Propellers TRIZ Cases

Self-adhering elastomer ramp tabs enable repeatable field adjustments to reduce vibrations without damaging blade surfaces during removal.

A blade lock assembly with a drag brace and actuator rotates proprotor blades between horizontal and vertical planes.

Bayonet flanges secure the nose cone to the turbine hub using fewer fasteners, eliminating heavy support rings and reducing assembly complexity.

Elliptical feed apertures direct coolant jets perpendicularly onto chamber walls to increase impingement pressure and heat transfer efficiency.

A variable pitch fan cooling system uses blade positioning to induce airflow through computer hardware.

Segmented wind turbine blades reduce transportation costs by allowing modular assembly of individual segments at remote sites.

A flexible conduit delivers lubricant along a translating support, eliminating external nozzles and reducing system complexity.

Axial inserted turbine blade root uses a center cutout and stopper member to secure the component on the rotor.

Rotatable pod assembly decouples lift engines from pusher propellers to eliminate downwash interference during vertical takeoff.

Anchoring brake immobilizes the rod relative to the actuator, reducing weight and complexity while maintaining reliability.

Predicts rotor blade masses and moment weights to determine optimal assembly positions, eliminating post-assembly balancing lands.

Replacing friction brakes with a stepping motor achieves indexed blade locking, reducing drag and eliminating restart energy requirements.

A gas turbine fan blade root incorporates a structural zone of weakness to fracture upon impact, lowering casing load.

An angled fir tree blade root suppresses peak notch stresses and fretting fatigue by enabling controlled surface slide under centrifugal forces.

Removable sleeve connects front fan shaft to low-pressure shaft, enabling rear fan access and bearing lubrication without full disassembly.

Propeller blades use negative Poisson's ratio composites with positive Poisson's ratio layers to resolve strength versus impact resistance trade-offs.

Segmented swashplates with constant-velocity joints reduce pitch-flap coupling in high collective configurations, improving tiltrotor precision.

Automated feedback control replaces manual iterations, reducing tracking time while compensating for bearing wear.

Segments the impeller into two blade sets to boost wind pressure and volume while reducing resonant noise.

A two-outlet electromechanical motor drives independent transmissions via braking and disconnector means.

Decouples variable pitch fan engine control into independent single-input single-output loops for precise propeller and turbine speed management.

Sliding bushings and a single outboard pin secure rotor blades without counterbored holes, reducing shear stress concentrations that cause delamination.

A magnetic brake locking mechanism secures rotorcraft blade hinges against parasitic rotation during flight.

An additively manufactured single-piece transfer tube eliminates seal joints to prevent hydraulic fluid leakage while reducing weight and assembly complexity.

Flanged connecting pieces join windmill arm sections with bolts to ensure reproducible assembly and reversible maintenance under field conditions.

Coupling rods drive blades to fold inward, reducing space occupation and wear while maintaining air ventilation.

Relocating UAV motors to the center frame via bevel gears reduces leading end weight, resolving stability and agility trade-offs.

Dihedral sails with controller lanyards reduce drag loads and simplify maintenance by eliminating complex rotor hub assemblies.

Replacing combustion engines with electric motors eliminates heat generation while maintaining sufficient thrust for personal flight.

Redesigned compressor airfoil profile alters natural frequency to prevent tip cracking.

An impeller heating passage directs bleed air through the rotor bore, reducing thermal gradients and extending low-cycle fatigue life.

Sinusoidal hub contours and chamfered edges reduce kinetic energy losses from secondary flows, improving turbine efficiency.

Segmented pressure-retaining ring with relief holes reduces turbulence from axial-radial flow collisions, increasing air pressure and volume.

Downstream cylinders and control shafts adjust upstream propeller pitch, eliminating high-pressure oil ducts and reducing engine weight.

A rotating gun system mounts inside a rotorcraft spinner to fire while the mast turns.

Shape memory alloy actuators adjust vane geometry to resolve the trade-off between structural complexity and noise reduction in unducted fan engines.

Pivoting blades retract the downstream impeller to minimize vortex noise while an epicyclic gear train maintains thrust.

A ducted fan fastening device uses a metallic guide body to receive and align a mounting pin, resolving mounting complexity while ensuring structural integrity.

An emergency actuator moves the collective control to minimum pitch upon detecting low rotor speed.

Helical gussets connect fan blades to the hub, forming a triangulation structure that resolves the trade-off between structural strength and manufacturing ease.

A pitch angle blocking device constrains rotor blade orientation via non-rotatable attachment means and connecting devices.

A centrifugal impeller with a cylindrical wall guides airflow to enhance air-blow efficiency while reducing turbulence noise.

Routing plate assembly merges hydraulic plumbing into gearbox housing to eliminate external lines and reduce oil leakage risk.

Angular segments with variable mass correct rotor unbalance without adding weight or dismantling stages.

Radial limiting faces on the propeller blade root engage bowl stop surfaces to transmit torque, maintaining feathering capacity after kinematic chain breakage.

A retractable propeller apparatus uses a lift unit to move a cover, exposing or hiding the propeller based on flight phase.

Angled guide ramps on the rear lip direct hook engagement, resolving obstructed visibility issues during assembly.

A self-orienting propulsor pivots between lift and thrust modes by reversing electric motor rotation.

A turboprop propeller control system adjusts blade angle schedules during engine restart to maintain safe rotational speeds.