Propellers TRIZ Cases

Electromagnets adjust individual blade pitch angles to eliminate heavy flight control surfaces and reduce aerodynamic drag.

Arc-shaped blades reduce noise while maintaining high tip speed ratios, achieving power coefficients above 52%.

A conical spinner design with specific radial distance ratios deflects debris away from the fan rotor.

A combined control system manages propeller speed and pitch via a priority selection stage that merges separate regulator outputs into a single driving quantity.

Cascade tip baffles bridge pressure and suction side ribs to partition the airfoil tip into sealed pockets, reducing combustion gas leakage.

Concave-curved leading edge inflections align with gas flow paths to minimize incidence loss and prevent leakage across varying velocity ratios.

Axial hoop locking device uses convex blocks and guiding inclined planes to secure objects.

Cladded vane retaining ring prevents hub failure vane loss by ensuring continued radial retention.

Pivoting sheath aligns with exhaust flow to shield blade roots and minimize acoustic emissions.

Contra-rotating turbopellers invert downstream blade sweep, avoiding wake-vortex interaction as smaller diameter raises loading and lowers yield.

Segmenting the hub into spokes reduces drag from motor housing, improving propulsion force and efficiency.

Liquid-tight impingement faces shield porous damping material from contamination while channels direct sound waves for broadband attenuation.

A flexible yoke supports a non-axisymmetric bearing element with spherical and conical surfaces to react rotor blade forces.

Tilting the propeller blade centreline offsets the center of gravity to generate a centrifugal bending moment that counteracts aero-loading forces.

Geometric codings on securing plates enable haptic and visual distinction, reducing assembly errors in gas turbine stages.

Cylindrical sleeve links locking pin and tubular component in rotation, preventing forcing nut unscrewing under engine vibrations.

Zigzag separation gaps in a turbo machine shroud provide dynamic vibration damping through friction, resolving efficiency versus vibration trade-offs.

A wind turbine airfoil family featuring a blunt trailing edge, an oval suction side, and an S-shaped pressure side for enhanced structural stiffness.

Segmented masses on a radial lever absorb diesel engine torque pulsations, reducing transmission weight while maintaining compact rotorcraft design.

Lock plates direct cooling air through truncated fir tree passages to resolve inadequate root cooling.

Segmented circumferential ring propulsors provide three-dimensional maneuvering capability without protruding rudders, reducing damage susceptibility.

A control ring for variable-pitch blades uses a pivoting axis carried by the shaft support to maintain precise alignment.

Eight thrust producing units divided into two independent sub-assemblies enable dynamic tilt and aerodynamic shrouding for efficient flight.

A pultruded composite blade uses a torsion spring for pitch control.

Tapered rotor blade tip sides maintain laminar airflow and prevent separation in stowed configuration, reducing drag during jet mode.

Segmented platform cooling arrangement directs coolant flow through distinct high and low-pressure manifolds to resolve sealing inadequacy.

Individual blade control system compensates dynamic forces via pitch adjustments, reducing vibration and noise while lowering control loads.

A coolable borescope boss sprays cooling air into a central hole to manage thermal loads on the plug tip.

Variable speed drive adjusts propeller pitch via coupled rotors, reducing motor energy consumption and wear.

A virtual swashplate UAV propulsion system controls propeller pitch by varying motor rotor positions.

Segmented conductive extensions allow removable receptors to channel lightning strikes, reducing maintenance complexity.

An inductively energized propeller hub uses a reversible hubmotor to actuate precise blade pitch changes across a full range of settings.

A propeller assembly compensates for twisting moments using a counterweight blade, reducing parasitic energy loss and actuator size.

Dual-layer non-metallic wraps protect composite turbine airfoil leading edges, eliminating metallic detachment risks while maintaining structural integrity.

Non-uniform blade spacing in a rotary machine disrupts periodic wakes and bow waves, reducing resonance and vibration on stationary structures.

Snap-fit retaining clips engage axial grooves to constrain composite blades, eliminating stress concentrations from deforming smash plates.

Selective energy activation of frangible additives enables controlled bondline degradation for safe aircraft component disassembly.

Aircraft wing pivots between split and monoplane configurations to enable vertical lift and high-speed forward flight modes.

Chevron rectilinear tongues seal turbine sectors, reducing air leakage by 10-20% while minimizing stress concentration near the hot face.

Autonomous engine controllers verify synchronized blade angles before commanding reverse thrust, eliminating yawing from unsynchronized transitions.

Composite gas turbine blade voids initiate controlled delamination to dissipate impact energy from bird strikes.

Automated design tool compares entered circuit elements against known non-compliant patterns to alert designers of violations during the layout phase.

A rotor blade pitch-change apparatus adjusts blade angles via a ratcheted hub mechanism responding to electric motor torque variations.

Segmented annular retaining ring prevents fan blade decoupling from the hub during variable pitch adjustments.

Overlapping skin portions merge with spar body sections to eliminate adhesive interfaces, reducing delamination risk under load fluctuations.

Variable blade pitch and outlet flow control redirect fluid flow from one inlet to eliminate separate thrusters, reducing aircraft weight.

Annular attenuation bracket secures impeller tubes via frictional shear bonds through aligned through-holes.

Blades with an outer periphery slope suppress turbulence to reduce noise by 0.7 dBA while integral molding simplifies manufacturing.

Preheating titanium aluminide turbine and rotating alloy shaft with varying pressure stages reduces thermal stress and cracking during bonding.