Patent ID: 7390163
Filing Date: 2008-06-24
Classification: F01D,F02C

Abstract:
1. 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.