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 |
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.
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