US 11,885,242 B2
Diffuser ring with air manifold
Hervé Turcotte, Sainte-Julie (CA); Kenneth Parkman, Halton Hills (CA); Oleg Morenko, Oakville (CA); Nicholas Guglielmin, Toronto (CA); Gavin Kisun, Oakville (CA); and Ryan Miskie, Guelph (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on May 5, 2022, as Appl. No. 17/662,143.
Prior Publication US 2023/0358145 A1, Nov. 9, 2023
Int. Cl. F01D 9/06 (2006.01); F01D 25/24 (2006.01); F01D 25/16 (2006.01)
CPC F01D 9/065 (2013.01) [F01D 25/162 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01); F05D 2240/53 (2013.01); F05D 2260/60 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft engine comprising:
a compressor section having a compressor rotor rotatable about a central axis;
a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis;
a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and
an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.