公开(公告)号：US20130074505A1

公开(公告)日：2013-03-28

申请号：US13240286

申请日：2011-09-22

申请人： David Kaylor Toronto ,  Carolyn Ashley Antoniono ,  Andrew Grady Godfrey

发明人： David Kaylor Toronto ,  Carolyn Ashley Antoniono ,  Andrew Grady Godfrey

IPC分类号： F23R3/28

CPC分类号： F23R3/04 ,  F23R3/005 ,  F23R2900/03043

摘要： A system includes a gas turbine combustor. The gas turbine combustor includes a combustion liner disposed about a combustion region and a sleeve disposed about the combustion liner. The combustion liner and the sleeve define an airflow passage circumferentially about the liner. The gas turbine combustor also includes multiple axial injectors configured to direct an airflow into the airflow passage in an axial direction facilitating a momentum exchange between an injection flow and a crossflow from an upstream portion of the combustor. The multiple axial injectors are asymmetrically configured to provide an uniform injection of the airflow circumferentially about an axis of the gas turbine combustor.

摘要翻译： 一种系统包括燃气轮机燃烧器。 燃气轮机燃烧器包括围绕燃烧区域设置的燃烧衬套和围绕燃烧衬套设置的套筒。 燃烧衬套和套筒围绕衬套周向地限定气流通道。 燃气轮机燃烧器还包括多个轴向喷射器，其构造成沿着轴向引导气流进入气流通道，从而促进喷射流与来自燃烧器的上游部分的交叉流之间的动量交换。 多个轴向喷射器被非对称地配置成提供围绕燃气轮机燃烧器的轴线周向的气流的均匀喷射。