|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B63H-011/00 F02C-003/073 F02C-003/107 F02C-003/08 F02K-003/068 F02C-007/36 F04D-025/04 F16H-048/10|
|미국특허분류(USC)||060/204; 060/039.162; 060/268|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 72|
A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of...
1. A method of operating a turbine engine including the steps of: rotatably driving a fan having a plurality of hollow fan blades with a turbine mounted to an outer periphery of the fan, wherein the turbine includes turbine blades disposed radially outward of the plurality of hollow fan blades; andcounter-rotatably driving an axial compressor rotor via rotation of the fan, wherein the axial compressor rotor is counter-rotatably driven by a planetary gearset that couples the fan to the axial compressor rotor. 2. The method of claim 1 further including the...