Gas turbine combustion chamber - has fuel lines to burner nozzles extending through secondary air duct and contained in tubes connected to atmosphere

摘要

The combustion chamber assembly (4) for a gas turbine or a pressure-fired steam boiler comprises burner nozzles (8) in the combustion chamber (7) which are connected to fuel injection lines (6,14) extending from outside the outer wall (19) of the assembly through a secondary air supply (11) duct (16). These lines are contained in outer tubes (12,15) which extend from outside the wall (19) to inside the chamber (7) where their ends are sealingly connected with the nozzle perimeters. The annular spaces between the lines and the tubes are connected (13) to atmosphere at positions outside the wall (19). ADVANTAGE - The arrangement positively prevents any leakage of fuel into the compressor air flow and condensation from the compressed air through cooling by the cold fuel which could lead to excessive thermal stress in the fuel lines.