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    Row of long and short chord length turbine airfoils
    4.
    发明公开
    Row of long and short chord length turbine airfoils 审中-公开
    涡轮机叶片排由具有长和短的弦长叶片的

    公开(公告)号：EP1424467A3

    公开(公告)日：2006-09-27

    申请号：EP03257438.6

    申请日：2003-11-26

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Turner, Mark Graham ,  Cedar, Richard David ,  Orkwis, Paul David

    IPC分类号： F01D5/14

    CPC分类号： F01D5/142 ,  F01D5/141 ,  F01D9/041 ,  F05D2240/12 ,  F05D2250/34 ,  F05D2250/70 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    摘要： A gas turbine engine turbine stage has an annular row of turbine airfoils including a first plurality (41) of first airfoils (44) having a first chord length (CL1) and a second plurality (43) of second airfoils (46) having a second chord length (CL2) shorter than the first chord length. At least one of the second airfoils is circumferentially disposed between adjacent each pair (66) of the first airfoils. The leading edges (47) of the second airfoils are located downstream of the leading edges (53) of the first airfoils. The first and second airfoils have different first and second temperature capabilities respectively and the first temperature capability is greater than the second temperature capability. The first and second airfoils may be made from different alloys and/or the second airfoils may be constructed to use lower amounts of cooling airflow than the first airfoils. More than one of the second airfoils may be disposed between each pair (66) of the first airfoils.

    Row of long and short chord length turbine airfoils
    5.
    发明公开
    Row of long and short chord length turbine airfoils 审中-公开
    Turbinenschaufelreehe bestehend aus Schaufeln mit langer und kurzerSehnenlänge

    公开(公告)号：EP1424467A2

    公开(公告)日：2004-06-02

    申请号：EP03257438.6

    申请日：2003-11-26

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Turner, Mark Graham ,  Cedar, Richard David ,  Orkwis, Paul David

    IPC分类号： F01D5/14

    CPC分类号： F01D5/142 ,  F01D5/141 ,  F01D9/041 ,  F05D2240/12 ,  F05D2250/34 ,  F05D2250/70 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    摘要： A gas turbine engine turbine stage has an annular row of turbine airfoils including a first plurality (41) of first airfoils (44) having a first chord length (CL1) and a second plurality (43) of second airfoils (46) having a second chord length (CL2) shorter than the first chord length. At least one of the second airfoils is circumferentially disposed between adjacent each pair (66) of the first airfoils. The leading edges (47) of the second airfoils are located downstream of the leading edges (53) of the first airfoils. The first and second airfoils have different first and second temperature capabilities respectively and the first temperature capability is greater than the second temperature capability. The first and second airfoils may be made from different alloys and/or the second airfoils may be constructed to use lower amounts of cooling airflow than the first airfoils. More than one of the second airfoils may be disposed between each pair (66) of the first airfoils.

    摘要翻译： 燃气涡轮发动机涡轮级具有环形排的涡轮机翼型，其包括具有第一翼弦长度（CL1）和第二多个（43）第二翼型件（46）的第一多个（41）第一翼型件（44） 弦长（CL2）比第一弦长短。 第二翼型件中的至少一个沿周向设置在相邻的第一翼面对（66）之间。 第二翼型件的前缘（47）位于第一翼型件的前缘（53）的下游。 第一和第二翼型分别具有不同的第一和第二温度能力，并且第一温度能力大于第二温度能力。 第一和第二翼型件可以由不同的合金制成，和/或第二翼型件可被构造成使用比第一翼型件少的冷却气流。 第一翼型件中的多于一个可以设置在第一翼型件的每对（66）之间。