|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/53B ; 137/151|
|우선권정보||UK-0026136 (1973-05-31); UK-0053123 (1973-11-15)|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 26 인용 특허 : 0|
A supersonic two-dimensional intake arrangement for two or more jet propulsion engines has a duct for each engine, a mouth region for each duct, said mouth regions being positioned in adjacent rearewardly staggered rearwardly such that at least one shock wave is common to all mouth regions. Preferably one duct wall is common to adjacent intake mouths.
An air intake arrangement for at least two jet propulsion engines for a supersonic aircraft the air intake arrangement comprising: means defining a first intake duct, including four bounding sidewall means in two pairs of opposing sidewall means defining a first forward facing intake duct mouth region of generally rectangular shape; means defining a second intake duct, including four bounding sidewall means in two pairs of opposing sidewall means defining a second forward facing intake duct mouth region of generally rectangular shape; the intake ducts be...