US 12,352,215 B2
Devices and methods for guiding bleed air in a turbofan engine
Alexandre Capron, Toronto (CA); Karan Anand, Mississauga (CA); and Hien Duong, Mississauga (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jun. 1, 2023, as Appl. No. 18/204,646.
Application 18/204,646 is a continuation of application No. 16/929,715, filed on Jul. 15, 2020, granted, now 11,702,995.
Prior Publication US 2023/0304448 A1, Sep. 28, 2023
Int. Cl. F02C 9/18 (2006.01); F02C 6/08 (2006.01); F02C 7/18 (2006.01)
CPC F02C 9/18 (2013.01) [F02C 6/08 (2013.01); F02C 7/18 (2013.01); F05D 2240/12 (2013.01); F05D 2260/606 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A louver for guiding bleed air into a bypass duct of a turbofan engine, the louver comprising:
an axial direction along a central axis of the turbofan engine and a radial direction perpendicular to the axial direction;
a first portion defining a flow-guiding surface at least partially defining a bleed air passage, the first portion having a first camber line extending from a leading edge of the louver to a trailing end of the first portion; and
a second portion extending from the trailing end of the first portion to a trailing edge of the second portion, the second portion protruding into the bleed air passage and having a second camber line that intersects the first camber line and forms a discontinuity in tangency with the first camber line at an intersection of the first camber line with the second camber line, the second camber line extending from the intersection to the trailing edge of the second portion, wherein:
the leading edge of the louver is axially forward of the intersection and axially forward of the trailing edge of the second portion;
the leading edge of the louver is radially inward of the intersection and radially inward of the trailing edge of the second portion; and
the trailing edge of the second portion is radially inward of the intersection.