Propellers TRIZ Cases

Circumferential slots and reinforcing ribs segment the outer rim to relieve thermal fatigue stresses while maintaining structural integrity.

An integrated interlock mechanism prevents radial separation during primary failure while eliminating vibration, wear, and skilled assembly requirements.

A propeller blade projects a Fibonacci spiral onto a square hyperbola surface to guide fluid flow evenly along the span.

Spherical cap composite arms distribute bending stresses in propeller pivots, reducing moving object weight by up to 50% compared to metal designs.

Axial pins through radial lugs secure inter-blade platforms, eliminating bulky nut-and-bolt tools in small-diameter turbomachine engines.

Tension elements within variable pitch blades maintain constant lateral force to increase structural stiffness, reducing noise from aerodynamic deformations.

Phase generator module adjusts relative propulsor azimuthal positions to minimize spatially-averaged sound pressure levels over designated low-noise zones.

Recessed blade tip geometry redistributes high cyclic stresses to prevent cracks during tip rubs, maintaining power output without compromising reliability.

Golden ratio aperiodic micropillar arrays disrupt turbulence and diffuse sound waves, achieving 2-4 dB noise reduction for urban air mobility vehicles.

Adjusting inlet and outlet blade angles to less than 80 degrees reduces noise levels without sacrificing air volume in air-cooled engines.

Unison ring gears synchronize remote counterweights to prevent phase misalignment during pitch adjustments, resolving reliability trade-offs.

A propeller blade tip slot connects pressure and suction sides to generate counter-vortices that mitigate energy losses.

A composite fan blade integrates an internal fluid passageway extending from root to tip.

A U-shaped flex beam with a tall cross section increases rotor assembly stiffness along the central axis.

A welded intermediate component bridges incompatible materials, resolving thermal stress while maintaining structural integrity.

Pre-tensioned strings within composite fan blades restrain fragmentation upon brittle failure, preventing engine damage from loose debris.

An LVDT sensor detects propeller feedback ring axial position via mechanical linkage.

Integrated extraction holes in fastening means allow axial dome removal, eliminating protruding inserts that cause aerodynamic losses.

Dual pivot points on a folding yoke allow rotor blades to fold inboard of the outboard bearing, reducing aircraft volume without increasing pivot distance.

Increasing spinner aspect ratio beyond 1.8 reduces inlet flow separation during crosswinds, maintaining cruise performance without adding complexity.

Replacing mechanical cables with one actuator reduces weight while enabling electronic control of variable-pitch blades.

Orthogonal centrifugal fan driven by rotary engine eliminates propeller drag, noise, and icing risks.

Varying adhesive bondline thickness compensates for component tolerance stackups, maintaining consistent tip-gap uniformity in ducted-rotor aircraft.

A ratiometric sensor system calculates clearance between turbine components using dual signals.

A propeller control system inserts movable blades into a fixed hub to reduce overall size.

A rotor yoke hub assembly uses a cylindrical elastomeric clamp to transmit torque without drilling apertures through the composite structure.

Asymmetrical stator arrangement minimizes rotor-wake interaction noise by optimizing separation distances between rotor blades and stators.

A slider mechanism translates the lower skin relative to the spar, enabling controlled twist of the rotor blade airfoil shape.

Segmented annular flanges pivot radially outward via centrifugal force to lock metal matrix composite rings, eliminating complex drilling operations.

Removable airfoil tip segment reduces rotational mass, avoiding full blisk replacement costs.

Spiral vortex propeller blades optimize fluid flow and angle of attack, resolving aerodynamic drag and structural strength trade-offs in wind turbines.

Segmented flow guides with radial slots increase heat transfer surface area, reducing rotor-stator temperature disparity and preventing seizing.

Triangulated ducted fans enable high-speed cruise by separating lift from thrust, reducing fuel consumption compared to compound helicopters.

Integrated radial legs and feather seals minimize leakage between adjacent segments while maintaining effective platform cooling to reduce hot spots.

Segmented mounting plates enable secure attachment of turbine rotor blades to a triangular hub structure, simplifying maintenance operations.

Replacing internal combustion with electric drive reduces noise generation while maintaining power output through tooth coil windings.

A helicopter rotor blade uses torsion resonance to generate dynamic twist for cyclic pitch control without a mechanical cyclic plate.

A radial turbine wheel integrates a hub sub-path to merge fluid streams into rotational motive force.

Folding turbine blades and hinges allow mooring to the tower, reducing structural loads on the hub and bearings while enabling lighter component designs.

Composite return flange with internal geometric support enhances structural stiffness and foreign object resistance.

Rotatable linear actuator and transmission mechanism reconfigure blade pitch control for coaxial propellers.

Segmented blade pitch control resolves lateral maneuvering limits in fixed designs, enabling six-degree-of-freedom motion at low speeds.

Clocking shafts via a planetary mechanism folds blades for compact storage while maintaining continuous drive connectivity to eliminate manual removal errors.

Biasing means preload dovetail root crush faces against slot faces, resolving the weight versus robustness trade-off in composite vane mounting.

Individually controlled ailerons and tilting rotors reduce wind impact on hybrid drones, enabling stable flight in high-speed crosswinds.

An eight-rotor mediator accelerates fixed-wing aircraft to takeoff speed, eliminating long runway requirements.

Direct mounting of the actuator on the control ring eliminates intermediate rods, reducing assembly complexity and deformation errors in gas turbine engines.

A controller manages gas generator output using a single throttle lever input and coefficient reference table.

Mechanical interlocking replaces thermal welding, reducing production costs and improving thermal dissipation efficiency.

A beta tube assembly translates hydraulic pressure into axial motion to rotate propeller blades.