Pump Components TRIZ Cases

A nested compressor architecture positions one centrifugal wheel radially within another to share a common longitudinal axis.

Differential radial heights on the rotor base resolve conflicts between reliable coating mask support and axial contact prevention during compressor surge.

A slot-free cylindrical stator winding arrangement on a laminated core enhances magnetic flux density and packing density in brushless DC motors.

Asymmetric fin geometry prevents detachment on composite blades by avoiding fiber alignment and dissipating impact energy.

Consolidating pump mounting structures on the flow housing part reduces interface complexity and manufacturing effort across vehicle models.

A seal assembly with radial and axial components minimizes core airflow leakage in tip turbine engines.

A steel wire mesh cap covers composite fan blade tips to provide structural reinforcement and efficient heat dissipation.

A thermal fuse in a vortex-flow blower housing melts to open the discharge port and release pressure.

Merging guide claws with the base ring eliminates separate guide components, reducing manufacturing costs while stabilizing drive ring rotation.

An open compartment spaces the motor casing from the impeller body, using hydraulic sealing means to prevent liquid leakage and reduce vibration.

Boundary layer ingestion fan reduces aircraft drag by reenergizing airflow, while mixing vanes uniformize velocity profiles to maintain engine efficiency.

Specific arc radius relationships minimize slippage loss, enabling size reduction while maintaining discharging capability.

A blower housing motor cover embeds a strip conductor formation to link internal and external electrical contact areas for the electric motor.

Segmented shroud slots dissipate motor cogging torque, reducing noise and vibration without increasing weight or manufacturing cost.

Replacing gear pumps with progressing cavity pumps eliminates abrasive wear while maintaining high pressure delivery accuracy.

Cavities and notches in variable diffuser vanes create stabilizing loads that prevent dithering, vibration, and resonance under unstable airflow conditions.

Permeable casing creates inner cells decoupling resonance frequencies to reduce noise without enlarging silencer volume.

Adjustable guide vanes in a vehicle duct direct airflow to drive a turbo impeller, recovering energy at high speeds and reducing pressure drag at low speeds.

Circumferential cooling passages around grease-sealed bearings manage thermal loads in high-pressure stage supercharging systems.

Segmented hub geometry absorbs centrifugal tensile stresses at blade transitions, reducing weight while preventing damage to the compressor housing.

Segmented radial blade areas in a rotating component reduce pressure losses and minimize power dissipation during hydraulic fluid transfer.

Merging the air inlet duct and electronic card housing into a single casing eliminates inter-card connections, reducing parasitic radiation and volume.

Inclined passage disrupts resonance and reduces periodic noise in series fan assemblies.

Diverging cooling holes in turbine nozzle vanes direct air toward inner and outer bands, reducing radial temperature profiles near shrouds.

An uncoupling fuse element between the reduction device and turbine shaft limits torsional torque to prevent shaft breakage during fan blade loss.

Spring-mounted blade outer air seal mounts counteract thermal growth interference and unequal pressure loads to maintain optimal clearance.

Jamming device actuates turbine components by evacuating fluid from a bladder to apply compressive force.

Curved supporting legs position the shaft body toward the inlet, reducing turbulence and improving suction characteristics.

A temperature control unit adjusts cooling fan rotation speeds based on measured device temperatures.

Integrated gas-liquid extraction units and ejectors produce liquid-rich fluid for bearing lubrication, resolving complexity in compact subsea designs.

Spiral grooves convert linear motion from an actuator into precise blade rotation, resolving complexity issues in centrifugal compressor flow control.

A vacuum pump rotor assembly uses a low shear strength filling member to join the shaft and rotor without thermal processing.

Guiding grooves on the thrust member create a pressurized oil layer that reduces deflection and vibration during high-speed rotation.

Merges impeller and bearing functions using air lubrication to resolve installation space constraints in fuel cell systems.

Integrated magnetic shaft support eliminates complex bearings to lower manufacturing costs and reduce vibration in water pumps.

Orifices in turbine casing arms reduce vortex amplification and preserve engine efficiency.

A pump assembly uses a heat-conductive cap inner layer to cool electronic components while maintaining electrical insulation.

Mismatched C-clip curvatures accommodate thermal expansion, reducing bending stress on shroud mounting flanges during hot operation.

Varying surface fluence by thickness minimizes delamination in thin gas turbine airfoils while maintaining compressive residual stresses.

A thrust bearing device uses deformable pillows to support sliding blocks and maintain fluid film formation between rotor surfaces.

Piezoelectric heating circuits generate heat via electromagnetic induction to prevent ice accretion and reduce rotor imbalance.

Axial flow water pump assembly with laminar flow box eliminates turbulence and cavitation to increase water velocity.

Segmenting the seal spacer into elastomeric and plastomeric portions prevents retention system relaxation caused by grommet deformation under structural loads.

Asymmetric piston geometry creates six variable-volume chambers in a three-piston rotary machine, resolving unused central volume and low power-to-size ratios.

Composite blade leading edge with variable-density metal zones reduces centrifugal stress while maintaining impact resistance.

Biasing element centers and clamps inner ring halves to prevent air leaks and reduce wear in gas turbine compressors.

Smaller first diffuser radius and larger second radius reduce recirculation losses near the tongue while maintaining downstream flow area.

A temperature-resistant plastic bearing housing cover thermally decouples the compressor diffuser from turbine heat sources.