Propellers TRIZ Cases

Modified under-platform tabs and layered coatings reduce mechanical stress factors while improving corrosion resistance in gas turbine engines.

Segmented concentric fans operate at distinct rotational rates to resolve the trade-off between high propulsive efficiency and excessive tip losses.

Merging individual film holes into common exit regions via trenches reduces manufacturing complexity while maintaining heat transfer rates.

Distributed propellers on a closed wing provide lift and thrust, resolving the stability versus speed trade-off in vertical takeoff and landing.

Defined Cartesian coordinates optimize the turbine vane profile to reduce mechanical stress and improve casting manufacturability.

Stream-driven vehicle mounts turbine to boost power output while reducing structural complexity.

Sharp inner wall deflects and breaks up birds, allowing sacrificial outer wall to absorb impact energy without complex reinforcement.

Concave channels on impeller blades direct air downward and outward, resolving the trade-off between design flexibility and energy efficiency.

A boundary layer ingestion fan system with a 0.45 to 0.55 hub tip ratio increases blade speed and reduces hub diffusion losses.

Active flow control systems eject gas through rotor blade apertures to modify aerodynamic properties and maintain turbine performance.

Composite reinforcing spars in a hollow casing framework increase bending strength while reducing weight.

A tailsitting biplane aircraft uses a tiltable coaxial rotor system to generate thrust for vertical takeoff and forward flight.

A hub assembly bearing arrangement combines spherical and radial bearings to manage rotor blade forces.

A pressure relief device with pivoted lids and air control units manages airflow through passages to adjust blade pitch angles.

Segmented side pockets with convex and concave surfaces guide moveable seals, maintaining structural integrity while regulating high-temperature gas flow.

A mobile rotor locking device secures a wind turbine main shaft using independent locking members to prevent rotation.

A spiral blade on the spinner directs air to the fan stage for efficient intake.

Synchronous rotation of the guiding cover and impeller prevents axial leakage, reduces intake noise, and increases air capacity.

A rotor blade weight system integrates a weight box within the spar structure to maintain aerodynamic surface continuity.

Moveable slat stows wing propulsors to reduce parasitic drag and enable high-speed aircraft operation.

Segmented propulsion along the wingspan reduces structural weight while blown control surfaces enhance low-speed maneuverability.

Adjustable eccentric bearing axis offset reduces centrifugal loads on the rotating blade to maintain rotor stability at high speeds.

Retractable downstream propeller blades minimize vortex interaction noise while maintaining thrust production.

Asymmetric blade spacing in a turbo machinery hub alters oscillating frequencies to reduce synchronous vibrations and stress.

Dual impellers with optimized front and rear blade lengths increase air amount and static pressure for small appliance cooling.

Segmenting power distribution into independent AC and DC subsystems reduces weight and losses while enabling precise flight-control thrust modulation.

Magnetic bias aligns propellers passively, reducing aerodynamic drag during idle flight.

Segmented acoustic panels redirect and absorb noise, reducing community impact without adding significant vehicle weight.

A bearingless rear deformation region eliminates discrete flap bearings and associated wear, reducing aerodynamic drag while maintaining adaptive lift control.

Thermoforming a chopped fibre composite insert within textile layers eliminates stepped ply drop-off at the blade root.

Composite propeller blades arranged in multiple parallel planes reduce spinner diameter and aerodynamic drag while maintaining structural integrity.

Automated fiber placement weaves conductive components directly into impeller structures, eliminating costly metal coatings and complex post-processing steps.

Variable rotor and blade hook dimensions balance centrifugal stress margins in low-pressure steam turbines.

An optimized airfoil profile redirects gas flow to enhance thrust capability.

Platform undercuts and serpentine cooling passages reduce trailing edge stresses by 37% and operating temperatures by 4.8%, extending design life by 769%.

Telescoping driveshafts adjust conformal propeller blades to minimize aerodynamic drag during cruise while maintaining vertical lift capability.

Dynamic propeller switching reduces noise disruption while maintaining delivery efficiency.

Gravity-fed oil holes and integrated cooling air passages in the forward cover resolve bearing temperature and reliability trade-offs.

A ceramic matrix composite turbine vane uses a segmented metal spar to manage internal pressure and reduce mechanical stress on the airfoil shell.

A folding propeller hub mounts blades via connecting pieces on a single surface to adjust rotary damping.

Non-periodic airfoil tubercles and trailing edge crenulations delay flow separation, resolving the trade-off between high efficiency and maneuverability.

A spindle-coupled structural fitting links stators to a duct ring, positioning the aerodynamic components aft of the trailing edge.

A ducted fan engine with at least 19 rotor blades reduces noise emission through acoustic shielding.

Segmented yokes with independent flap axes distribute aerodynamic load across blades, resolving thrust generation limits in rotary-wing aircraft.

A ram air turbine gearbox uses compound gearing to drive hydraulic and electrical devices at optimized speeds.

A conductive film layer applied to wind turbine enclosure structures forms a flexible shield against electromagnetic fields.

Segmented impeller blades with varying cross-sectional areas manage centrifugal loads to maintain structural integrity.

Tip connectors join adjacent propeller blades into a closed structure to improve structural rigidity and reduce noise.