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US 10,480,519 B2Granted
Hybrid compressor
AssigneeRolls-Royce North American Technologies Inc.
InventorWilliam B. Bryan
Life of this patent
Estimating the term…
Abstract
A compressor for a gas turbine engine is disclosed. The compressor includes a first compression stage mounted for rotation about a central axis that includes a plurality of first-stage blades. The compressor also includes a second compression stage mounted along the central axis aft of the first compression stage to receive air compressed by the first compression stage. The second compression stage includes a plurality of second-stage blades.
Claims17
A compressor for a gas turbine engine, the compressor comprising
- a first compression stage mounted for rotation about a central axis, the first compression stage including a plurality of first-stage blades, and
- a second compression stage mounted for rotation along the central axis aft of the first compression stage to receive air compressed by the first compression stage, the second compression stage including a plurality of second-stage blades, the second compression stage shaped to conduct air in a substantially radial direction away from the central axis and to discharge air in a substantially axial direction parallel to the central axis,
- wherein an average exit radius of the plurality of first stage-blades is greater than an inlet tip radius of the plurality of first-stage blades.
A compressor for a gas turbine engine, the compressor comprising
- a first compression stage mounted for rotation about a central axis, the first compression stage including a plurality of first-stage blades, wherein an average exit radius of the plurality of first stage-blades is greater than an inlet tip radius of the plurality of first-stage blades, and
- a second compression stage mounted for rotation along the central axis aft of the first compression stage, the second compression stage including a plurality of second-stage blades, the second-stage blades each having an inlet portion that has an inlet hub radius and an inlet tip radius, an outlet portion shaped to discharge air in a substantially axial direction parallel to the central axis that has an outlet hub radius and an outlet tip radius, and an average exit radius substantially midway between the outlet hub radius and the outlet tip radius that is greater than the inlet tip radius.
Dependencies are inferred from the claim text.