초록 ▼

One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath st

One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath structures. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

대표청구항 ▼

1. An integrated aero-engine flowpath structure, comprising: a 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 stru

1. An integrated aero-engine flowpath structure, comprising: a 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. 2. The integrated aero-engine flowpath structure of claim 1, wherein said composite outer flowpath wall, said composite inner flowpath wall and said composite linking structure are formed of a carbon-carbon material. 3. The integrated aero-engine flowpath structure of claim 2, wherein plies of said carbon-carbon material in said composite linking structure are aligned with plies in at least one of said composite outer flowpath wall and said composite inner flowpath wall. 4. The integrated aero-engine flowpath structure of claim 2, wherein said composite linking structure includes a segment extending parallel to at least one of said composite outer flowpath wall and said composite inner flowpath wall. 5. The integrated aero-engine flowpath structure of claim 2, wherein said composite linking structure is a vane. 6. The integrated aero-engine flowpath structure of claim 2, wherein said composite linking structure is a strut. 7. The integrated aero-engine flowpath structure of claim 2, further comprising a carbon-carbon transition structure bonded to said composite linking structure and to at least one of said composite outer flowpath wall and said composite inner flowpath wall, wherein plies of said carbon-carbon transition structure are aligned with plies in said composite linking structure and aligned with plies in at least one of said composite outer flowpath wall and said composite inner flowpath wall. 8. The integrated aero-engine flowpath structure of claim 1, further comprising a carbon-carbon tail cone bonded to said integral carbon-carbon plug nozzle. 9. The integrated aero-engine flowpath structure of claim 8, further comprising a threaded bond joint between said carbon-carbon tail cone and said integral carbon-carbon plug nozzle. 10. The integrated aero-engine flowpath structure of claim 2, further comprising a carbon-carbon forward structure bonded to said composite inner flowpath wall. 11. The integrated aero-engine flowpath structure of claim 10, further comprising a threaded bond joint between said carbon-carbon forward structure and said composite inner flowpath wall. 12. An integrated aero-engine flowpath structure, comprising: at 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. 13. The integrated aero-engine flowpath structure of claim 12, wherein said carbon-carbon linking structure includes a segment extending parallel to said at least one of said carbon-carbon outer flowpath wall and said carbon-carbon inner flowpath wall. 14. The integrated aero-engine flowpath structure of claim 13, further comprising a carbon-carbon transition structure bonded to said carbon-carbon linking structure and to said at least one of said carbon-carbon outer flowpath wall and said carbon-carbon inner flowpath wall, wherein plies of said carbon-carbon transition structure are aligned with plies in said carbon-carbon linking structure and aligned with plies said in at least one of said carbon-carbon outer flowpath wall and said carbon-carbon inner flowpath wall.