Supersonic Fluid Pumps TRIZ Cases

See how fluid recirculation through rotor-stator assemblies achieves high temperatures in fewer

A supersonic bladeless rotor pumps gas by molecular impingement, extending vacuum range without seals, blade wear, or multistage complexity.

Shock-wave heating in a zoned supersonic diffuser converts fluid kinetic energy into thermal energy while staying compact and tolerant of back pressure.

A larger-inlet, smaller-outlet channel between overlapping stator blades limits blockage and separation in transonic compressors.

Adjustable shock bodies vary supersonic passage throats, helping a two-rotor compressor maintain pressure and efficiency at part load.

Offset rotor vanes with compression ramps generate oblique shockwaves to compress fluid within flow channels.

Impeller peripheral velocity exceeds sonic limits to maintain compact size while boosting intake air supply.

Concave airfoil regions moderate passage shocks on suction and pressure surfaces, reducing pressure loss by suppressing boundary layer separation.

An axially translatable fluid control device adjusts the throat area to resolve startup and steady-state performance trade-offs.

A supersonic compressor rotor uses a third independently rotatable disk with a raised surface structure to adjust the fluid flow channel throat area.

Helical adjustment of centerbodies in supersonic passageways resolves startup challenges and reduces aerodynamic losses.

Intermediate stator vanes redirect airflow to prevent blockage and enable compact transonic compressor designs.

A compressor rotor blade profile uses continuous curvature progressions to reduce flow shedding and maintain lower Mach numbers on the suction side.

Compressor rotor blades operate at rotational speeds shifting blade passage frequency above 5500 Hz to reduce noise sensitivity.

Angled compression ramps in a supersonic compressor rotor create oblique shockwaves that prevent normal shockwave formation and reduce entropy rise.

Forward-swept fan blades confine inboard flow regimes to preserve low-pressure zones, reducing transonic turbulence and improving propulsion efficiency.

A supersonic compressor rotor uses a transition surface to adjust fluid flow orientation between axial and radial paths.

Series counter-rotating supersonic rotors boost pressure ratios while reducing system weight and complexity compared to conventional multi-stage designs.

Segmented diffuser vanes with supersonic ramps compress fluid via shock waves, achieving 10:1 ratios without increasing component count.

A compressor impeller features main blades with an inclined leading edge to enhance high-speed rotation performance.

Segmented vanes in a curved annular passage deswirler fluid exiting the centrifugal compressor to reduce system footprint while maintaining diffusion quality.

Alternating blade types generate distinct shock patterns that aerodynamically mistune the rotor, reducing supersonic flutter and resonant stress loads.

A transonic blade shifts its stacking line upstream to reduce shock loss and improve stall margin in axial-flow rotating machines.