|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/226.1; 060/208.3; 060/209.4|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 11 인용 특허 : 53|
A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.
We claim: 1. An aircraft bypass turbofan engine comprising an engine core and a casing surrounding at least a portion of the engine core, the casing including a plurality of thin walled hollow struts and a plurality of thin walled adjoining members having a V-shaped cross-section for providing a splitter between airflows paths through the engine core and bypass, the struts arranged in a circumferential array between an inner hub and the casing, the struts extending continuously from the inner hub to the casing to thereby mount the inner hub directly to ...