US 12,448,900 B2
Local stiffening for gas turbine engine casing
Morgan Demenois, Montreal (CA); Negin Abaeian, Westmount (CA); Tomasz Olech, Rzeszow (PL); Raghavendra Pendyala, Montreal (CA); and Domenico Di Florio, Saint Lazare (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Aug. 9, 2024, as Appl. No. 18/799,108.
Application 18/799,108 is a division of application No. 18/348,915, filed on Jul. 7, 2023, granted, now 12,158,076.
Prior Publication US 2025/0012204 A1, Jan. 9, 2025
Int. Cl. F01D 25/04 (2006.01); F01D 25/24 (2006.01); F02C 3/04 (2006.01)
CPC F01D 25/04 (2013.01) [F01D 25/24 (2013.01); F02C 3/04 (2013.01); F05D 2260/81 (2013.01); F05D 2260/96 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A method of providing a casing for a gas turbine engine comprising the steps of:
1) modeling a casing design for a casing to be formed of sheet metal;
2) determining at least one peak displacement point based upon the modeling of step 1); and
3) providing a stiffening element at the at least one peak displacement point, the stiffening element fixed to a wall of the casing; wherein there is a cutout through the wall of the casing and the at least one peak displacement point is adjacent one wall of the cutout, and the at least one stiffening element is dimple formed in the wall.