Gas turbine engine combustor and method of forming same
Abstract:
A gas turbine engine combustor is described which includes outer and inner annular combustor liners formed of sheet metal. The exit duct circumscribes an annular combustor exit and defines a combustion gas path. The exit duct includes a large exit duct having an annular forged metal section which is butt welded at an upstream end to the outer combustor liner to form a first annular joint. The annular forged metal section is fixed at a downstream end to an annular sheet metal wall to form a second annular joint. Methods of forming and of repairing a gas turbine engine combustor are also disclosed.
Public/Granted literature
Information query
Patent Agency Ranking
0/0