Patent ID: 6250062
Filing Date: 2001-06-26
Classification: F23R,Y10T

Abstract:
A gas turbine combustor, comprising:a main combustor chamber having a liner and an annular collar mounted to said liner so as to define an opening therethrough;at least one burner attached to said main combustor chamber and having a fuel nozzle mounted adjacent to said liner and a tip of said fuel nozzle disposed through said opening of said annular collar of said main combustor chamber with an outer periphery of said tip disposed within and adjacent to said annular collar; anda fuel nozzle centering device mounted to said outer periphery of said tip of said fuel nozzle and disposed between said outer periphery of said fuel nozzle tip and said annular collar of said liner, said device including a sacrificial body of material contacting said liner collar and spacing said fuel nozzle tip radially inwardly from said liner collar such that said fuel nozzle tip is prevented from contacting said liner collar during assembling of said fuel nozzle of said burner to said liner of said main combustion chamber, said sacrificial body of material being at least partially wearable away upon initial operation of said gas turbine combustor such that said sacrificial body of material will diminish in quantity and thereby reduce contact with said liner collar during further operation of said gas turbine combustor so that said fuel nozzle tip will remain spaced from and substantially out of contact with said liner collar of said main combustion chamber during continued operation of said gas turbine combustor.