Patent ID: 9062565
Filing Date: 2015-06-23
Classification: F01D,F05D,Y02T

Abstract:
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.