Supersonic compressor

A supersonic gas compressor for compressing a selected gas, comprising:

• a casing comprising a low pressure gas inlet and a high pressure gas exit;
• a rotor comprising a plurality of blades and configured to act on a selected gas to impart axial and tangential velocity thereto to provide a supersonic gas flow;
• a stator comprising a diffuser including one or more aerodynamic ducts configured for diffusing a gas received therein, said one or more aerodynamic ducts each having a converging portion, a diverging portion, and an effective contraction ratio, such that, with input of a supersonic gas flow, each aerodynamic duct generates a plurality of shock waves (S1 to Sx) in said selected gas as said selected gas passes therethrough, said one or more aerodynamic ducts having an inlet relative Mach number for operation associated with a design operating point selected within a design operating envelope for a selected gas composition, gas quantity, and gas compression ratio, wherein said one or more of said aerodynamic ducts are helically arranged around a longitudinal axis, said one or more aerodynamic ducts comprising
• (a) a geometrically adjustable portion, operable to adjust said effective contraction ratio, and
• (b) boundary layer control structures, said boundary layer control structures comprising one or more of (1) outlet bleed ports for boundary layer removal, (2) inlet jets for energizing a boundary layer by gas injection, and (3) one or more vortex generators, said one or more vortex generators each comprising a base with a forward end and a leading edge extending outward and rearward from said forward end to an outward end, wherein said leading edge comprises a first angular discontinuity at a height H1 above said base, and a second angular discontinuity at a height H2 above said base, for generating at least two (2) vortices.