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    COMBUSTOR FOR GAS TURBINE ENGINE
    1.
    发明专利
    COMBUSTOR FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：JP2003185139A

    公开(公告)日：2003-07-03

    申请号：JP2002354301

    申请日：2002-12-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BURD STEVEN W ,  SISKIND KENNETH S ,  GRAVES CHARLES B

    IPC: F23R3/42 ,  F23M5/02 ,  F23R3/00 ,  F23R3/06 ,  F23R3/60

    Abstract: PROBLEM TO BE SOLVED: To provide a combustor capable of improving a heat transfer, hardly increasing a pressure drop. SOLUTION: This combustor for gas turbine engine comprises a plurality of liner segments 12 and a support shell. The support shell comprises an inner surface, an outer surface, a plurality of mounting holes, and a plurality of impingement cooling holes extendedly passed through the support shell. Each of the liner segments 12 comprises a panel 24 and a plurality of mounting studs 32. The panel 24 comprises a front surface, a rear surface 36, and a plurality of cooling holes 38 extendedly passed through these surfaces. The rear surface 36 of the panel 24 comprises a surface profile for preventing the drop of a pressure passing in the combustor from substantially increasing and increasing the heat transfer of the liner segments 12. COPYRIGHT: (C)2003,JPO

    SEAL WITH NON-METALLIC INTERFACE
    3.
    发明申请
    SEAL WITH NON-METALLIC INTERFACE 审中-公开
    密封非金属界面

    公开(公告)号：WO2014007891A2

    公开(公告)日：2014-01-09

    申请号：PCT/US2013034304

    申请日：2013-03-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BURD STEVEN W ,  BURSEY ROGER W ,  MARTINEZ GONZALO F ,  HARRIS-MILLER MEGGAN H

    CPC classification number: F16J15/0887 ,  F01D15/12 ,  F02C3/067 ,  F02C7/36 ,  F02K3/072 ,  Y02T50/672

    Abstract: A seal for use between a first duct and a second duct and, the ducts having relative motion therebetween, includes a first plurality of fingers for attachment to the first duct to be disposed about one of the first duct and the second duct, a seal land attaching to about an other of the first duct and the second duct, and a seal attaching to the seal land and in contact with the plurality of fingers wherein one of the plurality of fingers and the seal is metallic and an other of the seal land or the plurality of fingers is non-metallic.

    Abstract translation: 一种在第一管道和第二管道之间使用的密封件，并且其间具有相对运动的管道包括用于附接到第一管道的第一多个指状物，以围绕第一管道和第二管道中的一个设置;密封区域 附接到所述第一管道和所述第二管道中的另一个，以及附接到所述密封接合面并与所述多个指状物接触的密封件，其中所述多个指状物和所述密封件中的一个是金属的，并且所述密封区域中的另一个 多个手指是非金属的。

    4.
    发明专利
    未知

    公开(公告)号：AT383211T

    公开(公告)日：2008-01-15

    申请号：AT03252688

    申请日：2003-04-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BURD STEVEN W

    IPC: B22C9/04 ,  F02C7/00 ,  B22C9/10 ,  B22C9/24

    Abstract: A method for casting a workpiece comprising the steps of applying a protective coating (21) to a base core (10) the base core comprising, a metal strip (19) comprising a generally planar expanse, a plurality of tabs (17) arranged in a pattern upon the metal strip each of the tabs comprising a base end (11), a terminus end (13), and a tab shaft (15) extending from the base end to the terminus end wherein each of the tabs is angularly displaceable about each the base end of the tabs, injecting a molding substance about the tabs of the base core, encapsulating the base core in a shell (23), removing the molding substance, casting the base core, and removing the base core.

    FAN NACELLE INLET FLOW CONTROL
    5.
    发明申请
    FAN NACELLE INLET FLOW CONTROL 审中-公开
    风扇入口流量控制

    公开(公告)号：WO2015130384A3

    公开(公告)日：2015-11-05

    申请号：PCT/US2014070039

    申请日：2014-12-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BURD STEVEN W

    IPC: F02C7/057 ,  F02C7/047 ,  F02K3/06

    CPC classification number: F02K3/075 ,  F01D25/02 ,  F02C3/04 ,  F02C7/047 ,  F02C7/057 ,  F02K3/06 ,  F04D29/522 ,  F04D29/541 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/17

    Abstract: The present disclosure relates generally to a system for fan nacelle inlet flow control in a gas turbine engine, the nacelle comprising a nacelle inlet cowl including an inlet lip disposed at a leading edge of the nacelle inlet cowl, an inner surface extending aft from the inlet lip, and an outer surface extending aft from the inlet lip and positioned radially outward of the inner surface; and at least one flow control passage extending through the nacelle inlet cowl, each of the at least one flow control passage including a flow control passage inlet, disposed on the inlet lip, and a flow control passage outlet; wherein air may flow into the flow control passage inlet, through the flow control passage, and exits the flow control passage outlet.

    Abstract translation: 本公开总体上涉及一种用于燃气涡轮发动机中的风扇机舱入口流量控制的系统，所述机舱包括机舱入口罩，其包括设置在所述机舱进气罩的前缘处的入口唇缘，从所述入口向后延伸的内表面 唇缘和从入口唇缘向后延伸并且位于内表面的径向外侧的外表面; 以及延伸穿过所述机舱入口前罩的至少一个流量控制通道，所述至少一个流量控制通道中的每一个包括设置在所述入口唇缘上的流量控制通道入口和流量控制通道出口; 其中空气可以通过流量控制通道流入流量控制通道入口，并且离开流量控制通道出口。

    9.
    发明专利
    未知

    公开(公告)号：DE60318515D1

    公开(公告)日：2008-02-21

    申请号：DE60318515

    申请日：2003-04-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BURD STEVEN W

    IPC: B22C9/04 ,  F02C7/00 ,  B22C9/10 ,  B22C9/24

    Abstract: A method for casting a workpiece comprising the steps of applying a protective coating (21) to a base core (10) the base core comprising, a metal strip (19) comprising a generally planar expanse, a plurality of tabs (17) arranged in a pattern upon the metal strip each of the tabs comprising a base end (11), a terminus end (13), and a tab shaft (15) extending from the base end to the terminus end wherein each of the tabs is angularly displaceable about each the base end of the tabs, injecting a molding substance about the tabs of the base core, encapsulating the base core in a shell (23), removing the molding substance, casting the base core, and removing the base core.

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