Pump Components TRIZ Cases

External ventilation unit cools motor housing using radial guide devices.

Spring biasing eliminates gear backlash and hysteresis in variable stator vanes, improving angle accuracy while accommodating manufacturing tolerances.

Heating the housing engaging portion via induction allows plastic deformation during swaging, maintaining precise clearance between the cover and impeller.

A non-linear linkage mechanism connects the actuator to a movable wall member within a variable geometry turbine housing.

Integrating a torsional spring into the clamp structure eliminates screw fastening, reducing assembly complexity and improving production efficiency.

A slider seal assembly uses a moveable composite plate within a curved housing recess to maintain sealing contact across rotating interfaces.

A snap-fit fixing structure secures a fan unit to an electronic equipment housing using elastic engagement portions and guiding features.

Asymmetric stator vanes create time delays that cancel excitation forces, preventing harmful rotor-stator vibrations.

A fan assembly nozzle directs airflow to separate outlets for amplified or non-amplified delivery via a valve mechanism.

Axially movable turbine rotor adjusts brush seal clearance to minimize leakage flow during thermal expansion cycles.

Pressurized oil jet impinges casing surface to cool turbomachine seal elements, reducing heat flux and preventing elastomer degradation at high temperatures.

Differential speed gearing resolves the conflict between pump weight reduction and multiphase flow efficiency in aero-engine fuel systems.

A passive microfluidic pump uses capillary action to drive fluid flow through resistive and absorbent regions without external power.

An axial compressor blade features an S-shaped leading edge profile that redistributes fluid flow to reduce aerodynamic losses.

Integrated liquid separator and compressor handle well flow liquid without separate pumping systems, reducing system height and complexity.

Axial wall surfaces in the second recess area prevent claylike balance weight separation from centrifugal forces, ensuring stable operation.

An eccentric screw pump meters fluid volume independently from gas atomization, eliminating blob formation on substrates.

A three-concentric tube gas-liquid separator directs liquid into the inner tube while routing gas upward through the middle annulus.

Baffles intercept radial cooling air in the annular cavity to create circumferential flow around the inner casing.

Mounts the pump rotor directly on a pinion shank to eliminate separate shafts and guide bearings, reducing accessory box volume.

A propeller fan blade features a recessed portion at the trailing edge to redirect inward air streams and stabilize flow distribution.

Segmented safety and adjustment chambers reduce hydraulic complexity while maintaining reliable over-pressure protection and adaptive pressure control.

An inverted supercharger system with an interlaced cross-runner pattern reduces parasitic power loss by utilizing intake air pressure differentials.

Forming a contact surface on the axially forward or aft side of the outer shroud minimizes edge damage during pretwist measurements.

Edge guards with internal heating conduits prevent ice formation on turbine engine fan blades.

An expandable housing air blower adjusts internal volume to suppress noise during operation.

Variable speed transmission matches booster compressor output to pneumatic demand, stabilizing airflow and pressure while exhausting excess gas.

Segmented caps replace complex stelliting to resolve wear resistance versus manufacturing complexity.

Integrating a modular low NPSH stage eliminates external boost pumps, reducing system complexity and manufacturing costs.

A reconfigurable grille switches vane curvature to produce focused laminar or turbulent splayed flows.

Segmented overmolded flux ring design distributes heat via ventilation openings and flexible arms, minimizing thermal stress during eddy-current operation.

An integrated blower control assembly combines start and speed functions to prevent accidental maximum speed activation, enhancing user safety.

Curved biasing support members reduce operating clearances between turbine shells, minimizing friction and wear while maintaining structural stability.

A single-piece outer shroud assembly secures axial turbomachine compressor stator vanes to the casing.

Optimized inlet geometry in a ported shroud compressor housing reduces first-order pulsation noise and improves rotor stability.

A compressor assembly method uses a positioning member to align bearings independently.

A beveled circumferential wall edge redirects liquid flow from horizontal to vertical orientation within a compact intake device.

Wing-like flow deflection devices reduce vortex formation to improve energy capture at low wind speeds.

Segmented bolt shafts and spacer elements create captive clearance fits that prevent conduit cracking while enabling finger access to threaded connections.

A lowered skeleton curve portion adapts to circumferential platform depressions, reducing shockwave losses and maintaining uniform speed distributions.

A mechanical linkage couples a bleed valve actuator to a variable outlet guide vane.

Curved pump surfaces minimize material damage during transport while maintaining high torque stability.

A hidden fan lamp uses a turntable assembly to drive fan blades via elastic components and linkage mechanisms.

A wet seal chamber isolates pump seals from debris using a compressible bladder to maintain pressure balance and prevent overheating during idle operation.

Truncated sphere bearing interface dissipates imbalance energy via friction, eliminating fusible pins and reducing structural rupture risk.

An epicyclic gearbox decouples fan and turbine speeds, resolving the trade-off between propulsive efficiency and engine weight.

Discrete circumferential grooves in the compressor casing manage tip leakage flow to increase stall margin without reducing engine efficiency.

Contoured three-dimensional airfoil surfaces defined by Cartesian coordinates improve second stage turbine nozzle guide vane efficiency by 1.38%.

A turbocharger housing seal insert supplies fluid to adjust pressure differences across piston rings.

An electric coolant pump positions the electronic power circuit radially outside the pump chamber to leverage centrifugal convection for thermal management.