Pump Components TRIZ Cases

Varying the inlet edge angle along blade height reduces pressure loss by minimizing vortex formation in radial turbomachines.

Segmented compression bulkheads counteract down thrust and thermal fatigue in multistage centrifugal pumps, preventing diffuser rotation.

Circumferential bolts fix the thrust collar and pinion gear, distributing reaction forces to prevent axial misalignment without shrink fitting.

Retractable barriers in a rotary engine isolate combustion from intake, eliminating compression energy costs.

Segmented gear casing decouples drive and impeller housings, eliminating complex multi-side machining.

A width changing mechanism adjusts throat passage width along the circumferential direction of a turbine impeller to control exhaust gas flow.

Self-excited sound generation structures synchronize with control sound to reduce jet fan noise without increasing speaker weight or installation space.

Fan blades feature physical nonuniformities to generate decay-resistant harmonics for gas turbine engines.

A multi-part housing design uses a single sealing element to separate liquid and electronics chambers in an electric motor driven pump.

A compressor rotor blade design with optimized local maximum thickness distribution along the span.

A mold assembly uses a lattice structure to position a core for forming components with internal passages.

Variable hub and shroud stagger angles in a leaned airfoil diffuser suppress secondary flows and delay stall to extend compressor operating range.

Curved fan struts align with wing elements to minimize turbulence, reducing noise while maintaining structural rigidity.

A hydraulic locking valve isolates the actuator from control valve leakage, stopping continuous micro-movements that cause guide vane bearing wear.

A compressor housing uses a sacrificial impeller cover to fragment on impact and absorb energy during failure conditions.

A turbocharger sealing structure uses segmented rotating bodies to form an annular groove for the sealing ring.

Volume expanding portions in the fan labyrinth increase clearance volume, improving waterproof performance without requiring tight assembly accuracy.

Segmenting the bellcrank into four branches reduces mass while maintaining strength under aerodynamic stresses.

Spirally widening curved outlet channels eliminate settling points for long fibers, preventing clogging while maintaining smooth flow distribution.

Segmented restrictor plates with varying apertures dissipate acoustical energy to minimize high cycle fatigue in compressor discharge lines.

Segmented perforations in the stator vane liner concentrate cooling jets at edges, reducing radial stresses and temperature gradients.

Distinct blade thickness distributions separate natural vibration frequencies to prevent resonant response and reduce stress loads in gas turbine engines.

A control device monitors pump characteristic variables to detect rotor stator jamming and automatically switches the drive motor on and off in alternating directions.

Single dispensing head adjusts sugar concentration and carbonation pressure via software control, eliminating separate flavor chips.

Sliding perforated outer ring aligns with fixed inner ring to eliminate dead zones and reduce pressure losses during gas bleeding operations.

Fusible safety element breaks to rotationally disengage fan wheel, eliminating complex shear shafts and reducing weight.

A single unducted rotor engine uses a controller to adjust blade and vane pitch angles for thrust vectoring.

Sloped NACA submerged inlet redirects compressor bleed air flow to reduce flow separation and recover pressure loss in gas turbine engines.

Secondary struts in a fan grille suppress vortices generated by primary radial supports, reducing operating noise while maintaining static efficiency.

Digital fan imaging detects blade deformation and foreign object ingestion during aircraft turbine missions.

A contoured fan base plate directs airflow at an acute angle to enhance attachment over a motor housing.

A drain pump seal component presses against a housing and cover in axial and radial directions to maintain structural integrity.

Radial grooves on the rotor cylinder hold adhesive that bonds the impeller cup, strengthening fixation while reducing fan thickness.

Cartesian coordinate tables define scalable airfoil profiles that enhance compressor efficiency while reducing vibratory stress.

Hydrophobic and hydrophilic surface layers on compressor components manage liquid phases in wet gas streams.

A variable capacity turbine inlet flow path accelerates exhaust gas through a continuous throttle geometry.

Segmented primary and secondary blades increase air outlet area, resolving vibration and noise issues caused by larger diameters.

Segmented seal portions and dual bearing structures prevent fluid leakage through high-pressure clearances in centrifugal compressors.

Ribs redistribute stress at cuff bases to extend casing lifespan from 6000 to 50000 cycles.

Transverse flow splitting via separating elements in the stabilizer channel resolves the surge limit versus map width trade-off.

Press fit members couple vane arms to actuation rings, distributing rotational loads across larger bearing surfaces.

Branching structures eliminate central platforms to reduce flow disturbances while maintaining blade strength through distributed load paths.

Inter-blade apertures on the rotor back wall allow precise material removal without compromising structural strength.

A motorized insect repellent device couples to a standard bottle via a tapered stem, eliminating the need for dedicated table space.

Grooved abradable segment minimizes blade tip clearance and aerodynamic losses while reducing stress from rubbing loads.

Ejection ports on the vane platform channel coolant to impinge exposed surfaces, reducing thermal distress and parasitic losses.

A magnetic coupler securely seats a centrifugal fan damper against the backplate to prevent slippage during low-speed operation.

A pump inlet bonnet defines a flow path between its internal surface and an extension tube to combine fluid streams before entering the volute.

Circumferential offset between connection piece and vane root simplifies assembly in congested hub.

Axial and centrifugal impeller sections drive coolant at high speed to resolve limited heat exchange area in constrained computer spaces.