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US 8,192,141 B1Granted
Dual compression rotor
AssigneeThe United States of America as represented by the Secretary of the Air Force
InventorMark R. Dale
Life of this patent
Estimating the term…
Abstract
The present invention provides a gas turbine rotor having a first axial compression stage for compressing air in a first direction and a second axial compression stage for compressing the air in a second direction, the second direction being generally opposite the first direction.
Claims12
A gas turbine rotor comprising:
- a plurality of first axial compression blades configured for compressing air in a first direction, the plurality of first axial compression blades having a first blade quantity and a first blade height;
- and
- a plurality of second axial compression blades configured for compressing the air from the first axial compression blades in a second direction, the second direction being generally opposite the first direction, the plurality of second axial compression blades having a second blade quantity that is greater than the first blade quantity and a second blade height that is less than the first blade height, wherein the plurality of second axial compression blades are discontinuous with the plurality of first axial compression blades and extend radially outward from the plurality of first axial compression blades such that the plurality of second axial compression blades are substantially coplanar with the plurality of first axial compression blades.
A gas turbine rotor comprising:
- an inner ring;
- a plurality of first axial compression blades connected to the inner ring, the plurality of first axial compression blades having a first blade quantity and a first blade height;
- an intermediate ring connected to the plurality of first axial compression blades;
- a plurality of second axial compression blades connected to the intermediate ring, the plurality of second axial compression blades having a second blade quantity that is greater than the first blade quantity and a second blade height that is less than the first blade height, wherein the plurality of second axial compression blades are discontinuous with the plurality of first axial compression blades;
- a rim connected to the plurality of second axial compression blades;
- and
- a plurality of turbine blades connected to the rim, the plurality of turbine blades having a third blade quantity that is greater than the second blade quantity and a third blade height that is greater than the second blade height, wherein the plurality of turbine blades are discontinuous with the plurality of second axial compression blades.
4 more elements
Dependencies are inferred from the claim text.