公开(公告)号：US20140150452A1

公开(公告)日：2014-06-05

申请号：US13991419

申请日：2012-11-30

Applicant: General Electric Company

Inventor： John Frederick Pohlman ,  Daniel Doyle Vandale ,  Sergey Victorovich Koshevets ,  Mehmet Tartan ,  Carey Edward Romoser

IPC: F02C7/20

CPC classification number: F02C7/20 ,  F01D9/023 ,  F05D2250/74 ,  F23R3/04 ,  Y02T50/673 ,  Y02T50/675

Abstract: A system includes a gas turbine transition piece. The gas turbine transition piece includes a duct body having a forward end portion and an aft end portion. The duct body defines an enclosure for routing a flow of combustion products from a combustor to a turbine first stage nozzle, and the forward end portion includes a straight portion extending in a downstream direction of the flow. The gas turbine transition piece also includes a first set of dilution holes formed in the forward end portion and arranged in a first pattern configured to reduce emissions. In certain embodiments, the gas turbine transition piece includes a second set of dilution holes formed in the aft end portion and arranged in a second pattern configured to alter the thermal gradient of the combustion gases.

Abstract translation: 一种系统包括燃气轮机过渡件。 燃气轮机过渡件包括具有前端部分和后端部分的管道主体。 导管主体限定用于将燃烧产物流从燃烧器引导到涡轮机第一级喷嘴的外壳，并且前端部分包括在流动的下游方向上延伸的直线部分。 燃气轮机过渡件还包括形成在前端部分中的第一组稀释孔，并以配置成减少排放物的第一模式布置。 在某些实施例中，燃气涡轮机过渡件包括形成在后端部分中的第二组稀释孔，并且布置成构造成改变燃烧气体的热梯度的第二图案。