US 12,326,112 B2
Gas turbine engine bypass louver and baffle rib design
Marco P. Convertini, Vaughan (CA); Shervin Aslani Amoli, Toronto (CA); and Harinath Bodugutla Venkata, Etobicoke (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Aug. 29, 2023, as Appl. No. 18/239,320.
Prior Publication US 2025/0075657 A1, Mar. 6, 2025
Int. Cl. F02C 7/04 (2006.01); F02C 9/18 (2006.01)
CPC F02C 7/04 (2013.01) [F02C 9/18 (2013.01); F05D 2260/96 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a fan operable for delivering air into a bypass duct;
the fan also operable for delivering air into a core engine housing, the core engine housing enclosing a compressor section, a combustor and a turbine section;
the core engine housing having an upstream end defining a separation point between the bypass duct and the core engine housing;
an air separation device including a baffle and an opposed louver, the baffle and louver curved for defining an airflow path to guide air with a radially outward and axially downstream components, there being baffle ribs on a curved surface of the baffle facing an opposed curved surface of the louver ribs on the louver, with at least some of the louver ribs being circumferentially offset from the baffle ribs; and
wherein a passage height of the flow channel between the louver and the baffle at a maximum distance is defined, and there being a baffle rib height of the baffle ribs on the baffle extending away from a nominal face of the baffle, with a ratio of the baffle rib height to the passage height being greater than or equal to 0.1 and less than or equal to 0.75.