Gas turbine engine containment device

摘要

A fan containment system for a gas turbine engine, and a method of making the same, is disclosed that in one embodiment includes casing that surrounds at least a portion of a plurality of fan blades. In one form, a pair of standoff rings is formed in an outer surface of the casing that are spaced apart from one another a predetermined distance running circumferentially about the inner nacelle ring. A containment ring is positioned around a radially outer surface of the standoff rings to form an interference fit between the two.

主权项

1. A containment system for rotating turbomachinery, comprising:
a gas turbine engine flow path structure having an annular shape; an outer ring located radially outward of the gas turbine engine flow path structure, the outer ring operable to be at least partially radially in-line with a rotating blade of a gas turbine engine, wherein the outer ring includes first and second protrusions extending radially inward from a surface to form an inner space of the outer ring; and an abutment structure coupling the outer ring to the gas turbine engine flow path structure in an interference fit; wherein the gas turbine engine flow path structure includes first and second standoffs extending from the same base, wherein the standoffs and base form a monolithic structure, the first and second standoffs forming a portion of the abutment structure coupling the outer ring to the gas turbine engine flow path structure; wherein the first and second standoffs are located between the first and second protrusions.