adjacent the tip (62). The body (58) tapers between the base (60) and the tip (62) such that a first widthwise cross-sectional area adjacent the base (60) is greater than a second widthwise cross-sectional area adjacent the tip (62).

    BLADE DAMPER
    6.
    发明专利
    BLADE DAMPER 未知

    公开(公告)号：CA2483071A1

    公开(公告)日：2005-04-08

    申请号：CA2483071

    申请日：2004-09-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： COLON DENNIS I ,  SURACE RAYMOND

    IPC: F01D5/26 ,  F01D5/22 ,  F01D11/00 ,  F04D29/08 ,  F04D29/38 ,  F02C7/28

    Abstract: A turbomachine blade damper has a damper member with first and second dampi ng surfaces far respectively engaging first and second surfaces of adjacent fir st and second blades. The damper has a seal having a first portion engaged in the damper member to resist relative movement of the seal in at least one direction and a second portion engaging at least one of the blades and advantageously forming a seal to resist upstream gas infiltration.

    8.
    发明专利
    未知

    公开(公告)号：NO20051543D0

    公开(公告)日：2005-03-23

    申请号：NO20051543

    申请日：2005-03-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND ,  PROPHETER TRACY

    IPC: F01D5/16 ,  F01D5/18 ,  F01D5/26 ,  F16F15/12 ,  F03B

    Abstract: A rotor blade damper (48) is provided that includes a body (58) having a base (60), a tip (62), a first contact surface (64), a second contact surface (66), a trailing edge surface (68), and a leading edge surface (70). The trailing edge and the leading edge surfaces (68,70) extend between the contact surfaces (64,66). The first contact surface (64), second contact surface (66), trailing edge surface (68), and leading edge surface (70) all extend lengthwise between the base (60) and the tip (62). The body (58) includes at least one cooling aperture (82) disposed adjacent the base (60), that has a diameter that is approximately equal to or greater than the width of the trailing edge surface (68) adjacent the tip (62). The body (58) tapers between the base (60) and the tip (62) such that a first widthwise cross-sectional area adjacent the base (60) is greater than a second widthwise cross-sectional area adjacent the tip (62).

    9.
    发明专利
    未知

    公开(公告)号：NO20050623L

    公开(公告)日：2005-08-05

    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 ,  F01D5/18 ,  F01D25/06 ,  F01D5/16 ,  F01D5/12 ,  F01D5/00

    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).

    10.
    发明专利
    未知

    公开(公告)号：NO20044251L

    公开(公告)日：2005-04-11

    申请号：NO20044251

    申请日：2004-10-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND ,  COLON DENNIS I

    IPC: F01D5/22 ,  F01D11/00 ,  F04D29/08 ,  F01D5/26 ,  F04D29/38 ,  F01D5/10 ,  F01D5/00 ,  F02C6/12

    Abstract: A turbomachine blade damper has a damper member (52) with first and second (58,60) damping surfaces for respectively engaging first and second surfaces of adjacent first and second blades (20). The damper has a seal (70) having a first portion (22) engaged in the damper member (58) to resist relative movement of the seal in at least one direction and a second portion (74) engaging at least one of the blades and advantageously forming a seal to resist upstream gas infiltration.

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