US 12,215,654 B2
Cascade element for a thrust reverser system of an engine
Ludwig Loretz, Stockerau (AT); Andreas Hoellrigl, Vienna (AT); and Guenter Nelboeck, Seewalchen (AT)
Assigned to FACC AG, Ried im Innkreis (AT)
Appl. No. 18/005,344
Filed by FACC AG, Ried im Innkreis (AT)
PCT Filed Jul. 13, 2021, PCT No. PCT/AT2021/060248
§ 371(c)(1), (2) Date Jan. 12, 2023,
PCT Pub. No. WO2022/011407, PCT Pub. Date Jan. 20, 2022.
Claims priority of application No. A 50605/2020 (AT), filed on Jul. 13, 2020.
Prior Publication US 2023/0265811 A1, Aug. 24, 2023
Int. Cl. F02K 1/72 (2006.01); F02K 1/76 (2006.01); B33Y 10/00 (2015.01); B33Y 80/00 (2015.01)
CPC F02K 1/72 (2013.01) [F02K 1/766 (2013.01); B33Y 10/00 (2014.12); B33Y 80/00 (2014.12); F05D 2220/323 (2013.01); F05D 2230/30 (2013.01)] 17 Claims
OG exemplary drawing
 
13. A method for producing a cascade element for a thrust reverser system of an engine, comprising:
additive production of a number of adjacently arranged deflecting blades for deflecting an airflow, wherein at least one of the deflecting blades is constructed with a twist with respect to its longitudinal axis along a twisting longitudinal section, and wherein at least one deflecting blade is constructed with a bulge on an edge delimiting the deflecting blade in a direction of downward extent, so that a shape of the edge deviates from a straight line or, in the twisting longitudinal section, from a helix.