发明名称 |
AERODYNAMIC SEAL FOR REDUCTION OF NOISE GENERATED ON AIRCRAFT CONTROL SURFACES |
摘要 |
Flap side edge noise mechanisms have been addressed in a large number of studies during the last decades. A specific vortex system emanates from the flap side edge due to the static pressure difference between the upper and lower flap surfaces. Such pressure difference leads to a merging between the two vortex systems that are generated on the upper and lower edges of the flap side contour. The present invention intends to show the application of a perforated blade seal (21) at the lower (11) and/or upper (8) side edges of the control surface contour, such as a flap (3), with the purpose of acting as a vortex generator, making difficult for the lower vortex system to move upwards and merge with the upper vortex system. The perforated blade seals (21) are preferably arranged on the inboard and outboard edges of high lift flaps (3).
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申请公布号 |
US2010294883(A1) |
申请公布日期 |
2010.11.25 |
申请号 |
US20080595679 |
申请日期 |
2008.03.27 |
申请人 |
TRICHES JR MARIO;VALLE DO CARMO MICAEL GIANINI;CALDEIRA DA SILVA BRUNO ARANTES;FRANCA BARBOZA MARKOS VINICIUS;LOSADA GOUVEIA VINICIUS |
发明人 |
TRICHES, JR. MARIO;VALLE DO CARMO MICAEL GIANINI;CALDEIRA DA SILVA BRUNO ARANTES;FRANCA BARBOZA MARKOS VINICIUS;LOSADA GOUVEIA VINICIUS |
分类号 |
B64C3/50 |
主分类号 |
B64C3/50 |
代理机构 |
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代理人 |
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地址 |
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