|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||181/213 ; 181/264 ; 181/269 ; 181/273|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 37 인용 특허 : 10|
A compressor bleed air passageway includes a duct having an upstream section (48) which terminates in a baffle (44) and a downstream duct section (54) having a forward portion (56) which surrounds the baffle (44). Bleed air flow through openings (58) in the baffle wall (52). This reduces velocity of the bleed air stream at the duct discharge port to a value equal to or less than Mach 1.0. The baffle (44) has virtually no effect on a low-velocity, low-pressure air stream. The downstream duct section (54) may be perforated and surrounded by outer wall (64)...
In a system for bleeding air from a compressor of an aircraft engine to maintain compressor stability, said system including a flow passageway having an inlet end portion communicating with the engine and a discharge port communicating to atmosphere, an improvement for suppressing noise generated by supersonic exhause air from said discharge port, said improvement comprising: a baffle positioned in the passageway and having openings through which exhaust gas passes when moving through the passageway from said inlet end portion to the discharge port; said...