Patent ID: 8850823

Claim:
An integrated aero-engine flowpath structure, comprising: a composite outer flowpath wall; a composite inner flowpath wall; and a 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; and wherein 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.