Gas turbine combustion chamber wall structure for minimizing cooling
film disturbances
    1.
    发明授权
    Gas turbine combustion chamber wall structure for minimizing cooling film disturbances 失效
    用于最小化冷却膜的气体涡轮机燃烧室壁结构

    公开(公告)号:US5209067A

    公开(公告)日:1993-05-11

    申请号:US778283

    申请日:1991-10-17

    IPC分类号: F23R3/06 F23R3/08

    CPC分类号: F23R3/06 F23R3/08 Y02T50/675

    摘要: A combustion chamber wall structure is formed of a plurality of segments, each segment having an upstream portion and a downstream portion. The upstream portion is attached to an outer surface of an adjacent wall segment at its downstream portion in an overlapping fashion such that the overlapping portions form a cooling air chamber. The main cooling air holes are defined by the upstream portion so as to communicate with the cooling chamber, which has an exit to direct the cooling air along an inner surface of the downstream portion of the wall segment. A primary air hole is defined by the downstream portion of the segment and is located adjacent to the main cooling air holes. This location maximizes the distance between the primary air hole and an upstream portion of the same segment, which, in turn, maximizes the distance along the inner surface of the segment on which the cooling air may flow without being disrupted by air passing through the primary air hole. The guidance of the primary/dilution air streams can also be carried out by a portion of the downstream air cooling film.

    摘要翻译: 燃烧室壁结构由多个段形成,每个段具有上游部分和下游部分。 上游部分以其重叠的方式在其下游部分处附接到相邻壁段的外表面,使得重叠部分形成冷却空气室。 主冷却空气孔由上游部分限定,以便与具有出口的冷却室连通,以沿着壁段的下游部分的内表面引导冷却空气。 一个主要空气孔由该段的下游部分限定,并且位于主冷却空气孔附近。 该位置使得主空气孔和同一段的上游部分之间的距离最大化,这又使得沿着冷却空气可流动的段的内表面的距离最大化,而不会被穿过主要空气的空气中断 气孔。 初级/稀释气流的引导也可以由下游空气冷却膜的一部分进行。