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A method of fabricating an annular liner for a combustion chamber of a gas turbine engine. The combustion chamber has a dome including a fuel nozzle for delivering fuel to the combustion chamber. A metal piece is formed into an annular section constituting at least a portion of the liner and having

A method of fabricating an annular liner for a combustion chamber of a gas turbine engine. The combustion chamber has a dome including a fuel nozzle for delivering fuel to the combustion chamber. A metal piece is formed into an annular section constituting at least a portion of the liner and having at least one seam extending generally axially with respect to an axial centerline of the liner. An upstream end of the liner is machined to have a registration feature for connecting the liner to the combustion chamber dome in at least one predetermined orientation with respect to the dome. Further, the method includes ensuring the registration feature and the seam are located relative to each other on the liner so the seam is at a preselected position with respect to the combustion chamber dome when the liner is connected to the combustion chamber dome in the predetermined orientation.

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1. A method of fabricating an annular liner for a combustion chamber of a gas turbine engine in which fuel and flowpath gases are mixed and burned to heat the flowpath gases, the combustion chamber having a dome defining an upstream boundary of the combustion chamber and including at least two fuel

1. A method of fabricating an annular liner for a combustion chamber of a gas turbine engine in which fuel and flowpath gases are mixed and burned to heat the flowpath gases, the combustion chamber having a dome defining an upstream boundary of the combustion chamber and including at least two fuel nozzles for delivering fuel to the combustion chamber, the method comprising the steps of:forming a metal piece into an annular section constituting at least a portion of said liner and having at least one seam extending generally axially with respect to an axial centerline of the liner; machining an upstream end of the liner to have a registration feature for connecting the liner to the combustion chamber dome in at least one predetermined orientation with respect to the dome; and ensuring the registration feature and the seam are located relative to each other on the liner so that the seam is at a preselected position with respect to the combustion chamber dome when the liner is connected to the combustion chamber dome in said predetermined orientation; wherein the fuel nozzles are spaced around the centerline of the liner when the liner is connected to the combustion chamber dome in said predetermined orientation, and the preselected position of the seam is at an angular position around the liner centerline between two of said fuel nozzles.