首页>
外国专利>
Hybrid through holes and angled holes for combustor grommet cooling
Hybrid through holes and angled holes for combustor grommet cooling
展开▼
机译:混合通孔和倾斜孔,用于燃烧室索环冷却
展开▼
页面导航
摘要
著录项
相似文献
摘要
Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.
展开▼