Pump Components TRIZ Cases

Segmented casing and integral impeller reduce discrete frequency noise and wideband turbulence while maintaining high productivity.

An adjustable expansion chamber wall in a vane heat engine changes compartment volume to match ambient exhaust pressure, resolving fixed-volume inefficiencies.

Nested retaining members secure a fan hub to a motor shaft, preventing blade detachment when the shaft breaks.

Controller monitors current or speed changes to stop the DC motor when a fan blade breaks, preventing continued rotation hazards.

Segmented stator inserts with solidified reinforcing material enable quick field replacement of worn downhole motor parts.

A turbo-molecular pump uses segmented cooling and heating zones to manage rotor and stator temperatures.

Segmented stators and labyrinth seals resolve the complexity-reliability trade-off in downhole blowers, extending gas flow duration.

A bearing design constrains axial play through thrust washer and collar thickness dimensions.

Integrated scroll casing reduces device volume while maintaining cooling effectiveness for densely packed battery cells.

A turbine vane integrates an internal duct connecting suction openings near the leading edge to exhaust slots at the trailing edge.

A centrifugal compressor integrates a backflow air cooling system with flexible integral top-layer foils for thrust bearings.

A propeller fan blade features a ring at the tip and variable axial height to enhance workload.

Offset holding devices tilt a fan downward onto a top-hat rail, eliminating upward space requirements and preserving full device height.

A cooling jacket with an internal flow guide directs coolant around the pump housing to prevent urea precipitation and maintain NOx reduction efficiency.

Multi-air stream cooling system divides airflow into independent paths to maintain lower temperatures near the combustor chamber, preventing overheating.

Constant thickness non-airfoil vanes reduce surge and choked flow losses while maintaining high efficiency in centrifugal compressors.

Composite fan blades with variable thickness profiles attach to a dual-plate center hub assembly.

A turbine airfoil trailing edge structure uses linear and curved portions to control fluid acceleration.

A pump housing uses pressurizing means to equalize pressure between interior and exterior chambers, reducing stress on the circumferential wall.

A centrifugal compressor shroud features a reinforced region at the structural member intersection to enhance local stiffness.

Segmented reinforcing ribs on the rotor blade groove distribute stress to prevent bottom cracking while enabling surface crack detection for easier repair.

A fiber reinforced composite spacer for gas turbine engines provides enhanced structural strength and thermal resistance.

Segmented wall segments on a metal fan base resist wrapping force from insert molding, preventing base deformation that disrupts blade clearance and balance.

An interrupter limits reverse airflow in a compact regenerative blower, reducing noise for respiratory devices.

Porous plate divides fan casing into airflow and noise rooms, dispersing air to reduce wind shear without complex mechanical adjustments.

Quick-change blade holders allow repositioning on the motor shaft to maintain airflow direction, eliminating manual adjustment time and spare parts costs.

An integrated cooling system cools the motor and oil via heat exchange, reducing housing volume and complexity.

Variable blade thickness directs bending stress to high-rigidity regions while preserving compression performance in low-rigidity areas.

Adjusting stage radii reduces compressor flow rate without dropping the compression ratio, enabling component reuse for humid air turbines.

Merging the silencer with the fan housing eliminates separate installation space while maintaining effective noise dampening for industrial environments.

Bonding segmented metal sheets yields high rigidity and airflow efficiency while eliminating welding bead friction losses.

Composite titanium compressor case with high heat capacity liner and diffusion barrier reduces fire risk while maintaining low weight.

Root through holes connect to internal cavities, reducing weight while preventing condensation migration and mitigating stress concentration.

A gas turbine compressor control system adjusts air extraction valves and inlet guide vanes to manage airflow dynamics.

A nested eccentric pin and push rod adjust the lower-half inside member without increasing the outside cylinder outer diameter.

Segmented cooling channels distribute coolant across the turbine rotor blade platform region.

Thermal coupling between the second exhaust duct and stator prevents product deposition without additional heating components.

A vane arm claw press-fits onto a turbine stem to secure radial attachment and maintain precise orientation.

An asymmetric suction surface protrusion on the fan blade suppresses locally-high velocity air streams by uniformizing radial blowing flow.

Segmented impeller blades reduce noise while maintaining air pressure by optimizing airflow at lower rotation speeds.

Disk-shaped axial field motor drives a side channel compressor wheel, enabling rapid preheating to prevent ice bridge formation during cold starts.

A rear mounting structure uses a six-rod link device to transfer inertia-induced loads from the core portion to the bypass duct wall.

Rotating assemblies on enamel-coated pipes remove dust via flue gas flow, preventing blockages and maintaining heat exchange efficiency.

A vortex fluid separator and porous filter system cleans reservoir oil before it reaches journal bearings, preventing abrasive sand wear on motor components.

Rotor cut-out portions intersect vane grooves to facilitate compressed air flow and pressure increase for outward vane displacement.

Segmented chambers and a pumping device lower motor pressure, reducing windage losses while maintaining cooling effectiveness.

Segmented ceramic coating resists heat transfer while reducing internal stresses, eliminating compressor bleed cooling.

An internal epicyclic gear reducer adjusts variable pitch blades inside the rotor shaft, reducing radial bulk and hub ratio for propulsion assemblies.