US 12,187,420 B2
Optimised nozzle geometry
Martin Leslie, Fintona (GB); Patrick Mallon, Fintona (GB); and Michael Rice, Fintona (GB)
Assigned to Genesis Aerotech Limited, County Tyrone (GB)
Appl. No. 17/635,122
Filed by Genesis Aerotech Limited, Fintona (GB)
PCT Filed Aug. 12, 2020, PCT No. PCT/EP2020/072680
§ 371(c)(1), (2) Date Feb. 14, 2022,
PCT Pub. No. WO2021/028508, PCT Pub. Date Feb. 18, 2021.
Claims priority of application No. 1911520 (GB), filed on Aug. 12, 2019.
Prior Publication US 2022/0306309 A1, Sep. 29, 2022
Int. Cl. B64C 27/18 (2006.01); B05B 1/00 (2006.01); B64C 9/16 (2006.01); B64D 27/00 (2006.01); F15D 1/04 (2006.01); F15D 1/08 (2006.01)
CPC B64C 27/18 (2013.01) [B05B 1/005 (2013.01); B64C 9/16 (2013.01); B64D 27/00 (2013.01); F15D 1/04 (2013.01); F15D 1/08 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A compressed gas ejection means non-movably located on a trailing edge of a rotating wing aircraft blade, the compressed gas ejection means comprising a compressed gas passage means, the compressed gas passage means being adapted to allow a substantially constant velocity of compressed air flowing through the compressed gas ejection means across substantially the entire width of the compressed gas passage means, wherein the rotating wing aircraft comprises a compressor for producing compressed air for the compressed gas ejection means, wherein the compressed gas ejection means comprises a guide means for guiding compressed air from the compressor through a turn to the compressed gas passage means, wherein the guide means comprises a plurality of guide channels and wherein the cross-sectional areas of the plurality of guide channels are adapted to allow a substantially constant velocity of compressed air flowing through the compressed gas ejection means across substantially the entire width of the compressed gas passage means.