发明名称 Combustion liner with bias effusion cooling
摘要 A system and method for improving the cooling to a portion of a combustion liner of a gas turbine combustor is disclosed. The combustion liner is cooled by supplying air through a plurality of cooling holes arranged in axially spaced rows in an upper and lower portion of the liner. The cooling holes are spaced accordingly so as to direct additional cooling flow to an area of the combustion liner not receiving sufficient flow due to maldistributions of air from the compressor discharge.
申请公布号 US9429323(B2) 申请公布日期 2016.08.30
申请号 US201414278770 申请日期 2014.05.15
申请人 General Electric Technology GMBH 发明人 Richardson Brian;Oumejjoud Khalid;Cutright John;McMullen Nikki;Stuttaford Peter John;Parker Richard;Soni Sumit
分类号 F23R3/04;F23R3/00;F23R3/06 主分类号 F23R3/04
代理机构 Shook, Hardy & Bacon, L.L.P. 代理人 Shook, Hardy & Bacon, L.L.P.
主权项 1. A combustion liner for a gas turbine combustor comprising: a generally annular body having an inner wall, an outer wall spaced a distance from the inner wall, an inlet end, and an opposing outlet end, the generally annular body also having a plane extending through a centerline to bisect the generally annular body and define an upper portion and a lower portion of the generally annular body; a seal positioned along the outer wall proximate the outlet end; the upper portion having a plurality of cooling holes, the upper portion having a lower boundary defined by the plane extending through the centerline, a left boundary defined by a column of one or more cooling holes most near to the inlet end, and a right boundary defined by a column of one or more cooling holes most near to the outlet end; the lower portion having a plurality of cooling holes, the lower portion having an upper boundary defined by the plane extending through the centerline, a left boundary defined by a column of one or more cooling holes most near to the inlet end, and a right boundary defined by a column of one or more cooling holes most near to the outlet end, wherein the lower portion comprises a section of the generally annular body that is positioned closer to an engine axis upon installation of the combustion liner in the gas turbine engine; and wherein the entire lower portion of the generally annular body has a higher concentration of cooling holes than the entire upper portion of the generally annular body.
地址 Baden CH