Pump Components TRIZ Cases

A debris trap uses a buoyant float valve to restrict particle size in liquid streams.

Modular exhaust assembly attenuates noise while auxiliary blower mounting arrangement reduces stress on the motor during shock loads.

Internal damping compartments with elastomeric material attenuate vibratory stress in gas turbine fan blades, extending fatigue life.

Extractable isostatic bearing support prevents fluid leakage while enabling easy maintenance of gas expansion turbines.

A Cu-Ni sintered alloy bearing utilizes a specific Ni-Sn-Cu-P grain boundary phase to enhance material performance.

Segmenting the fan blade body from a variable-area elliptical shroud prevents airfoil fracture while minimizing engine weight.

Frequency band filtering isolates stall energy from non-stall noise, reducing false positives and preventing premature VGD closure.

Flat circuit boards eliminate recesses to increase element quantity without adding structural complexity.

A thermal insulation layer on the damping ring controls thermal inertia, stabilizing radial clearances without air flow diversion.

Segmented shroud and baffle assembly fills air-filled cavities between rotor and stator to reduce vibration while maintaining strict forward shape requirements.

Sealed chambers and hydrophobic grease prevent salt crystal corrosion in semi-submerged vertical pumps.

Variable draft angle impeller design resolves manufacturing and efficiency trade-offs by reducing blade spacing divergence to improve pumping performance.

Peripheral bellows absorb axial bursting forces via elastic and plastic deformation, protecting housing connections without increasing construction volume.

Plane contact surfaces replace complex double curved profiles to reduce machining time and cost while maintaining blade stability.

Metal electrodes oxidize in air to control droplet motion, enabling low voltage operation and standard IC integration without high drive requirements.

A supplementary passage enables direct leaching fluid access to remote cooling zones within cast turbine blades.

A swirl control device adjusts fluid flow in pipelines using a feedback loop to maintain optimal conditions.

A ring generator uses a stator bell to create a pressure chamber for active air cooling, solving slow-speed thermal management and corrosion risks.

Stator vane ridges inject high-pressure air into the boundary layer to prevent separation, resolving asymptotic efficiency limits in axial compressors.

Mushroom-shaped anchors on a fan case engage elastic holding parts of a fan seal, preventing air leakage from thermal expansion while simplifying manufacturing.

A coolant pump uses a thermal conductor to bridge the motor control unit and containment shell.

A hermetically-sealed turbomachine uses a compliant mechanical coupling to transmit torque while thermally isolating the hot turbine end from the cool motor end.

Extending the volute inner wall surface axially increases flow path area, suppressing velocity spikes and pressure loss during radial miniaturization.

A centrifugal fan spacer creates separate air exhaust vents to manage airflow direction and pressure distribution within the enclosure.

Multiple bearings arranged around a rotating plate distribute radial loads evenly, reducing friction and extending the blower's operational lifespan.

Segmented pump casings with dedicated leg portions resolve vibration and noise issues in twin pump configurations.

Centrifugal force activates a bistable presser between blade roots and disk slots, reducing fretting wear while ensuring accurate rotor balancing.

Inverting a balance piston to the suction side exposes mechanical seals to stable discharge pressure for precise barrier fluid regulation.

Nested zigzagged fluid passages with radial and chordal components enhance convective heat transfer at high-temperature trailing edges.

Fluoropolymer linings on high-speed centrifugal pump seal housings prevent fluid buildup and fouling while maintaining structural integrity.

Segmented compressor casings use porous thermal breaks to reduce gradients, maintaining clearance gaps while simplifying assembly.

Pre-swirl contours on the nacelle inner wall condition airflow to eliminate shock losses and flow separation at high rotational speeds.

An asymmetric screw groove design suppresses suction side pressure increases by minimizing backflow from the exhaust side.

Segmented bearing housing segments align via hollow dowels that transport fluid, enabling electric motor rotor assembly within tight bores.

A turbomolecular pump uses a rectangular second inlet opening to reduce transverse space requirements.

An airflow passage guides air from a high pressure zone to a low pressure zone within the fan frame.

A pump foot uses flexible hinges and snap connections to pivot between stable positions.

Curved air intake duct structure directs fluid swirl to enhance pressure ratio and stability, expanding the operating range without mechanical mechanisms.

Inlet opening directs tempering gas flow to reduce thermal stratification and prevent rotor rubbing during shutdown.

A radially sloped face on the stator vane platform directs compressed air along the shroud surface.

A turbine compressor inner band integrates a cooling air circuit to dissipate heat from seal fingers.

A fan blade with a third-order polynomial leading edge curve reduces flow discontinuities and turbulence at transonic speeds.

Elastomeric grommets couple the hanger bracket to the mounting plate, reducing vibration noise transmission during operation.

A tower fan housing assembly features a detachable air-throughflow part mounted via a slide fastener structure for easy access to the internal fan wheel.

Variable curvature leading edges reduce shock loss at high velocities while maintaining flow volume through local quality optimization.

A translation assembly pushes a flexible impeller through a constraining sleeve into a water pump cavity.

Active cooling through rotor openings reduces thermal stress on the sealing lip, resolving the weight versus stability trade-off in jet engine designs.

Alternating high and low modulus materials in the shroud reduce rotor loading, allowing tighter clearances without blade instability.

Segmented bleed passages with circumferential tapering reduce pressure differential and vortices in gas turbine engine shrouds.

Isolated internal cooling passages with distinct inlet feeds direct separate fluid streams to leading and trailing edges of gas turbine components.