Pump Components TRIZ Cases

A resin or rubber sliding member containing 10 to 30 percent metal powder enables rapid wear detection in eccentric screw pumps.

Feedback control modifies inlet guide vane angles to prevent high-pressure compressor runaway during acceleration.

Hydraulic pistons shift axially to distribute thrust evenly across bearing pads, preventing pad overload and deterioration in gas turbines.

Modifying inner shroud thickness ratios tunes airfoil natural frequencies, reducing structural distress in gas turbine engines.

An auxiliary bearing supports the vane rotation, reducing wear and minimizing relative speed between the vane and stationary components.

A segmented cooling passage channels liquid coolant to absorb heat from a compressor impeller back surface.

Spherical bearings mediate actuator rod rotation in swashplate systems, preventing clevis damage and extending component lifespan.

A segmented liner assembly uses an impact resistant layer and interior layer to reinforce a gas turbine engine fan case.

Composite micro-actuators switch magnetization direction to enable remote addressable control in enclosed spaces.

Low-conductivity spacers maintain elevated temperatures to inhibit product deposition without external heating components.

Reducing the splitter blade height ratio below unity blocks leakage interference and achieves uniform flow distribution, enhancing impeller efficiency.

Segmented command modules with universal rotors resolve adaptability versus complexity trade-offs in vehicle cooling systems.

Ball-joint and sliding pivot connections in a turbo-machine vane control ring distribute forces uniformly, reducing mechanical stress and preventing jamming.

Segmented fan rotor with curved cooling plate directs airflow to reduce temperature rise in motor components.

A shell protrusion redirects impeller wake flow to lower blade frequency noise while maintaining air convection for heat dissipation.

Gear reduction mechanisms separate fan speed from turbine speed, resolving compressibility limits while maintaining high efficiency.

Independent gear assemblies rotate tip and hub segments of a variable fan outlet guide vane to match distorted fan exit air and reduce incidence.

Active control feedback system adjusts variable inlet guide vanes based on pressure readings to correct distorted airflow and maintain engine stability.

Curved support bracket isolates thermal loads on impeller shrouds, preventing deflections that compromise pressurization efficiency.

A diffuser channels compressor discharge air through a turbine nozzle segment cavity to cool airfoil vanes via internal turbulators.

Axial blade tip overlap with the impeller cap reduces cantilever length, raising natural frequency and suppressing self-excited vibration.

A fan housing with a moveable member positions fans near heat-producing components, eliminating hinged baffle wear and reducing manufacturing costs.

A turbine rotor blade profiling method adjusts the mean camber line to maximize isentropic Mach number differences between pressure and suction sides.

Segmented rotor blade platform uses nested damper pins and slots to enhance vibration damping while housing seals within the same spatial envelope.

Varying circumferential edge spacing between adjacent blade rows reduces boundary layer separation at hub and housing side walls.

Segmented trailing ribs and cut-back blocks enhance heat transfer while retarding crack growth at the blade trailing edge.

Selective aero-dampers mistune diffuser pipe frequencies, preventing synchronized vibration amplification and reducing structural stress in gas turbine engines.

High thermal conductivity webs in a turbine liner conduct heat from the first wall to cooling channels, reducing plate temperature and pressure fall.

A compressor blade airfoil design with a distinct tip portion generates higher meridional velocity and total pressure at the tip than at midspan.

Replacing screw-based fixation, an elastic clamping mechanism enables rapid fan installation while preventing component loss and reducing assembly labor.

A resin-fabric covering shields a turbojet shaft from friction and heat when a fusible bearing fails, preventing rupture.

Segmented cutoff modules replace fixed geometries to reduce acoustic noise while maintaining manufacturing simplicity.

A concave rotor surface and through hole reduce blood damage and air bubble formation by minimizing impact and stagnation zones.

Molded clamshell blower housing with radial draft maintains uniform axial gap between impeller backplate and scroll wall.

Integrated bowed rotor management systems maintain minimal compressor build clearances by controlling pre-start rotation to prevent thermal expansion damage.

A turbocharger compressor injection device positioned outside the flow channel directs air into the conical diffuser to enhance swirl and reduce pressure.

A computer fan integrates a hollow wire-passing shaft with an LCD screen to organize internal cabling and simplify assembly.

A fan circuit board adjusts motor power output through a stepless adjusting member for continuous wind speed regulation.

Asymmetric fixing slots in a fan module frame prevent component misplacement, maintaining thermal dissipation efficiency and preventing overheating.

Centrifugal stiffening rigidifies flexible blade tips to cut a case groove, reducing air leakage and preventing rub damage.

Independent ferrules attached to the shell prevent axial force transmission, reducing mechanical stress concentration and weight in turbine engine compressors.

A composite compressor housing uses layered fiber reinforcement to enhance mechanical strength, resisting rotor blade contact damage under high stress.

Radial bores in a separate chamber behind the impeller mix air with liquid to resolve flow breaks caused by air pockets.

Segmented dual inlet ducts with specific spacing ratios minimize moisture condensation collection during varied aircraft orientations.

Elongated intake channel grooves dissipate partial load vortex energy through friction, reducing NPSH instability without affecting peak efficiency.

Angled profile portions create a pressure gradient that increases pumping capacity while reducing energy dissipation zones in metallurgical applications.

Unidirectional rolling bearings eliminate gear coupling to reduce vibration and extend lifespan in the rotary engine.

Segmenting the airfoil into fixed and rotatable portions with dual thrust surfaces resolves adaptability versus complexity trade-offs.

Asymmetric bearing surfaces minimize sub-synchronous frequency vibrations by reducing outer axial dimensions, eliminating noise in rotating machinery.

Segmented bushings redistribute loads to the fillet radius, reducing thickness from 0.07 inches to 0.05 inches and avoiding galvanic corrosion scrapping.