Patent ID: 11885349
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A compressor for an aircraft engine, comprising:
a dual-impeller rotatable about a central axis, the dual-impeller having:
a first impeller having a first inlet and a first outlet located radially outwardly of the first inlet relative to the central axis, and
a second impeller rotatable with the first impeller, the second impeller having a second inlet and a second outlet located radially outwardly of the second inlet relative to the central axis, the first inlet and the second inlet facing opposite axial directions relative to the central axis; and

first conduits circumferentially distributed around the central axis, the first conduits having first conduit inlets and first conduit outlets, the first conduit inlets fluidly connected to the first outlet of the first impeller, the first conduit outlets fluidly connected to the second inlet of the second impeller; and
second conduits circumferentially distributed around the central axis, the second conduits having second conduits inlets, the second conduit inlets fluidly connected to the second outlet of the second impeller, a second conduit of the second conduits disposed circumferentially between two adjacent first conduits of the first conduits.