US 12,252,250 B2
Aviation turbofan engine and fan duct nozzle
Zheng Cui, Beijing (CN)
Assigned to BEIJING AERONAUTICAL SCIENCE & TECHNOLOGY RESEARCH INSTITUTE, COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Beijing (CN); and COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD., Shanghai (CN)
Filed by Beijing Aeronautical Science & Technology Research Inst., Commercial Aircraft Corporation of China, Beijing (CN); and COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD., Shanghai (CN)
Filed on Dec. 26, 2023, as Appl. No. 18/396,195.
Application 18/396,195 is a continuation of application No. PCT/CN2022/129923, filed on Nov. 4, 2022.
Claims priority of application No. 202210283285.9 (CN), filed on Mar. 22, 2022.
Prior Publication US 2024/0124121 A1, Apr. 18, 2024
Int. Cl. F02K 1/52 (2006.01); B64C 7/02 (2006.01); F02K 1/40 (2006.01); B64C 7/00 (2006.01)
CPC B64C 7/02 (2013.01) [F02K 1/40 (2013.01); F02K 1/52 (2013.01); B64C 7/00 (2013.01); F05D 2220/36 (2013.01)] 5 Claims
OG exemplary drawing
 
1. A fan duct nozzle of an aviation turbofan engine, comprising a notch formed in a rear edge of an engine nacelle on an outer side of an engine pylon, and a flow guide curved surface matching the notch in shape is arranged on a profile of the fan duct nozzle,
wherein a depth of the notch is not larger than 20% of a mean aerodynamic chord of the engine nacelle and not smaller than 5% of the mean aerodynamic chord of the engine nacelle, and a width of the notch is not larger than ¼ of a perimeter of the rear edge of the engine nacelle and not smaller than 1/20 of the perimeter of the rear edge of the engine nacelle.