Pump Components TRIZ Cases

Permeable chamber separation elements in a vehicle heater blower absorb and reflect noise, reducing device complexity by eliminating external sound absorbers.

Perforations in the turbine casing create uniform ventilation, reducing thermal deformation and mechanical stress on the support ring.

A friction-based damping element positioned at the blade platform perimeter dampens vibrations in variable pitch open fan rotors.

Capacitor-start motor design generates high starting torque for axial flow fans without requiring high voltage or current inputs.

Segmented louvers automatically close upon fan failure to block recirculation, maintaining linear airflow across components.

An abradable coating on a stator seal accommodates axial expansion during transients while maintaining tight clearance to prevent rotor lock-ups.

Ammonia nitriding strengthens vane pump casings to reduce wear and prevent fluid contamination.

A compact automotive electric liquid pump uses a radial slide bearing within the motor rotor to reduce axial length and friction.

A pressurized cooling fan uses coaxial inner and outer blades to increase static pressure while reducing power consumption.

Conical expansion structure compensates for rotor thermal growth, preventing mechanical shocks from unstable magnetic bearing preload.

An iron-containing bushing structure with an extension portion bonds to a plastic fan frame via injection molding.

Roughed ceramic shroud surface removes material imperfections during rub events, preventing thermal buildup and improving sealing effectiveness.

Arranging rotor blades by critical mode stiffness minimizes vibration mismatch and reduces stress concentrations.

Metal heat dissipation plate conducts thermal energy from the electronic control board to the pump housing via silicone grease.

Part-span inlet guide vanes pre-swirl airflow upstream of fan blades, reducing shock losses and flow separation that occur at high rotational speeds.

Air collecting component redirects impeller airflow through a widened gap to bypass blocked outlets, maintaining cooling efficiency in thin laptops.

Resin intermediary cushions ball bearings to eliminate sliding noise while a safety switch detects bolt wear to prevent loose connections.

Segmented bearing cup sections prevent glue flow into the shaft hole and avoid shaft compression during assembly.

An inner rotor uses circumferentially expandable projections to mesh with an annular housing and create variable volume chambers.

Strategic cooling entrance placement directs fluid to hot spots, reducing thermal stress on gas turbine components.

Preformed prepreg panels secure to composite surfaces via thermal treatment, creating a self-extinguishing protective layer.

Compliant seals and a spring mechanism maintain seal contact in gas turbine duct blocker assemblies.

A waterproof fluid pump transfers torque via magnetic coupling between separated rotor and impeller assemblies.

An angled socket and notch in the hanger bracket prevent down rod contact, eliminating rubbing noise on sloped ceilings.

Self-rotating cylindrical vanes eliminate vane interference noise while directing airflow to improve heat dissipation efficiency.

Lateral air inlets and outlets enable radial heat dissipation, resolving axial-flow turbulence and blower-type limitations.

Varying the guide vane inlet edge angle along the blade height resolves pressure loss inconsistencies by matching local flow incidence angles.

Inward actuation with an axial cam ring prevents roller binding to reduce engine profile and complexity.

Curved cooling passages distribute medium across turbine platforms, reducing thermal stress and manufacturing costs compared to complex cored structures.

Flexible U-shaped connection blocks deform elastically to release cover plates, resolving the trade-off between secure engagement and dismantling convenience.

An integrally formed partition plate isolates the heat-generating electrical control unit from the motor compartment, reducing assembly complexity.

A single motor drives a fan for airflow or an eccentric mass for haptic feedback via directional rotation.

Interlocking protrusions and recesses merge the fastening function into the frame structure, eliminating multiple screws that weaken structural integrity.

Offsetting intersegment gaps relative to the longitudinal axis reduces hot gas ingestion and cooling air consumption.

Segmented frames and detachable blades minimize storage space while maintaining integrated lighting and airflow functions.

Mixed-flow contra-rotating fans reduce back pressure resistance and energy loss by changing flow parameters.

Vortex generators disrupt boundary layers in confined internal cavities, improving heat transfer efficiency where traditional pin-fin banks fail.

A turbojet fan blade with a leading edge sweep angle of at least 28 degrees between 60 and 90 percent radial height.

An abrasive tip uses a eutectic aluminum-silicon matrix to dissipate frictional heat, preventing delamination of the polymeric overcoat from seal rubbing.

A rounded inlet aperture delays fluid separation to enhance acoustic energy dissipation in engine resonators.

Radial preload on elastomeric damper creates frictional resistance, solving installation complexity and insufficient damping of prior art.

Composite housing sections combine rigid containment with deformable energy absorbing materials to reduce manufacturing complexity while maintaining safety.

Bleed ports in a turbine exhaust case duct reduce thermal gradients, preventing fatigue cracking in thin metal components under rapid cycling.

A turbine thrust load adjusting mechanism controls contact pressure via a balance piston chamber to stabilize bearing loads.

Asymmetric upper and lower air inlets match airflow to the opening degree, resolving insufficient diffusion and high-frequency noise in centrifugal fans.

A magnetic bearing controller adjusts coil current middle values to reduce power consumption.

An inducer sleeve extracts recirculating fluid into a secondary cavity, reducing velocity and preventing cavitation in spacecraft turbopumps.

Varying shim thicknesses maintain concentric alignment between gas turbine case and synchronizing rings, eliminating ring distortion from adjustable bumpers.