Patent ID: 10012108

Abstract:
The invention concerns a gas turbine engine component (37) comprising an outer ring structure (10), an inner ring structure (20) and a plurality of circumferentially spaced radial elements (15) for transferring loads between the inner ring structure (20) and the outer ring structure (10), wherein the outer ring structure (10) comprises a circular ring member (11) for withstanding an internal pressure during operation of the gas turbine engine. The invention is characterized in that the outer ring structure (10) comprises a first set of circumferentially distributed and substantially straight reinforcement ribs (16) for achieving radial stiffness, wherein the reinforcement ribs (16) form sides in a polygonal shape and wherein each of said reinforcement ribs (16) extends between two adjacent radial elements (15). The invention also concerns a gas turbine engine (1) comprising a component (37) of the above type.