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US 7,390,163 B2Granted
Radial flow turbine
AssigneeLuke W. Clauson
InventorLuke W. Clauson
Life of this patent
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Abstract
A multi-stage radial flow compressor and turbine includes a rotor having a first plurality of blades and a second plurality of blades radially outward from the first plurality. A stator has a plurality of blades radially positioned between the two sets of rotor blades. The stator also includes a plurality of combustors positioned radially outward from the stators. The rotor also has turbine blades radially outward from the combustors which are driven by the combusted gas.
Claims23
A multi-stage compressor and turbine, comprising:
- a housing;
- a gas inlet coupled to the housing;
- a gas outlet coupled to the housing;
- a rotor having a first plurality of rotor blades and a second plurality of rotor blades both being positioned radially outward from the gas inlet, the rotor being rotatable about an axis of rotation relative to the housing, the axis of rotation defining radial directions perpendicular to the axis of rotation;
- a stator having a first plurality of stator blades positioned radially outward from the first plurality of rotor blades and radially inward from the second plurality of rotor blades, the stator also having a plurality of combustors positioned radially outward from the second plurality of rotor blades;
- the rotor also having a plurality of rotor turbine blades positioned radially outward from the plurality of combustors.
3 more elements
A compressor and turbine, comprising:
- a housing;
- a gas inlet coupled to the housing;
- a gas outlet coupled to the housing;
- a rotor having a first plurality of rotor blades positioned radially outward from the gas inlet, the rotor being rotatable about an axis of rotation relative to the housing, the axis of rotation defining radial directions which are perpendicular to the axis of rotation;
- and
- a stator having a first plurality of stator blades positioned radially outward from the first plurality of rotor blades, the stator also having a plurality of combustors positioned radially outward from the first plurality of rotor blades;
- the rotor also having a plurality of rotor turbine blades positioned radially outward from the plurality of combustors, the rotor having a radius defined by a radial distance from the axis of rotation to a radially outermost part of the rotor turbine blades, the first plurality of rotor blades having a radially outermost part which extends radially outward to a position no more than one half the radius of the rotor.
4 more elements
A compressor and turbine, comprising:
- a housing;
- a gas inlet coupled to the housing;
- a gas outlet coupled to the housing;
- a rotor having a first plurality of rotor blades positioned radially outward from the gas inlet, the rotor being rotatable about an axis of rotation relative to the housing, the axis or rotation defining radial directions perpendicular to the axis of rotation;
- and
- a stator having a first plurality of stator blades positioned radially outward from the first plurality of rotor blades, the stator also having a plurality of combustors positioned radially outward from the second plurality of rotor blades;
- the rotor also having a plurality of rotor turbine blades positioned radially outward from the plurality of combustors, the rotor having a radius defined by a distance from the axis of rotation to a radially outermost part of the rotor turbine blades, the first plurality of rotor blades having a radial length defined by a radial distance from a radially innermost part to a radially outermost part which is less than one third the radius of the rotor.
4 more elements
Dependencies are inferred from the claim text.