|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||181/214; 181/213; 181/210; 244/053.B|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 19 인용 특허 : 13|
An aircraft engine assembly is provided that is adapted to reduce noise produced by an engine included in the engine assembly. The engine assembly includes a nacelle having an inlet section and a main section that is houses the engine and fan assembly associated with the engine. The inlet section is coupled to the main section at a main bulkhead junction between the inlet section and the main section. A one piece annular acoustic panel is located within a recess in an internal wall of the nacelle. The annular acoustic panel extends from a forward portion...
1. An aircraft engine assembly adapted to attenuate noise, said engine assembly comprising:a nacelle including an inlet section coupled to a main section adapted to support an engine and fan assembly therewithin; and a one piece annular acoustic panel that forms a segment of an internal wall of the nacelle, wherein the annular acoustic panel forms at least a portion of the inlet section and a forward portion of the main section. 2. The engine assembly of claim 1, wherein the annular acoustic panel extends from a forward portion of the inlet section to a ...