Combustor anti-surge retention system
AssigneeUnited Technologies Corporation
InventorsThomas E. Clark, Harvey C. Lee, Brian C. McLaughlin, Jonathan Lemoine
Life of this patent
Estimating the term…
Abstract
A combustor assembly for a gas turbine engine comprises a vane support ring; an annular combustor extending around a central axis and being located radially inwards of the vane support ring, the annular combustor including an aft end, a forward end with at least one opening through which at least one fuel nozzle is received, and an annular outer shell and an annular inner shell that define an annular combustion chamber there between, the annular outer shell including a radially-outwardly extending flange including at least one scallop cut; and a stop member integrally formed with the vane support ring.
Claims15
A combustor assembly for a gas turbine engine, comprising:
- a vane support ring;
- an annular combustor extending around a central axis and being located radially inwards of the vane support ring, the annular combustor including an aft end, a forward end with at least one opening through which at least one fuel nozzle is received, and an annular outer shell and an annular inner shell that define an annular combustion chamber there between, the annular outer shell including a radially-outwardly extending flange including at least one scallop cut;
- and
- a stop member integrally formed with the vane support ring.
A gas turbine engine comprising:
- a static structure;
- a compressor section;
- an annular combustor in fluid communication with the compressor section, the 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 through which at least one fuel nozzle is received, 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 having at least one scallop cut;
- a turbine section in fluid communication with the annular combustor;
- and at least one stop member integral with a vane support ring on the static structure and adjacent the radially-outwardly extending flange such that axial-forward movement of the annular combustor is limited, with respect to directionality defined by the forward end and the aft end.
Dependencies are inferred from the claim text.