Integrated aero-engine flowpath structure

An integrated aero-engine flowpath structure, comprising:na composite outer flowpath wall;a composite inner flowpath wall; anda composite linking structure extending between said composite outer flowpath wall and said composite inner flowpath wall, wherein said composite linking structure is structured to separate said composite outer flowpath wall from said composite inner flowpath wall,wherein said composite outer flowpath wall and said composite inner flowpath wall define therebetween a primary flowpath for a working fluid of an aero-engine; andwherein said composite outer flowpath wall, said composite inner flowpath wall and said composite linking structure are co-bonded to form a unitary structure operable to withstand thermal and mechanical loading during the operation of said aero-engine without additional structural backing, wherein an integral carbon-carbon plug nozzle forms a portion of said composite inner flowpath wall and wherein said composite inner flowpath wall is annular.

An integrated aero-engine flowpath structure, comprising:nat least one of a carbon-carbon outer flowpath wall and a carbon-carbon inner flowpath wall;a carbon-carbon linking structure extending from said at least one of said carbon-carbon outer flowpath wall and said carbon-carbon inner flowpath wall;wherein said outer flowpath wall, said inner flowpath wall and said linking structure are co-bonded to form a unitary structure; anda bond joint between said carbon-carbon linking structure and at least one of said carbon-carbon outer flowpath wall and said carbon-carbon inner flowpath wall,wherein, at said bond joint, plies in said carbon-carbon linking structure are aligned with plies in said at least one of said carbon-carbon outer flowpath wall and said carbon-carbon inner flowpath wall, wherein an integral carbon-carbon plug nozzle forms a portion of said inner flowpath wall and wherein said inner flowpath wall is annular.