| 发明名称 | Integrated aero-engine flowpath structure | ||
| 摘要 | 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. | ||
| 申请公布号 | US8850823(B2) | 申请公布日期 | 2014.10.07 |
| 申请号 | US201012978954 | 申请日期 | 2010.12.27 |
| 申请人 | Rolls-Royce North American Technologies, Inc. | 发明人 | Ress, Jr. Robert A.;Yount Randall E.;Destefano Thomas D.;Patel Jitendra R. |
| 分类号 | F02K1/04;F02K1/82;F02K1/78;F02K1/80 | 主分类号 | F02K1/04 |
| 代理机构 | Krieg DeVault LLP | 代理人 | Krieg DeVault LLP |
| 主权项 | 1. 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. | ||
| 地址 | Indianapolis IN US | ||