Gas turbine engine combustor surge retention

摘要

A combustor assembly for a gas turbine engine includes a static structure and an annular combustor extending around a central axis and located radially inwards of the static structure. The annular combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber there between. The annular combustor is free of any rigid attachments directly between the static structure and the annular outer shell. The annular outer shell includes a radially-outwardly extending flange. A stop member is rigidly connected with the static structure and is located adjacent the radially-outwardly extending flange such that axial-forward movement of the annular combustor is limited.

主权项

1. A combustor assembly for a gas turbine engine, comprising:
a static structure; an annular combustor extending around a central axis and being located radially inwards of the static structure, the annular combustor including an aft end, a forward end with at least one opening through which at least one fuel nozzle is received with a clearance gap distance G between the fuel nozzle and the opening, and an annular outer shell and an annular inner shell that define an annular combustion chamber there between, the annular combustor being free of any rigid attachments directly between the static structure and the annular outer shell, the annular outer shell including a radially-outwardly extending flange; and a stop member rigidly connected with the static structure and axially-forwardly spaced apart by a distance D from the radially-outwardly extending flange such that axial-forward movement of the annular combustor, with respect to directionality defined by the forward end and the aft end, is limited to an amount equal to the distance D, and the distance D is less than the clearance gap distance G.