Propellers TRIZ Cases

Asymmetric serration patterns on the rotor blade surface maintain noise reduction performance across varying wind flow directions.

Merging guide grilles with structural ribs eliminates separate components, reducing aircraft weight and manufacturing complexity while maintaining strength.

Varying included angles between stationary blades suppresses pure-tone noise without complicating impeller balance adjustments.

Automated control system manages variable-pitch propeller blade angles and engine power for aircraft landing operations.

Segmented airfoil sections join a continuous spar via clamps and adhesion, reducing transportation costs for large wind turbine blades.

Circumferentially oriented fibers in a polymer matrix enable integral abutment surfaces that reduce weight while maintaining structural strength.

Variable pitch propulsor blades pivot between thrust and idle positions to resolve the trade-off between high horizontal thrust and vertical lift capability.

Segmented shroud segments join airfoils via weld connections to enhance aeromechanical stability while reducing manufacturing complexity.

Tensile forces between opposite internal bushings counteract weight-induced deformation of composite wind turbine blades during storage.

Outer drive gears rotate the rotor rim to move blades, reducing hub size and assembly weight.

A propeller control system uses estimated blade angle to set controller gains for speed governance.

Segmented bearings reduce fan hub diameter by separating force absorption, enabling higher blade counts without increasing mass.

Elastomeric supporting members absorb vibration and noise transmission to the fuselage, reducing wear without increasing structural complexity.

A rotatable radiator pivots between a heat dissipation position and a retracted transport orientation.

A static dissipative coating material manages electrical charge on metallic fan blades.

Movable shroudings on inclined rotors reduce drag during forward flight while maintaining safety enclosures for hover operations.

A single actuation system articulates the stabilizer across flight modes, reducing device complexity while maintaining control precision.

Nesting a mass and elastic rod inside the drive shaft cavity reduces vibration transmission without altering rotor components or airflow.

Axial turbine configuration overcomes radial drive limits by stacking multiple wheels to exceed 1000 W output.

A controller monitors propeller blade pitch and torque signals to detect erroneous sensor readings.

Nesting motion conversion units inside the hollow motor shaft reduces the axial length of the propellant force generator while enabling variable pitch angles.

Electronic pitch adjustment maintains constant torque and thrust by estimating parameters from speed and density signals, preventing structural overloads.

Force sensors measure airflow asymmetry to tilt a plate assembly, reducing parasitic moments and wear on turbine propeller components.

Dual-driven impellers mix exhaust gas with ambient air to create a high-velocity columnar plume, extending effective stack height beyond physical constraints.

A levered counterweight assembly rotates fan blades to a feathered position using centrifugal force.

A ducted fan cowl lip groove utilizes Coanda effect jet flow to draw air inward, preventing separation at the compressor blade inlet during inclined flight.

A propeller safety device inserts a moving part into a fixed part to reduce total length during flight.

A phonic wheel with angled markers detects propeller rotational position to maintain phase synchronization across multi-engine aircraft.

A pitch control system uses a multi-position switch to generate commands for adjusting propeller blade angles.

A turbine exhaust strut airfoil profile defined by specific Cartesian coordinates to axially straighten gas flow and reduce residual swirl.

Buckling members in passive adaptive wings change shape to mitigate gust loads, reducing structural mass and complexity for high-altitude endurance aircraft.

Notched flank segments arrest cracks under centrifugal force, preventing catastrophic detachment and enabling early damage detection.

Beamwise folding reduces tiltrotor footprint while minimizing drive system stress.

A pressure-adaptive honeycomb structure alters stiffness via cell differential pressure to enable wing morphing.

Applying a damping coating to gas turbine airfoils reduces vibrational stresses and extends fatigue life without adding mechanical complexity.

A foldable propeller uses a sliding moving portion and link assembly to rotate blades around a hub.

A tilt mechanism reorients the rotor mast to quickly cross natural frequencies and minimize flapping loads.

Merging the drive wheel with the working member reduces device complexity while enabling versatile terrain adaptation and multi-tasking.

An engine with a movable aerodynamic component adjusts exhaust geometry via transmission, eliminating complex actuators to reduce weight.

Angled attachment surfaces in the adapter enable folding without removing fairings, reducing manufacturing complexity.

An inert compound layer with specific crystalline structures prevents molten sand penetration in thermal barrier coatings, extending component lifespan.

A counter-rotating propeller drive system uses independent electric motors to replace mechanical gearboxes.

Solvent-free high char resin boosts green strength, reducing porosity and cycle time.

A fan blade assembly uses an integral openwork structure on the blade iron to support flexible materials without a separate frame.

Segmented cooling passages apply localized turbulation to improve thermal stress resistance while minimizing pressure loss.

Segmented rings minimize centrifugal forces at high speeds, preventing failure from knit lines while maintaining airflow efficiency.

Geometric tangential shifts of blade stacking axes reduce synchronous forced response in turbomachines without compromising aerodynamic efficiency.

An offset apex point on a tapered fairing body resolves air flow area distribution contradictions in short intake gas turbine engines.

A unitary rotor hub consolidates structural components to eliminate redundant hardware.

Control system detects rotor-blade pitch changes by analyzing motor torque and speed parameters, eliminating the need for additional mechanical sensors.