Propellers TRIZ Cases

Pivoting vanes capture wind from any direction without yawing the entire structure, eliminating directional constraints.

Segmented diffuser trailing edges arc into discharge ducts to minimize abrupt area changes and reduce fluid separation losses.

Elastic buckling arms detach hooks from limit portions to enable tool-free maintenance without replacing the entire UAV.

Aerofoils with serrated edges featuring ogee-like tooth profiles concentrate sharpness at tip and root points to reduce acoustic disturbance.

A locking finger mechanism secures an electric motor shaft assembly to limit rotational movement and minimize induced forces.

A conductive nickel alloy band on the propeller blade leading edge channels electrical current into the airframe.

Segmented strain sensors calculate steady bending moments to accurately detect blade damage while reducing unnecessary maintenance checks.

A dual-function Ln-Al-Fe-O coating merges thermal insulation with radio frequency absorption into a single layer.

A compressor blade undercut redirects load paths away from critical stress areas, reducing vibratory stresses and extending component lifespan.

Extending blades axially beyond the hub and rounding connection portions reduces air flow disturbance to lower noise while maintaining high static pressure.

Anti-phase wave engine operation reduces noise and vibration while maintaining thrust in a hybrid aircraft propulsion system.

Helical blade trajectories resolve the trade-off between high-efficiency lift and low-speed drag operation in horizontal axis turbines.

A frustoconical centrifugal wheel directs air radially and axially through angled blades extending between front and back plates.

A titanium compressor wheel design with a frequency ratio below 4.0 utilizes superior damping capacity to reduce vibration.

Oblique spacer nib face converts violent axial forces into friction, reducing shear stress and enabling a lighter fan rotor design.

Segmented conductive elements monitor turbine blade degradation without requiring machine downtime, enabling continuous maintenance scheduling.

A propeller vane with a tilted distal end redirects airflow toward the rotation center to increase wind-receiving surface area.

Hydraulic pitch mechanism with separated guiding surfaces resolves space constraints while maintaining precise blade position tracking.

Defining the airfoil core shape with precise Cartesian coordinates expands the impingement cooling area, reducing reliance on downstream film cooling.

Segmented hollow blades with laser-welded covers reduce centrifugal fan impeller weight, resolving the trade-off between mass reduction and blade strength.

Seal strips with three-dimensional curvature stiffeners bridge gaps between aerofoils and annulus fillers in gas turbine engines.

Asymmetric contra-rotating rotors reduce vortex interaction noise while maintaining lift and eliminating tail rotor requirements.

Integrated rotor head suspension eliminates skilled labor alignment by stabilizing center of gravity during installation.

A bistable pitch propeller system uses aerodynamic forces and mechanical stops to rotate blades into stable positions for different flight modes.

Self-shredding composite blade dissipates kinetic energy via frangible sections, preventing secondary impact damage to adjacent engine components.

Variable chord length patterns on helicopter tail rotor blades reduce acoustic noise and control loads by equalizing airflow homogeneity.

A sculptured throat spool minimizes alternating tensile and bearing stresses in tension-torsion strap assemblies.

A tower-mounted robotic arm engages wind turbine blades for simultaneous cleaning and inspection, reducing downtime caused by manual maintenance operations.

Rounded leading edge geometry reduces sensitivity to surface irregularities like dirt and scratches, maintaining stable aerodynamic performance.

Replacing heavy swashplates with integrated BLDC actuators reduces vibration by 80% and noise while enabling rapid higher-harmonic control.

A composite protective coating for ram air turbine blades uses compressible and non-compressible fillers to shield surfaces.

A variable pitch cross-flow fan assembly adjusts blade angles to generate thrust at constant rotational speed.

Segmented foam blocks within rotor blade cavities reduce torsional rigidity while maintaining compression strength.

Merging propulsion and pitch motors into one rotatable housing reduces mechanical complexity and bearing count.

A centrifugal multiblade fan uses an inclined front edge shape to maintain constant blade thickness and curvature radius across the span.

Cyclic pitch actuators twist wings to adjust incidence, reducing structural weight and drag while improving aerodynamic efficiency.

A propeller pitch control system uses discrete fluid passages to limit hydraulic flow for specific operational modes.

Resilient balancing weight clips attach to gas turbine rotor flanges via elastic deformation, eliminating rivets and reducing assembly weight.

Segmented radial heating arrays selectively warm blade portions to remove ice, reducing power consumption without compromising rotational balance.

Filling surface cavities with nonmetallic materials tunes vane frequencies to avoid engine excitation bands.

A spoked spacer ring with core gas path seals reduces rotor weight while maintaining thermo-mechanical fatigue resistance.

Inflatable ducted fan UAV folds components parallel to center body, enabling multi-UAV carriage in small launch tubes.

A multi-motor RPM control system maintains uniform rotational speed across independent propellers using dynamic electronic speed commands.

Increasing cross-section lift device reduces acoustic noise through shear flow diffusion while maintaining high lift performance.

Pivotable ring wing sections transition between flight modes while actuators lock positions to reduce vibrations and turbulence during operation.

Segmented attachment features on a conical fan hub reduce blade off-load mass and impact energy during dislodgement events.

Alternating pressure side thickness in integrally bladed rotors alters blade vibration frequencies to reduce flutter susceptibility.

A clip absorbs axial forces in a thermal turbomachine rotor end piece assembly.