Propellers TRIZ Cases

Threaded lock unit prevents blade damage by restricting upward rotation during storage.

A composite propeller blade uses a non-interlinking housing inside the fiber reinforcement to secure the root portion against mechanical displacement.

Axial installation of turbine blade clusters onto a diffuser surface via radial locking lugs reduces leakage between adjacent platforms.

A gimbal lock and blade stop assembly reconfigure rotor degrees of freedom for mode transition.

Separate air inputs prevent fuselage boundary layer ingestion, maintaining thermal efficiency while differential gears ensure thrust redundancy.

An embedded multi-electrode array generates electrical signals to monitor corrosion rates, eliminating offline inspections and reducing turbine downtime.

A cam and control rod mechanism links proprotor tilt to blade pitch adjustment.

Stopping a propeller rotor and adjusting blade pitch converts swirling flow into thrust without adding weight.

Upward airflow drives the rotor to generate lift, eliminating complex torque counteracting mechanisms.

A propeller blade incorporates ribs formed by grooves in the spar core filled with fibrous material to increase chordwise stiffness.

Boundary layer ingestion fan ingests slow airflow to improve propulsion efficiency while thermal management maintains bearing health.

Eliminating the stationary stator allows a single motor to drive dual propellers, resolving energy efficiency limits in battery-powered aircraft propulsion.

Localized wing chord and twist variations neutralize propeller wake asymmetry, reducing trim drag and fuel consumption.

A propeller dynamic scoop captures ventilation air to cool blade roots during low-speed flight phases.

Contoured channel walls manage paste thickness to eliminate air voids and reduce stress concentrations at the shear web connection.

Circumferential rib channels leaking oil through discharge holes to prevent fire hazards in pressurized enclosures.

Sealed slip ring housings isolate components from contaminants, reducing wear and maintenance.

Active flutter reduction system adjusts propeller thrust to mitigate wing motions, increasing stability without adding structural weight.

Segmented slots with partition walls equalize pressure differences, extinguishing harmful vortices at the blade tips.

Aligned channels in a retention housing guide tension-torsion straps, minimizing gaps that cause pin bending moments.

Distributed local control computers manage rotor motion to overcome aeroelastic instability, enabling higher forward airspeeds.

Rotatable wings and foldable proprotor assemblies minimize the aircraft footprint while preventing excessive drive system moments during stowage.

An optimized airfoil shape with a thicker pressure side and cutback trailing edge reduces vibrations while maintaining aerodynamic performance.

A serpentine cooling circuit routes compressor-extracted air through the gas turbine bucket platform to lower temperatures.

Unique blade tilt angles distribute acoustic energy across distinct frequencies, lowering EPNL levels and improving certification.

Internal stiffener with flanges transfers shear forces between propeller blade structural layers, reducing thermal stress-induced cracking.

A pitch angle offset signal adjusts rotor blade orientation to manage rotational speed.

Rotatable arms shift rotor positions to align with payload-induced center of gravity changes, reducing power consumption.

Segmented shroud bodies with dynamic latches resolve the trade-off between blade protection and complex assembly time.

Laterally arranged propellers maintain unobstructed airflow and constant spacing, resolving torque issues caused by pilot obstruction.

A movable actuator sequentially couples electrical deicers to a rotating slip ring, reducing peak power requirements and system weight.

An integrated locking pointer secures turbine seal plates within rotor disc grooves, eliminating bolt assembly complexity and reducing maintenance costs.

A pulley transfer box apparatus routes a looped member around an annular rim to multiply output shaft revolutions.

A gas turbine vane adjusts its throat area via a moveable barrel to prevent flow separation and reduce energy losses.

An elevated shroud accelerates wind velocity by 2.5 times while a horizontal actuator moves the nacelle for maintenance access.

Self-actuating trailing edge reduces blade fatigue and failure risk by passively adapting aerodynamic loads without active control systems.

A turbine propeller blade features an adjustable leading-edge protrusion that modifies vortex formation to minimize acoustic noise.

C-shaped protective liners seal air leaks between blade roots and disk flanks without adding weight to the turbomachine assembly.

Curved wing portions guide propeller-driven quasi-laminar flow to increase lift while reducing the drag-to-lift ratio.

Segmenting the extra-high-pressure turbine into Ni base alloy and ferrite-based sections enables 650°C steam operation while maintaining mechanical reliability.

Flexible rotor blades maintain minimal clearance across rotation speeds, reducing induced drag and noise without adding components.

Conducting layer directs lightning current away from carbon fibre composite nose cone, preventing structural damage.

Four-blade proprotor decouples lead-lag and flapping frequencies to prevent aeroelastic instability at high forward speeds.

Hex-shaped structural core bonded to spanwise skin eliminates complex internal torque tubes, reducing manufacturing time and cost for tiltrotor aircraft.

Stacking I-shaped rings with radial webs reduces thermal loads and creep deformations, extending rotor service life.

Segmented pitch bearing teeth allow selective drive coupling to replace worn sets, eliminating costly hub removal and reducing maintenance downtime.

Dual pressure paths in an electrohydraulic governor eliminate expensive flyweights, reducing manufacturing cost while maintaining precise blade pitch control.

Fan rotor hub specifies cylindrical diameter ratios to generate an interference press-fit that eliminates dynamic imbalance and stress during co-rotation.

Optimized dovetail backcuts reduce stress concentrations at blade-disk interfaces, balancing fatigue life with aeromechanical performance.