Patent ID: 8596972

Claim:
A duct for a gas turbine engine comprising: a first composite duct section defined along a longitudinal axis; and a first metallic support ring section mountable to said first composite duct section at least partially about said longitudinal axis, said first metallic support ring section includes a first reinforcement ring section which extends from said first support ring section toward said longitudinal axis, wherein said first metallic support ring section includes a multiple of apertures to receive fasteners which interface with said first composite duct section, said first reinforcement ring transitions into a multiple of reinforcement plates, each of said multiple of reinforcement plates includes an aperture to receive a fastener to mount an engine system component; a second composite duct section defined along said longitudinal axis, said second composite duct section mateable with said first composite duct section; and a second metallic support ring section mountable to said second composite duct section at least partially about said longitudinal axis, said second metallic support ring section includes a second reinforcement ring section which extends from said second support ring section toward said longitudinal axis, said second metallic support ring section adjacent to said first metallic support ring section.