Pump Components TRIZ Cases

An axial flow blower design channels ambient air into the motor case to cool internal components.

A silencer housing with a sound-absorbing pad contacts diffuser vanes, absorbing acoustic energy from high-velocity fluid flow to minimize harmful noise levels.

Asymmetric gear and spindle features constrain inlet guide vane rotation, preventing backwards installation and costly compressor failures.

A bearing housing uses segmented spray outlets to direct cooling fluid across the inner shell for uniform heat transfer.

A fan lamp mount integrates multiple fan assemblies to deliver combined lighting and ventilation functions in a single compact unit.

A variable guide vane device uses a radially extending slot between fixed and pivotable vanes to re-energize the boundary layer.

Segmented elastomeric stirrups connect upstream and downstream rings, reducing radial spatial requirements while enhancing structural stiffness.

Varying cell lengths and porous walls reduce resonant vibrations without increasing external dimensions.

Segmented casing rings with a low conductivity conduction cut reduce outer ring temperature and match rotor thermal expansion.

Defining inlet guide vane suction and pressure sides via specific coordinate values improves energy levels and pressure ratios.

High friction oxide layers on snap surfaces increase static friction coefficients, reducing wear and stress on rotor components during gas turbine operation.

A tandem rotor disk apparatus merges two blade stages into a single assembly with axially offset blades.

Variable length canopy fins reduce shield mass and inertia without compromising impact energy dissipation on turbine blades.

Mixing bleed air with ram air at the turbine inlet reduces fuel burn by 40% while maintaining cabin pressure through electrical compression.

Bypass air compression raises duct exit pressure above core intake, enabling common engine cores across civil and military configurations.

Integrated pogo pins on the fan frame allow robotic assembly to connect directly to motherboard contacts, eliminating manual wiring steps.

Intermediary vibration insulators stabilize the clamped turbo-cartridge, suppressing resonance to ensure precise measurement accuracy.

A liquid ring vacuum pump adjusts rotational speed based on vibration measurements to manage cavitation conditions.

Three-boss cup damper maintains isostatic contact with chamber walls despite phase displacement, ensuring consistent energy dissipation.

Grouping fans by characteristics establishes reference values that identify deviations beyond tolerance ranges for accurate failure detection.

Closed impeller compressors reduce gas leakage and fouling risk while maintaining compact dimensions.

Stepped engagement portions on axial flow fan casings enable secure coupling through rotational sliding motion.

Segmented insulated wire plasma actuators reduce turbulence and air resistance on curved turbine blades while preventing short circuits.

V-shaped impeller blades reduce noise emissions by preventing sudden gas acceleration against interruption zone walls.

A centrifugal compressor movable member design featuring distinct contacting and non-contacting chamber surfaces to minimize mechanical friction.

A fan rotor uses a compound contoured surface on its upstream arm to direct airflow along blade roots.

A resiliently deformable cylindrical sealing member connects fluid passages between a turbocharger unit and an adjacent auxiliary component.

Quick-fixing devices with resilient tails and bayonet sliding triggers reduce assembly time for submerged pump cable protection.

Axially divided inner ring segments join via fastening elements and securing components to safeguard structural integrity against material overload and leakage.

A turbine compressor control ring adjusts stator vane pitch angles via oblong holes accommodating pin movement.

Liquid-filled balance rings stabilize high-speed fan rotation, reducing noise and vibration during acceleration cycles.

A geared gas turbine engine drives a fan at reduced speed via a speed reduction device, enabling independent optimization of turbine and fan rotational speeds.

Passive flow control passages extend through the nacelle cowl to stabilize airflow and reduce drag.

A movable air-bleed valve directs flow between compressor ducts and bypass channels to manage engine operations.

Staggered guiding and arranging slots prevent wire separation from vibration during assembly.

A propeller fan blade incorporates notches with acute side edges and obtuse bottom protrusions to distribute mechanical stress.

Segmenting the actuator into a unison ring and intermediary flange resolves complexity when positioning radial vanes parallel to the engine center line.

Segmented thrust collars and a mechanical component regulate axial load distribution, preventing uneven wear in constrained wellbores.

Circumferential groove and discharge passage guide lubricant oil downward, preventing centrifugal scattering into exhaust or intake air.

A low-expansion annular element moves radially to reduce the flow passage area by up to 4 percent, eliminating complex hinged mechanisms prone to seizing.

Thermal expansion of the stationary casing reduces tip clearance from 0.010 inches to 0.005 inches, improving efficiency without mechanical complexity.

Optimized inlet duct geometry reduces engine weight and length in geared turbofan applications.

Segmented radial studs reduce contact area to limit heat conduction, preventing circumferential rim overheating while maintaining structural stability.

Three-dimensional weaving creates integral fibrous preforms for composite turbine sectors.

Segmented fairing halves pivot on the pylon distal edge to resolve time-consuming equipment access without adding structural complexity.

Centrifugal compressor bleed channels direct cooling air to turbine components via angled metering holes.

A multistage compressor tie rod channels hot gas along its length to reduce startup temperature gradients and thermal stress.

Staggered guide vanes reduce aerodynamic losses in the backfeed stage, resolving space constraints and flow inefficiency.

Side-mounted actuation levers resolve geometric constraints from small vane shanks by enabling secure radial locking in compact compressor spaces.

Reinforcing plates distribute thermal mismatch-induced strain by attaching to the outer shroud skin at vane joining locations.