Patent ID: 6282886
Filing Date: 2001-09-04
Classification: F23C,F23D,F23L,F23R

Abstract:
A gas turbine combustor constructed within a turbine casing wall, comprising:an inner tube having a fuel inlet side, a central portion and an inner circumferential surface;a connecting tube and a tail tube sequentially connected to said inner tube such that said inner tube, said connecting tube and said tail tube are sequentially arranged from said fuel inlet side of said inner tube, wherein said tail tube has an outlet portion connected to a gas turbine inlet portion; anda cooling means for attaining uniform cooling in said outlet portion of said tail tube;wherein said inner tube comprisesa pilot swirler arranged in said central portion of said inner tube,a plurality of main swirlers arranged around said pilot swirler,a circular base plate fixed to said inner circumferential surface of said inner tube, wherein said pilot swirler and each of said main swirlers have respective end portions passing through said circular base plate so as to be supported thereby,a plurality of spaced supports supporting said inner tube on said turbine casing wall and forming an air intake,a rectifier tube for making air taken in to said inner tube through said air intake uniform, said rectifier tube comprising a sloping end fixed to said turbine casing wall, said sloping end comprising a sloping portion having a contracting diameter, and said sloping portion extending around said supports, and said rectifier tube further comprising an other end forming an opening such that the other end maintains a predetermined spacing from said inner tube, anda holding means for holding at least one of said pilot swirler and said main swirlers so as to mitigate thermal stress.