Pump Components TRIZ Cases

A composite casing integrates a perforated metallic ring to bond abradable coatings via plasma spraying.

A backing plate relief feature allows air to bypass diffuser vanes in aircraft compressors.

Swirl brakes dissipate rotational kinetic energy in multiphase pump passages to reduce rotor vibrations and maintain stability at high gas volume fractions.

Annular grooves in the balancing disc increase cross-sectional flow area, reducing pressure differences and power consumption fluctuations.

Shell converts connect to existing grooves to replace wheel sections, boosting stiffness while reducing downtime.

A screw-type pumping device moves liquid through coaxial rotor and stator cavities to generate hydraulic pressure.

A nickel braze alloy joins superalloy components via transient liquid phase brazing.

Integrally formed engaging members replace separate fasteners and hand tools, eliminating assembly labor costs while maintaining secure mounting security.

A two-phase flow pump uses a central liquid impeller and an outer gas turbine separated by a cylindrical wall to increase pressure for both fluid components.

A compressor wheel with a tapered connecting element guides fluid flow toward blade elements.

Segmented sliding vanes control boost pressure by minimizing expansion losses at varying exhaust flows, maintaining turbine efficiency across engine conditions.

Metal rings on a composite spool shell improve tribological performance and structural integrity while reducing weight.

A centrifugal blower system integrates a secondary gas inlet to mix separate streams internally.

An ion micro pump uses segmented electric fields to move gas without mechanical parts.

An airflow accelerator in the intake space increases gas speed toward impeller blades to reduce dust accumulation.

A compressor airfoil with a compound curvature profile on the suction side reduces aerodynamic losses.

Segmented housing sections and a baffle member direct vertical airflow while an anti-drip lip prevents water ingress during cleaning.

A hybrid magnetic suspension system stabilizes a compressor rotor using passive radial bearings and an axial bearingless motor.

Rear-surface balance holes paired with stress-relaxing recesses enable rapid on-site adjustment while minimizing centrifugal stress concentration.

A fan structure uses a protruding support shaft to maintain axial clearance between the impeller and external units.

A vacuum pump mounting arrangement uses a carrier with screw and spacer sleeve connections to absorb rotational energy.

Segmented multistage fan frames absorb motor vibrations to protect hard disc reading efficiency.

An air directing ramp in a furnace blower assembly redirects flow obliquely to prevent leaks and improve heating system performance.

A compressor control device adjusts inlet guide vane and variable stationary blade opening degrees to manage gas supply flow velocity.

Interchangeable pump segments with coaxial drive shafts resolve complexity trade-offs by combining outputs via a common passageway.

Segmented seal housing pipe with reinforced ribs resists hydraulic nozzle loads, enabling quick pump-motor shaft coupling without structural deflection.

Variable chord injection-molded plastic blades with serrated trailing edges reduce noise and energy consumption while maintaining high air circulation volume.

An arcuate heat shield intercepts radiated energy from compressor discharge air, preventing silencer module overheating and extending service life.

Single variable frequency drive controls dual shafts to maintain stage efficiencies while eliminating complex multi-motor control systems.

Mechanical differential valves replace complex electronic sensors to maintain pressure differentials and prevent leakage.

Segmenting the blade into equidistant bodies creates a cone-shaped outlet that increases wind force and coverage area.

Fiber metal laminate airfoils absorb impact energy through layered composite deformation while reducing overall component weight.

A fan assembly flow recirculation circuit draws downstream airflow and injects it upstream via stationary guide vanes.

Segmented closed-ended slots and composite materials secure sliders against disengagement during rotation, stabilizing gas flow.

Dynamic pitch control modules detect airfoil excitation phenomena and modify fuel flow to enhance propulsive efficiency while reducing cycle fatigue.

Relocating the electrical seal to the pressure zone eliminates glow discharge risks on conductors exposed to low-pressure vacuum environments.

A blower housing protrusion redirects airflow toward a static tap hole, accelerating vacuum switch triggering when exhaust paths block.

Elastically deformable turbomachine blade regions shift geometry under centrifugal force to maintain optimal aerodynamic shape across varying rotational speeds.

Closed-loop control with absolute angle detection eliminates open-loop misalignment, reducing metering variance and preventing leakage in orbital pumps.

Elastomeric rings and a buffer member absorb collision shocks to protect brittle thrust bearings from breaking during assembly.

Full extension of the L-shaped diffuser ring blocks reverse flow during shutdown, eliminating compressor backspin and transient loads.

A compressor impeller manufacturing method sequences inter-vane cuts to minimize post-cutting residual strain.

Segmenting the rotor from the stator isolates electrical components from hostile downhole conditions, reducing workover frequency and lost production time.

Dynamic adjustment of variable diffuser geometry and inlet guide vanes based on pressure recovery loading parameters prevents surge while maximizing efficiency.

Flat helix coil stator increases blade area by removing silicon steel sheets, reducing magnetic leakage through conductive structures.

A centripetal air bleed device channels cooling air through a rotor disc to manage thermal loads.