Propellers TRIZ Cases

A selective power transfer mechanism lets one motor switch between opposing unidirectional fans, cutting weight and power use in load control.

Through-thickness yarns within each ply raise interlaminar shear strength and impact resistance in lightweight composite propeller blades.

Adjustable blade treatments and transducers alter propeller airflow and phase to reduce UAV noise during flight.

Sensor data at the propeller seat verifies locking and motor compatibility before startup, helping prevent UAV propeller detachment and crashes.

By controlling rotor speed and blade pitch at a target advance ratio, this VTOL layout sustains forward-flight lift without fixed wings.

A compact pylon attachment uses articulated links and a main rod to carry engine loads with less bulk, reducing drag and weight.

A septum between adjacent aircraft propulsion ducts separates airflow to limit cross-flow, backflow, noise propagation, and icing while preserving thrust.

Propeller modulation and thermal coupling manage eVTOL icing by shedding balanced ice and heating targeted blade areas without added protection weight.

Angled wingtip motors add lateral thrust and torque for precise VTOL control with fixed-pitch propellers, reducing weight and power use.

Centrifugal-force engagement locks radially movable propeller blades during rotation, preventing unintended folding and preserving drone controllability.

Hydraulic blade pitch actuation replaces heavier electromechanical parts and internal bearing assemblies to shrink rotor hub size and weight.

Segmented front engine attachments and ball-joint links create compact load paths that reduce nacelle fairing bulk, weight, and drag.

A split front attachment between the pylon, central casing, and fan casing reduces bulk and weight while improving nacelle fairing.

Shared obstacle sensing and route updates help VTOL fleets avoid hazards, while cabin layout and dual doors speed safe boarding.

Cyclic pitch control with composite propeller blades cuts 1P mechanical loads, reducing mass and drag in high-bypass aircraft propulsion.

A variable metering valve slows hydraulic drain during propeller feathering to reduce thrust spikes, structural loads, and controllability issues.

Two 3D woven root skins are separated and wound around an insert to form a compact propeller blade root that resists tensile, bending, and hoop loads.

A plate-and-damper assembly converts airfoil flexing into radial plate motion, dissipating vibration and reducing wear, failure, and repair time.

A triaxially braided carbon fiber spar-root with wedge retention cuts airfoil weight while preserving strength and heat resistance in turbine engines.

A hollow 3D-woven root helps composite propeller blades withstand centrifugal and compressive loads while fitting compact rotor-disc interfaces.

A tungsten-based leading edge cap protects composite wind turbine blades from particle and liquid impact, preserving surface integrity and durability.

A larger slat-gap inlet and fixed outlet use the Bernoulli effect to accelerate airflow, cut drag, and support low-speed lift.

A braided carbon fiber spar and wedge-slot root assembly cuts airfoil weight while preserving structural integrity in hot turbine sections.

Interwoven composite plies with tailored fiber orientations help turbine airfoils resist mechanical and thermal stresses with lower weight.

Laser-projected visual references guide tracer-thread alignment during fiber blank shaping, standardizing decadration and part quality.

A pivoting lift body and single-axis torque transfer help VTOL aircraft balance vertical thrust with lower cruise drag and energy use.

A high T-tail above the wing stall region preserves pitch control in a trailing-rotor VTOL aircraft while supporting efficient hover-to-cruise flight.

Pivoting support sleeves in a turbine engine ring let each variable-pitch blade be removed separately, cutting hub dismantling time and cost.

A wing support grid houses multiple electric fans to deliver VTOL thrust while avoiding the efficiency and complexity limits of single propulsors.

Non-uniform blade pitch control adjusts each fan blade to oblique airflow, balancing loads and reducing high cycle fatigue.

A segmented pivoting support sleeve lets turbine engine variable pitch vanes be removed individually without dismantling the full hub.

Dual-side FPD chambers with permeable covers spread deicing fluid across propeller blade surfaces while limiting aerodynamic disruption.

Different thermal expansion layers create compressive force during curing to prevent core cracking and delamination in composite structures.

Periodic propeller modulation and targeted oil or electric heating manage in-flight ice accretion without adding heavy dedicated protection hardware.

A rotating bracket with swinging bodies changes blade pitch by inertia, cutting swashplate weight, complexity, and endurance loss.

A resistive wire and carbon fiber skin create non-uniform blade heating that prevents UAV propeller icing with low weight and power.

Placing an unducted fan propulsor in high-pressure airflow near the airfoil boosts thrust while reducing interference drag and noise.

Remote counterweight levers use centrifugal force to balance blade-induced axial loads and reduce actuator and hydraulic stress.

By placing an unducted fan in the wing's high-pressure flow region, this case boosts thrust while offsetting interference and scrubbing drag.

A hollow-fiber core and solid-fiber surface help gas turbine airfoils cut weight while preserving robustness and bird-strike integrity.

An electric motor drives the oil pump after engine shutdown so the pitch mechanism can feather propeller blades, cutting drag and airflow disturbance.

Wing-relative propulsor placement uses local high-pressure airflow to offset drag penalties and boost thrust without more engine power.

Conical blade geometry redirects flow axially instead of radially, cutting turbulence while improving propeller thrust efficiency.

A hollow-fiber core and solid composite surface help gas turbine airfoils cut weight while maintaining bird-strike resistance and strength.

Asymmetric blade and vane pitch schedules offset from the aircraft pitch axis cut 1P loading while improving open rotor thrust efficiency.

A forward vane ahead of the aircraft propulsion inlet redirects tripped boundary-layer air to curb low-speed vortex formation and stabilize inlet flow.

An embedded electric machine on the low-pressure shaft enables a three-stream turbofan to raise electrical power while improving efficiency and operability.

Upstream and downstream momentum shedding reshape the streamtube to cut viscous drag and power use at low free stream velocities.