公开(公告)号：US20100236248A1

公开(公告)日：2010-09-23

申请号：US12406657

申请日：2009-03-18

Applicant: Karthick Kaleeswaran ,  Ganesh Pejawar Rao ,  Pankaj Kumar Jha

Inventor： Karthick Kaleeswaran ,  Ganesh Pejawar Rao ,  Pankaj Kumar Jha

IPC: F02C1/00

CPC classification number: F23R3/06 ,  F23R2900/00005

Abstract: A combustor liner for a gas turbine combustor includes a cooling hole formed in the liner that delivers cooling air into a combustion zone of the combustor. A stub is secured in the cooling hole and is structured to provide added stiffness to an inside edge of the cooling hole. The added stiffness reduces cracking caused by thermal fatigue and provides resistance against high cycle fatigue failures at high frequencies.

Abstract translation: 用于燃气轮机燃烧器的燃烧器衬套包括形成在衬套中的冷却孔，其将冷却空气输送到燃烧器的燃烧区。 短管被固定在冷却孔中并被构造成为冷却孔的内边缘提供附加的刚性。 增加的刚度可减少由热疲劳引起的裂纹，并提供高频时高循环疲劳失效的阻力。