Pump Components TRIZ Cases

A one-piece molybdenum gas bearing sleeve cuts machining cost and complexity while maintaining tight clearance, heat dissipation, and high-speed shaft stability.

A partition wall and oil introduction passage keep the ring member from churning stored oil, improving speed increaser efficiency.

Shaped gear tooth and bushing microsurfaces improve axial balance, thicken lubricating films, and reduce wear, leakage, and power loss.

Variable bearing stiffness and damping help turbomolecular pumps pass resonance speeds with less vibration and noise while maintaining stable rotor support.

A slide-bearing gear bush and optimized gear meshing cut wear in internally rotating gear pumps handling viscous or solid-laden fluids.

A shaft-mounted transfer device and deflector keep bearing oil feed stable, recirculate lubricant, and prevent migration into the pump.

A vane-induced in-line deaerator removes entrained gas from auxiliary oil flow, preserving bearing lubrication during windmilling.

Pressurized gas is added only at startup and slowdown so turbocharger gas bearings stay contactless at low speed without bulky continuous air supply.

A lead screw puller with hooked arms removes variable stator vane bushings without rotor disassembly, cutting turbine maintenance time and cost.

Damaged bearing support and web sections are cut out and replaced with a welded insert, restoring compressor housing integrity with less waste.

A hollow threaded balancing weight combines mass correction and fluid venting in one impeller hole, cutting hub diameter and improving compressor efficiency.

A head-mounted blower and elastic seal cut hose bulk and damp noise while maintaining therapeutic pressure and humidity.

A measuring duct inside the non-return valve lets an internal pump sensor track delivery pressure without external cables, cutting size and assembly complexity.

Adjusting formed-tool parameters during each pass machines variable-lead screw rotors with accurate meshing profiles and lower leakage.

Extracted production gas feeds compressor gas bearings, enabling heavy rotor support with simpler oil-free architecture and low maintenance.

An axial pump assembly combines a friction clutch and electric motor to maintain engine coolant flow in low-rpm and shutdown conditions.

A compact aero-thermo model estimates thrust in real time, improving engine power control without heavy onboard computation.

A Holweck-style blocking stage in the rotor-stator gap lowers pressure around the magnetic bearing to keep process gases out and extend service life.

A spring-biased check valve vents expanding argon from a welded fan blade cavity to prevent bulging and preserve structural integrity.

Built-in oil passages in the pinion fairing deflector feed both teeth and barrel, easing mounting and improving low-pressure startup lubrication.

A clutch-based turbine lock blocks reverse shaft rotation in submersible ESPs, reducing restart overload, leakage risk, and electrical hazards.

Independent axial loading with a shaft sleeve, lock nut, and balance collars improves turbocharger rotor balance and stability at high speed.

Angled oil supply holes create a vortex that mixes fresh and mainstream lubricant, lowering oil temperature and stabilizing bearing load capacity.

Sacrificial flanges guide thin aerofoil sheath alignment during laser welding, reducing defects while forming a smooth curved outer profile.

Radial bearing housing arms cut contact with the compressor housing, limiting heat transfer while improving ambient heat convection.

Bleed gas handles bearing support in normal operation, while intermittent external static pressure keeps the rotor stable at low speed.

An elongate carrier pipe links inlet and outlet ports to stiffen a sheet steel pump base, cutting weight and cost without losing stability.

Two bushing sections with a movable connection fit improve rotor unit molding accuracy, avoiding post-machining and lowering cost.

Fuel or oil circulation stabilizes the solenoid valve in a bleed valve controller, preventing icing and enabling reliable high-temperature operation.

Internal through-passages in a magnetic pump bearing holder preserve axial stiffness while reducing inlet gas-flow restriction.

A rotating downrod adapter lets the ceiling fan fold for transport, cutting package volume while avoiding loose-part loss and handling issues.

Star-shaped webs and an elastomer bearing bush simplify blower housing assembly while supporting the motor and reducing airflow blockage.

Circumferential ribs and guiding ribs create a heating band channel that enables easy retrofit and replacement without full fan housing disassembly.

Cooling passages and insulated retainers protect flexible manifold seals from heat-driven leakage, wear, and shrinkage in propulsion systems.

Laser welding joins the rotating shaft directly to the metallic case, removing raised ring features to simplify molds and slim the fan.

Longitudinal bending bars create a replaceable frangible fuse that controls breaking torque and simplifies turbine cooling unit maintenance.

A numerical rotor model uses measured deflection below critical speed to calculate modal imbalance without test weights.

A front mount and flange position ratio helps large gas turbines resist fan-driven bending loads while preserving core stiffness and efficiency.

A continuous metal sheath wraps the fan blade core to improve structural integrity and resist cracking from debris and foreign object impact.

Centrifugal gas removal inside a hollow rotor maintains low flywheel vacuum pressure without turbomolecular pumps, cutting friction and maintenance.

Integrated curvilinear plate channels replace complex bleed-air piping to cut pressure loss and weight while maintaining heat transfer.

A hollow shaft cavity preserves shrink-fit coupling at high speed while lowering assembly force, shaft damage risk, and rotor mass.

A widened blind slot bottom with paired arcs redistributes vane-seat stress, enabling smaller or larger shaft sizing without sacrificing pump strength.

Curved transition portions on a ceiling fan blade reduce turbulence caused by manufacturing distortions, enhancing aerodynamic efficiency.

Segmenting motor current from magnetic bearing load enables precise power calculation for multiple semiconductor manufacturing pumps.

Partitioned plenums balance pressure in secondary gas flows without air diverters, improving cooling efficiency.

An impeller fixing mechanism immobilizes the rotating component relative to the pump shaft using flexible elastomeric members.

An annular sleeve with rolling elements distributes torsional and bending stresses on the spindle, improving durability.

Elastically deformable fastening parts thermally decouple wear rings from stators, preventing sealing gap shrinkage during thermal transients.

Concave-and-protrusion ridges mesh to reduce axial size and prevent rattling without separate gaskets.

Optimized airfoil profiles defined by specific Cartesian coordinates improve compression efficiency in multi-stage axial compressors.

Alternating carbon-fibre and glass-fibre blocks in fan casings resolve weight versus debris retention trade-offs through optimized stiffness distribution.

Segmented fan spacer adjusts housing dimensions to increase flow rate and pressure without requiring new tooling or complex scroll shapes.

Cylindrical foam block rotors generate cooling airflow via volumetric resistance, reducing acoustic noise while maintaining thermal performance.

A fan with an internal rotor structure and magnetic element receptacle enables dynamic balance maintenance during high-speed operation.

Outer rotor motor drives segmented impellers to generate static pressure difference, eliminating dead zones caused by low torque in inner rotor designs.

Segmented nacelle design positions an independent access door inside the housing to bypass fan cowl requirements and reduce maintenance time.

Segmented heating zones compensate for cryogenic contraction in end heads, preventing seal interference across wide temperature ranges.

Mixed air flow paths combine compressor extracted air with cooling air to reduce turbine rotor temperature and improve thermal responsiveness.

Rotating scoop tubes channel scavenge oil through cooler pathways, eliminating cooling air requirements and preventing coking in hot gas turbine frames.

A mechanical lubrication device adjusts oil flow via a centrifugal governor, preventing epicyclic gear flooding at low speeds.

A self-supported boom rotates on a rear turret to clear debris, eliminating front track obstructions that block the operator's view.

A turbine housing uses a linear area-to-radius distribution to deliver uniform exhaust gas flow across the turbine wheel circumference.

A battery holder secures a button cell on the electronics housing printed circuit board.

A mixed-flow fan uses a hub with inclined outer surfaces to direct airflow at an angle between axial and centrifugal modes.

An extension divides the bearing chamber into two pockets, routing clean fluid to the thrust bearing while trapping debris in a separate pocket.

Axially offset orifice guides air to multiblade impeller blades, preventing backflow and reducing noise.

Monoblock housing with angled rotors eliminates complex sealing while reducing peripheral speed and enabling multi-stage compression.

A vane pump insert merges housing and body functions into a single component secured by a retaining ring.

Segmented aluminum stiffeners connect the casing to guide vanes, reducing vibration from 25 ips to 10-15 ips without modifying existing modular structures.

Segmented shaft design isolates threaded attachment zones from smooth bearing sections, preventing chip contamination during lubrication system assembly.

A motor vehicle fan uses pseudo-random blade offsets to eliminate harmonic noise.

Segmented torque tube units distribute cooling air to turbine disks, resolving inadequate temperature reduction in gas turbines.

Segmented counter moulds orient and compact fibres radially to resolve flange stress trade-offs.

A fan motor housing integrates a vertical groove to position lead wires radially inward within the structure.

Spraying detergent liquid into the compressor inlet during operation to clean fouling without shutting down the engine.

Replacing heavy mechanical surfaces, a plasma actuator generates ionized gas to ignite fuel and stabilize combustion for faster hypersonic response.

Laser welding the core to a downward-protruding sleeve seat minimizes axial space, resolving the contradiction between fan thickness and fastening strength.

Transverse groove and radial rib secure the sealing member support, reducing weight while preventing detachment under axial pressure.

Segmenting the shroud into axially spaced pockets separated by ribs distributes noise absorption across the assembly while maintaining operational efficiency.

A turbine stage with a vane count exceeding the blade count directs cooling air to mix with combustion products.

Non-equidistant hub connections and blade spacing disrupt periodic air pressure variations, lowering sound volume at the structure pass frequency.

A high pressure turbine vane airfoil profile defined by specific Cartesian coordinates optimizes aerodynamic and structural performance.

Bleed ports relieve trapped fluid pressure past end seals, reducing hoop stresses and increasing the maximum pressure rating of submersible pump housings.

Magnetic fields secure stainless steel shot within strut cavities to reduce vibrational responses without increasing engine weight or complexity.

An integrated annular body absorbs water hammer forces to prevent damage while eliminating bulky external protection systems.

Slot parts and tubes divert working fluid away from gap regions to reduce turbulence and fluid loss near vane walls.

A radial fan uses an axially open bearing tube to dissipate heat via internal air flow.

Segmented distributor platforms slide circumferential abradable mounts, eliminating costly stelliting and enabling independent replacement without dismounting.

Segmented fillets concentrate vibratory stress away from the hub, preventing crack propagation and disc fractures in gas turbine engines.

Simulates operational speeds and stabilizes blade sectors to eliminate run-to-run unbalance variations in gas turbine rotors.

Stationary disk projecting portions maintain exhaust flow continuity between upstream and downstream regions in Siegbahn vacuum pumps.