|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/2261 ; 244/53B|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 25 인용 특허 : 0|
A propfan turbine engine for an aircraft has a shroud and on the leading edge of the shroud, has one or several, preferably two, separate sector-like annular profile parts which via actuating devices can be moved from the shroud such that slots can be formed between the profile parts and the shroud. This arrangement prevents dangerous air-flow separations on the outside of the upper shroud region and on the inside of the lower shroud region at large angles of attack of the aircraft engine for both high and low power operation.
A propfan turbine engine for aircraft having a shroud surrounding propfan blades, comprising: an annular leading edge of said shroud including a separate profile part forming an upper continuous annular section having an arc greater than 30°as a part of said leading edge; means for actuating coupled to said separate profile part to vary the position of said separate profile part with respect to said shroud; a single continuous annular slot-like duct formed between said profile part and said shroud when said separate profile part is in an extended positio...