Centrifugal compressor with axial impeller exit
AssigneeRolls-Royce North American Technologies Inc.
InventorWilliam B. Bryan
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a centrifugal compressor having an improved impeller structure. The impeller structure includes a near axial discharge configuration thus reducing the overall size of the envelop surrounding the compressor assembly. The impeller structure may have axial exit vanes.
Claims20
A gas turbine engine comprising:
- a centrifugal compressor having a rotational axis;
- and
- a rotating impeller structure having an inlet and a discharge, the inlet has a first central axis that may be parallel to the rotational axis or at an angle, the discharge has a central axis that is substantially parallel to the rotational axis.
The gas turbine engine as claimed in claim 5, wherein the exit member that is connected to the second vane has one of a longitudinally extending axis that may be substantially parallel to the rotational axis, or have a substantial angle to the rotational axis, or have a curved axis relative to the rotational axis.
A gas turbine engine comprising:
- a centrifugal compressor having a rotational axis;
- and
- an impeller housing having an axial discharge that is aligned with the rotational axis.
A gas compressor for use in connection with a machine comprising:
- a centrifugal compressor having an impeller discharge average radius greater than the inlet tip radius;
- and
- an impeller system for the centrifugal compressor, the impeller system having an inlet port and an outlet port, the impeller further having near axial discharge of gas.
Dependencies are inferred from the claim text.