Pump Components TRIZ Cases

Interchangeable downrods and an adjustable canopy resolve the trade-off between universal ceiling height compatibility and complex mounting hardware.

A pump mechanism uses a movable basket and segmented protrusions to enable precise level adjustment via a trigger-actuated switch bar.

Brittle sheath absorbs impact energy on fan blade leading edges, localizing damage to preserve structural integrity against debris strikes.

Radial orifices in a compressor spacer direct cooling air to reduce temperature gradients across stages.

Pre-fabricated universal housings with adjustable stator spacers accommodate various rotor lengths, reducing manufacturing costs and delivery time.

A composite turbine blade profile optimization method balances centrifugal and aerodynamic forces to reduce mechanical stress at the root.

Hollow drive shafts extract heat from motor housings to reduce temperature while maintaining control precision and minimizing device complexity.

Segmented heating zones in the side inlet air intake reduce compressor noise and eliminate costly acoustic nozzles.

Segmented outer core casing arrangement enhances structural stiffness in aircraft gas turbine engines, reducing flexing and weight penalties.

A compressor sealing channel connects a high-pressure region to the first segment, directing fluid flow to increase local pressure.

Merges diffuser vanes and deswirler into one component to prevent energy loss from inlet flow angle changes while reducing compressor weight.

Variable cross-section outlets resolve the trade-off between low liquid pressure and high flow rate by converting kinetic energy to pressure.

Optimized leading edge sweep and dihedral angles reduce shock losses and boundary layer buildup in high-speed gas turbine compressor stages.

Segmented flanges with recessed pockets reduce thermal mass while an impingement baffle directs non-chargeable air for effective cooling.

A rotor disk features an elongated balancing mark in the blade channel to reduce rotational imbalance.

A hybrid rotor design combines solid and hollow blades to independently tune vibratory responses across the engine stability pinch point.

Differentiating arcuate clearance from spiral clearance accommodates thermal expansion, suppressing positional deviation of seal points.

Heat shield prevents conduction from discharge cavity to seal cavity, maintaining temperature control at high compression ratios.

Interrupters on the fan blade support break up eccentric vortices, eliminating aerodynamic noise and motor inefficiency caused by unstable airflow patterns.

Segmented housing clearances prevent blade interference while maintaining airflow performance.

A single stage high pressure turbine vane airfoil profile defined by Cartesian coordinates equalizes static pressure gradients across the spanwise direction.

Identical platform overhangs balance centrifugal deformation stresses, halving radial movements and optimizing joint stress for stable aerodynamic performance.

Three-dimensional LTCC coils resolve aerodynamic trade-offs while ensuring accurate rotational speed measurements.

A single variable speed pump moves blended fluid while flow control valves maintain target ratios, eliminating complex multi-pump systems.

A waterproof axial flow fan uses ring collection grooves on the stator resin surface to manage water near the bearing.

A composite cover overlays hollow cavities in a metallic fan blade body, secured by a peripheral edge received within a slot featuring an inward lip.

A multistage pump bypass system redirects balancing flow to increase clearance gap pressure.

Casing groove walls generate aft directed jets to control tip leakage flow in gas turbine compressors.

A roof box with a lateral opening and segmented interior compartments resolves loading height constraints while maintaining aerodynamic efficiency.

Segmented blower impeller directs air through distinct front and rear blade series, resolving the trade-off between power source cooling and airflow rate.

An integrated connection block with internal channels reduces leakage risk by eliminating external pipe joints in liquid cooling stations.

Spring-loaded counter-element prevents rubbing during start-up, eliminating separate housings and lubrication requirements.

Ceiling fan motor connects brace and blade iron using engagement elements that contact a vibration dampener, reducing oscillation without ornate blade irons.

A bottom-mounted pump generates positive pressure in a vertical cold water pipe, eliminating negative pressure that requires costly reinforcement.

Aligned discrete contact zones on the fan hub reduce bending moments and distortion under high temperatures.

Dual blade bumps improve compression while minimizing corner separation.

Segmented radial ribs guide upstream air through the shaft hole to downstream regions, reducing stagnation volume and improving air-sending efficiency.

A sealless pump uses a dual impeller design to supply fluid to non-contact bearings, eliminating contamination risks from cooling systems.

Upstream particle separator cleans motor cooling air via centrifugal separation, resolving low ram pressure bottlenecks at lower flight speeds.

A suction-side elevated portion on an axial flow blade modifies the trailing edge geometry to adjust the outflow angle near the hub and tip regions.

Recessed cavities and integral tabs prevent pump tipping to ensure complete liquid discharge.

Inducer channels cooling air to the aft stage, reducing transient peak temperatures and enabling higher pressure ratios.

Heated composite blank sheet presses against a fan blade mold with shorter center length to align main fibers and prevent wrinkling.

Segmented pipelines and sensor feedback control the suck-back pump, preventing nozzle dripping and chemical waste in etching machines.

A magnetic bearing controller adjusts electromagnet currents using displacement-based equations to maintain stable non-contact support.

Mixing ram air with bleed air in a dual entry turbine drives the compressor, reducing fuel burn by 40-75% compared to conventional systems.

Segmented coatings and panel cooling channels increase airfoil thermal resistance, eliminating compressor bleed cooling requirements.