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    System and method for airfoil film cooling
    4.
    发明授权
    System and method for airfoil film cooling 失效
    翼型薄膜冷却系统及方法

    公开(公告)号：US06629817B2

    公开(公告)日：2003-10-07

    申请号：US09899305

    申请日：2001-07-05

    申请人： Monty Lee Shelton ,  Thomas Tracy Wallace ,  Robert Alan Frederick

    发明人： Monty Lee Shelton ,  Thomas Tracy Wallace ,  Robert Alan Frederick

    IPC分类号： F01D518

    CPC分类号： F01D5/186 ,  Y10T29/49339 ,  Y10T29/49341

    摘要： An airfoil for a gas turbine engine including an inflection that facilitates enhancing film cooling of the airfoil, without adversely affecting aerodynamic efficiency of airfoil is described. The airfoil includes a generally concave first sidewall and a generally convex second sidewall joined at a leading edge and at a trailing edge of the airfoil. A plurality of cooling openings extend between an internal cooling chamber and an external surface of the first sidewall. One cooling opening extends from the cooling chamber into the inflection at a relatively shallow injection angle with respect the airfoil external surface.

    摘要翻译： 描述了一种用于燃气涡轮发动机的翼型件，其包括有助于增强翼型件的薄膜冷却的拐点，而不会不利地影响翼型件的空气动力学效率。 翼型件包括大致凹入的第一侧壁和在翼型件的前缘和后缘处连接的大致凸形的第二侧壁。 多个冷却开口在内部冷却室和第一侧壁的外表面之间延伸。 一个冷却开口以相对于翼型件外表面的相对浅的注入角度从冷却室延伸到拐点。

    End rail cooling for combined high and low pressure turbine shroud
    5.
    发明授权
    End rail cooling for combined high and low pressure turbine shroud 有权
    用于组合的高低压涡轮机护罩的末端导轨冷却

    公开(公告)号：US06340285B1

    公开(公告)日：2002-01-22

    申请号：US09590590

    申请日：2000-06-08

    申请人： Craig Alan Gonyou ,  Roger Lee Doughty ,  Monty Lee Shelton

    发明人： Craig Alan Gonyou ,  Roger Lee Doughty ,  Monty Lee Shelton

    IPC分类号： F04D3100

    CPC分类号： F01D11/005 ,  F01D25/246 ,  F02C7/28 ,  F05D2240/11 ,  F05D2260/20 ,  F05D2260/202

    摘要： A segmented turbine cooling component, such as shroud segment for the high pressure and low pressure turbine sections of a gas turbine engine, useful in providing preferential cooling to the side rails or panels of the turbine component through the combination of cooling air fed into the intermediate pressure cavity between the discourager and primary seals and then through recesses in the bottom wall of the lower discourager seal slot that impinges air on the portion of the side panel below the discourager seal. The side panels of the turbine component have an upper primary seal slot and a lower discourager seal slot with a bottom wall having a plurality of alternating lands and recesses along the length thereof and a plurality of cooling air passages having outlets exiting into the lower slot above the lands. The subassembly can be formed from a plurality of such turbine components where the spacing of the lands and recesses of the lower discourager slots of the adjacent side panels are staggered such that the lands of the lower slot of one adjacent panel are opposite the recesses of the lower slot of the other adjacent side panel. This subassembly also has primary and discourager seals received by the respective upper and lower slots that are positioned in the gap between the adjacent panels which define the intermediate pressure cavity therebetween and trench below the discourager seal that is purged by spent cooling air from the recesses in the lower slot.

    摘要翻译： 分段涡轮机冷却部件，例如用于燃气涡轮发动机的高压和低压涡轮机部分的护罩段，其可用于通过组合供应到中间体中的冷却空气向涡轮机部件的侧轨或侧板提供优先冷却 沮丧者和初级密封件之间的压力空腔，然后通过下部砸痕器密封槽的底壁中的凹槽，其将空气撞击在挡板密封件下方的侧板部分。 涡轮机部件的侧板具有上主要密封槽和下部盘片密封槽，其底壁具有沿着其长度的多个交替的平台和凹部，以及多个冷却空气通道，其具有出口到上述下槽中 土地 子组件可以由多个这样的涡轮机部件形成，其中相邻侧板的下部罢工槽的平台和凹槽的间隔交错，使得一个相邻面板的下槽的平台与 另一个相邻侧面板的下槽。 该子组件还具有由相应的上部和下部狭槽接收的主要和沮丧的密封件，该密封件定位在相邻面板之间的间隙中，在相邻面板之间的间隙中限定了中间压力空腔，并且在捣实器密封件下方的沟槽被消耗的冷却空气从凹部 下槽。