Propellers TRIZ Cases

A single lever turboprop control system uses torque-based scheduling to adjust engine parameters.

Segmenting lift across multiple ducted propellers reduces blade size while maintaining high payload capacity and extended flight duration.

Segmented flexible joints enable curved blade shapes and inclined edges, resolving limited air-driving efficiency in self-assembly micro fans.

An asymmetric slot root design shifts peak stress radially outward in gas turbine rotor disks.

CFD-driven optimization of blade and vane profiles reduces starter weight while maximizing energy conversion efficiency.

Blade tip drive components eliminate heavy gearboxes to increase usable flow area and reduce assembly weight.

Zirconia or hafnia coatings prevent spalling and preserve fatigue life in gas turbine disks.

Distributed thrust array with independent propulsion assemblies enables stable hover and efficient transitions between VTOL and biplane orientations.

A propeller hydraulic actuator uses pressure sensors to measure load differentials for closed-loop control.

Radially offset one-piece rotor spool sections joined by a rotor ring enable independent broaching while preventing tangential movement.

A helicopter rotor blade control device uses a spherical joint to pivot actuators around the swash plate disk.

A rotor-shroud assembly rotates with pivotable blades to enable adjustable pitch control.

Convex hub surface transforms peak axial stress into radial stress, mitigating structural failure without increasing disk weight.

Offset impeller vanes and a flow splitter define a mid-impeller bleed location, enabling low-loss recovery of 1% to 10% bleed flow without complex redesigns.

S-shaped rotor blades prevent air inrush collisions and reduce hub stress while boosting viscous flow pumping speed.

Movable blades on rotatable hubs adjust average solidity, resolving the trade-off between vertical takeoff thrust and high-speed cruise efficiency.

A fluid turbine design positions all bearings on one side of the rotor to cantilever support the blades while housing the generator at ground level.

Web-connected impeller blades enable a compressible axial pump rotor to expand radially, resolving the trade-off between structural integrity and compactness.

A coaxial helicopter propulsion system uses a gimbal assembly to shift weight for flight control.

A gas turbine blade retention system uses an electroformed rubstrip and insulating layer to protect components from wear.

Pumped seawater disperses in the eyewall to reduce ascending air speeds, attenuating cyclone intensity without creating resonance effects.

Varying carbon fiber proportions in a wind turbine blade increases tip stiffness, reducing deflection and weight.

Segmenting the bond coat into oxidation and spallation resistant layers resolves the complexity-reliability contradiction while extending component life.

A fluid-flow machine blade uses an internal cavity and nozzle outlet to generate a tangential jet that energizes the boundary layer.

Actuators generate controlled vibrations on rotor blades to delay flow separation, reducing drag and increasing power production.

Segmented shaped wire fan grill with integrated handle and apertures resolves airflow restriction trade-off during blade protection.

Dual electrical control systems regulate blade pitch angles to prevent engine overspeed and excessive drag through redundant torque application.

Segmented internal cooling passages remove thermal energy from the attachment, platform, and airfoil sections despite limited inter-lobar space.

Flexible spring and bayonet flanges secure turbine nose cones without support rings, reducing weight and assembly complexity.

Articulating propulsors eliminate complex anti-torque gearboxes and protect rotors from shrapnel via enclosable nacelles.

Bonding a separate serrated plate to the trailing edge suppresses Karman vortices without reducing rotor speed or power generation efficiency.

An annular aft support ring enables radial attachment, reducing geometry complexity and manufacturing costs.

An additional steam inlet device manages flow to reduce temperature stress in turbine sections.

A quick disconnect coupling uses a retractable radial key to secure a propeller hub, reducing replacement time without adding aircraft weight.

Segmented blade tip fuse absorbs impact energy through sacrificial erosion, protecting the engine casing from secondary damage.

Segmented H-shape oil-sealing structure prevents lubricating oil loss under vibration, while plastic bushings lower material costs.

Internal passages and diffusers direct cooling fluid to form a protective film on turbine sidewalls, reducing thermal fatigue in high temperature regions.

Segmented battery pods isolate fire risks and reduce weight by enabling independent jettisoning and passive cooling.

Segmented clutch connections reduce starter size and starting time by driving separate spools, avoiding excessive power requirements.

An integrated balancing weight clip eliminates rivets by using elastic deformation and detent engagement to secure the assembly without adding weight.

A multi-element rotor blade uses a common cuff to support centrifugal forces, isolating slat struts from rotational loads.

Tilted forward rotors create a synthetic wing that reduces induced drag while maintaining even lift distribution across the span.

A bleed air driven lift fan rotates via compressed engine gas to generate vertical thrust.

Axial clamping mechanism secures propeller blade root against friction damage from aerodynamic vibration.

Resilient spring arms retain a block-like centerbody in a turbine rotor pocket, enabling repositioning without material removal.

An aircraft propulsion system uses an electric generator to transfer power from a turbomachine to an auxiliary propulsor assembly.

A side channel compressor housing shell integrates adjustable annular sealing areas via a disc spring system to optimize gas flow.

Enlarged strut sections form controlled fillet radii at duct wall junctions, eliminating sharp corners that cause high stress concentrations.

Axially offset dual annular rows double balancing capacity without increasing radial diameter, delaying costly maintenance interventions.