Pump Components TRIZ Cases

Mechanical strut attachment protects perforated acoustic panels from welding contamination, ensuring reliable sound attenuation.

Segmented porous plates form acoustic filters in a compressor discharge pipe, increasing noise reduction efficiency without extending the installation length.

A circumferentially extending groove in the fan casing creates a tuned cavity to suppress upstream pressure waves.

Axial connector engages rotor blades and annulus fillers using dovetail slots to secure components on the turbine wheel.

A single-piece annular acoustic insulation panel mounts inside a turbine engine casing wall using sliding and centering mechanisms for accurate positioning.

A fan motor housing uses a groove and cut portion to route lead wires through the structure.

Increasing vane count relative to blades completes combustion upstream, eliminating temperature non-uniformities that compromise turbine durability.

Integrating the internal hot gas bypass device with the inlet guide vane assembly reduces piping complexity while preventing compressor surging at low loads.

Decouples nozzle airfoils from flow path boundaries using caps and attachment members, reducing stress concentrations on ceramic matrix composite materials.

Varying exhaust port cross-sectional area and width along the spanwise direction to distribute reheat flow uniformly across the turbine.

Simulation-driven laser deposition adds mass to specific rotor zones, reducing tensile loads and extending component life.

Segmented airfoil substrates with discrete frangible volumes mitigate load transfer and reduce weight during rotor unbalance events.

Segmented fan blades rotate coaxially with the generator rotor to cool stator coils, avoiding complex flywheel designs.

Articulating seal components track an eccentrically rotating ring piston to maintain continuous surface seals under high pressure.

An angled shroud support in the recirculation cavity reduces turbulence and blade-pass noise while maintaining air compression performance.

Segmenting the blade array into integral and mechanical types resolves mistuning and machining contradictions in gas turbine engines.

A ceiling fan blade iron uses a snap-fit connector to secure blades through elastic deformation.

Segmented wear liner segments eliminate tolerance stacking to ease vane installation while minimizing leak paths.

A fifth stage compressor stator vane airfoil profile uses specific Cartesian coordinate values to define its suction and pressure sides.

A seat ventilation blower integrates the motor assembly and control circuit board into a single housing unit.

Rotating inlet flange redirects backflow air through the radial gap, reducing recirculation and audible noise in electronic device cooling systems.

An elliptical skeleton line shapes a radial compressor guide vane to distribute deceleration uniformly along the flow path.

A vacuum pump stator column uses a pressure-difference relaxing mechanism to ensure uniform gas flow through varying channel cross-sections.

Deflector and liquid trap walls create a meandering path in the blower air channel to prevent water ingress into the motor and electronic circuit.

A compressor diffuser and shroud uses a temporary cylindrical alignment tool to orient the rotor during assembly.

Segmented impeller blades connect to structural ribs, resolving the trade-off between miniaturization and blade stability during rotation.

A composite boss uses a metal injection molded part and sheet metal flange to create a secure mounting interface.

A split air bearing assembly supplies pressurized air to support a turbocharger shaft.

An integrated fluid pump assembly uses an electric motor to rotate an impeller and accelerate coolant through a selective valve switch.

An extraction opening in the fan case directs air to remove dust from heat dissipating components, avoiding added weight and complexity.

Controlled recirculation through rotating drums minimizes negative effects of pressure gradients and swirl, improving gas turbine engine stall margin.

Centrifugal fan impeller applies unequal air outlet intervals between blades to disrupt wake-tongue interactions and lower single tone noise.

A centrifugal compressor impeller uses a fillet to connect the airfoil trailing edge and hub back plate.

Crossed radial and tangential ribs on a mounting flange increase bending stiffness while minimizing material usage in plastic gas blower housings.

A contoured circumferential surface with a depressed upstream section reduces secondary and cooling air flow losses while maintaining manufacturing simplicity.

Labyrinth seals balance upthrust forces in downhole electrical submersible pumps to maintain impeller stability.

Curtain air flows protect pyrometry windows from hydrocarbon contamination, preserving measurement precision without adding complex separate air sources.

A thin pump structure uses magnetic levitation to suspend the rotor assembly within the chamber.

A tuned shroud structure resolves the trade-off between broadband noise attenuation and manufacturing complexity by integrating specialized acoustic treatments.

A rotor assembly mounts a fan wheel shaft inside a single-piece cylindrical separating can within the bearing tube.

Radial supports transfer creep forces to stationary components, resolving the trade-off between reliability and axial length.

Internal ovoid pathways in the axial compressor rotor direct bleed air to cool rims, eliminating secondary heat exchangers that disrupt aerodynamics.

Strategic shroud openings modify local resonance to reduce oscillations and noise emissions during high-power cooling operations.

Angled flow passages in the rotating vane seal minimize windage losses by routing cooling air through a continuous path, preventing dynamic energy dissipation.

Centrifugal force extends biaxial curvature fan blades for operation and springs retract them into a compact housing.

Rotating ducted fans reduce noise and drag while enabling seamless transitions between vertical takeoff and forward flight modes.

Fluid-activated retractable axial retainers prevent fan ejection in gas turbine engines by extending only during emergency retention events.

Asymmetric passages guide gas from the first-stage volute to the second-stage inlet, reducing swirl and thermal energy transfer between stages.

Recesses on cross-flow fan blades create secondary vortices that reduce nZ sound while maintaining air blow capability and power efficiency.