A counter-rotating supersonic compressor. A first subsonic rotor includes a plurality of unshrouded impulse rotor blades operating at sub-sonic conditions. A second, supersonic rotor includes a fixed second rotor portion and an adjustable second rotor portion. The fixed second rotor portion includes a plurality of supersonic passageways having converging-diverging sidewalls, and internal boundary layer bleed passageways. The adjustable second rotor portion includes a plurality of centerbodies which are disposed in the supersonic passageways. Helical movement (circumferential and axial) movement of the adjustable second rotor portion with respect to the fixed second rotor portion enables upstream and downstream movement of the centerbodies in the supersonic passageways. This movement facilitates ease of supersonic startup, and automatic adjustment for changes in operation conditions, such as pressure, temperature, or mass flow rate of a working fluid such as carbon dioxide.

An engine using centrifugal pumps to form a centrifugal multistage reverse compressor with flow alternating inward and outward in series. It is fed, at either the periphery or the center of one of the pumps, by either compressed then heated air or by products of combustion. This invention also includes a set of related inventions, comprising a group of flow guides to convert radial flow to axial flow and a group to convert axial flow to radial flow and the combination of those flow guides. The invention also includes a multistage centrifugal compressor using combinations of centrifugal pumps with alternating pumps having inward flow of gas traveling from the periphery to the vicinity of the axle and having outward flow of gas traveling from the vicinity of the axle to the periphery. The invention also includes the using the above in an external heat engine or heat pump.

Methods and systems are provided for an adjustable diffuser of a turbocharger compressor. In one example, a compressor includes a diffuser formed in a compressor housing downstream of an impeller of the compressor, the diffuser including guide blades mounted on a rotatable annular support of the diffuser. Further, an engine controller may adjust rotation of the annular support based on one or more engine operating conditions.

Example implementations relate to a fan module. The fan module may include an outer impeller having a first plurality of radial blades arranged between an inner circumference of the outer impeller and an outer circumference of the outer impeller. The outer impeller may be rotatable about a first axis of rotation. The fan module may include an inner impeller having a second plurality of radial blades, the inner impeller disposed within the inner circumference of the outer impeller and rotatable about a second axis of rotation.

A counter-rotating supersonic compressor. A first subsonic rotor includes a plurality of unshrouded impulse rotor blades operating at sub-sonic conditions. A second, supersonic rotor includes a fixed second rotor portion and an adjustable second rotor portion. The fixed second rotor portion includes a plurality of supersonic passageways having converging-diverging sidewalls, and internal boundary layer bleed passageways. The adjustable second rotor portion includes a plurality of centerbodies which are disposed in the supersonic passageways. Helical movement (circumferential and axial) movement of the adjustable second rotor portion with respect to the fixed second rotor portion enables upstream and downstream movement of the centerbodies in the supersonic passageways. This movement facilitates ease of supersonic startup, and automatic adjustment for changes in operation conditions, such as pressure, temperature, or mass flow rate of a working fluid such as carbon dioxide.

A counter-rotating supersonic compressor. A first subsonic rotor includes a plurality of unshrouded impulse rotor blades operating at sub-sonic conditions. A second, supersonic rotor includes a fixed second rotor portion and an adjustable second rotor portion. The fixed second rotor portion includes a plurality of supersonic passageways having converging-diverging sidewalls, and internal boundary layer bleed passageways. The adjustable second rotor portion includes a plurality of centerbodies which are disposed in the supersonic passageways. Helical movement (circumferential and axial) movement of the adjustable second rotor portion with respect to the fixed second rotor portion enables upstream and downstream movement of the centerbodies in the supersonic passageways. This movement facilitates ease of supersonic startup, and automatic adjustment for changes in operation conditions, such as pressure, temperature, or mass flow rate of a working fluid such as carbon dioxide.