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    Airfoil thermal management with microcircuit cooling
    6.
    发明公开
    Airfoil thermal management with microcircuit cooling 有权
    与微通道冷却翼热控制

    公开(公告)号：EP1900905A3

    公开(公告)日：2011-06-22

    申请号：EP07253638.6

    申请日：2007-09-13

    申请人： United Technologies Corporation

    发明人： Cunha, Francisco J. ,  Dahmer, Matthew T.

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F05D2260/2214

    摘要： A turbine engine component (100), such as a turbine engine blade, has an airfoil portion (104) with a pressure side wall (106) and a suction side wall (108), a plurality of ribs (110) extending between the pressure side wall (106) and the suction side wall (108), and a plurality of supply cavities (120, 144, 150, 164) located between the ribs (110). The component further has an arrangement for cooling the airfoil portion (104). The cooling arrangement comprises a first cooling circuit (114, 117) embedded within the suction side wall (108) for convectively cooling the suction side wall (108), a second cooling circuit (124, 130) embedded within the pressure side wall (106) for cooling the pressure side wall (106), and a third passageway (122, 128) for increasing a temperature of at least one of the ribs (110) by conduction.

    Turbine blade tip cooling
    7.
    发明公开
    Turbine blade tip cooling 有权
    冷却的涡轮叶片尖端

    公开(公告)号：EP1801351A3

    公开(公告)日：2010-11-24

    申请号：EP06256420.8

    申请日：2006-12-18

    申请人： United Technologies Corporation

    发明人： Cunha, Francisco J. ,  Albert, Jason E.

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  B22C9/10 ,  B22C9/103 ,  F01D5/186 ,  F01D5/20 ,  F05D2230/21 ,  F05D2230/80 ,  F05D2260/202

    摘要： A turbine engine blade (20) has an attachment root (42), a platform (40) outboard of the attachment root (42), and an airfoil (22) extending from the platform (40). The airfoil (22) has pressure and suction sides (34, 36) extending between leading and trailing edges (30, 32). An internal cooling passageway network includes at least one inlet (44) in the root (42) and a plurality of outlets (334, 376) along the airfoil. The passageway network includes a leading spanwise cavity (310) fed by a first trunk (323). A streamwise cavity (324) is inboard of a tip (26) of the airfoil. A spanwise feed cavity (326) feeds the streamwise cavity (324) absent down-pass. A second trunk (327) feeds the spanwise feed cavity (326).

    Turbine element cooling
    8.
    发明公开
    Turbine element cooling 审中-公开
    冷却涡轮机部件

    公开(公告)号：EP1813774A3

    公开(公告)日：2010-11-10

    申请号：EP07250256.0

    申请日：2007-01-23

    申请人： United Technologies Corporation

    发明人： Cunha, Francisco J. ,  Abdel-Messeh, William

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2250/185 ,  F05D2260/202

    摘要： A turbine engine component (10) having improved cooling is provided. The turbine engine component includes an airfoil portion (12) having a leading edge (18), a trailing edge (20), a pressure side (22), a suction side (24), a root (19), and a tip (21), and at least one cooling circuit (26, 42) in a wall of the airfoil portion (12). The at least one cooling circuit (26, 42) has at least one passageway extending between the root (19) and the tip (21). The at least one passageway has an aspect ratio of no greater than 2:1, and preferably substantially unity.

    Airfoil thermal management with microcircuit cooling
    10.
    发明公开
    Airfoil thermal management with microcircuit cooling 有权
    SchaufelblattwärmeregelungmitMikrokanalkühlung

    公开(公告)号：EP1900905A2

    公开(公告)日：2008-03-19

    申请号：EP07253638.6

    申请日：2007-09-13

    申请人： United Technologies Corporation

    发明人： Cunha, Francisco J. ,  Dahmer, Matthew T.

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F05D2260/2214

    摘要： A turbine engine component (100), such as a turbine engine blade, has an airfoil portion (104) with a pressure side wall (106) and a suction side wall (108), a plurality of ribs (110) extending between the pressure side wall (106) and the suction side wall (108), and a plurality of supply cavities (120, 144, 150, 164) located between the ribs (110). The component further has an arrangement for cooling the airfoil portion (104). The cooling arrangement comprises a first cooling circuit (114, 117) embedded within the suction side wall (108) for convectively cooling the suction side wall (108), a second cooling circuit (124, 130) embedded within the pressure side wall (106) for cooling the pressure side wall (106), and a third passageway (122, 128) for increasing a temperature of at least one of the ribs (110) by conduction.

    摘要翻译： 诸如涡轮发动机叶片的涡轮发动机部件（100）具有带有压力侧壁（106）和吸力侧壁（108）的翼型部分（104），多个肋（110）在压力 侧壁（106）和吸力侧壁（108）以及位于肋（110）之间的多个供应腔（120,144,150,164）。 该部件还具有用于冷却翼型件部分（104）的布置。 冷却装置包括嵌入在吸入侧壁（108）内的用于对流冷却吸入侧壁（108）的第一冷却回路（114,117），嵌入压力侧壁（106）内的第二冷却回路（124,130） ）和用于通过传导增加至少一个肋（110）的温度的第三通道（122,128）。