Propellers TRIZ Cases

Segmented damping sheets with air-passing holes cool turbine blade platforms, reducing temperature gradients and manufacturing complexity.

Actuators extend or retract active blade tips based on flight conditions, resolving the trade-off between thrust efficiency and collision risk.

A motor-driven screw mechanism with planetary gearing replaces hydraulic systems, reducing complexity while maintaining pitch control reliability.

Air cushions formed by delivery devices eliminate direct mechanical wear on turbocharger sealing faces while maintaining the required pressure seal.

Curved runner vanes suppress tip leakage flows and cavitation erosion while maintaining pressure recovery in draft tubes.

Pre-positioning blade tips upstream prevents tower contact during strong winds, resolving reliability and manufacturing cost trade-offs.

Segmented coils derive speed and position from induced current, increasing measurement bandwidth without separate excitation.

Independent braking mechanism rotates load application members against the pitch change mechanism, eliminating slip ring maintenance and common mode failures.

Dihydrazide-based curative enables low-temperature curing of fire retardant epoxy formulations, reducing energy costs while maintaining mechanical integrity.

Segmented spar structure reduces thermal stresses by distributing aerodynamic loads across multiple foam cores while maintaining structural integrity.

Segmented slot blocks and inflatable bladder clean cooling surfaces without disassembly, reducing turbine downtime.

Segmenting coaxial propellers into fixed different pitch units eliminates variable pitch complexity while maintaining adaptability across flight modes.

A stiffening plate attached to the outer ring of a wind turbine blade bearing equalizes raceway stiffness, resolving deflection issues in pitch control systems.

An axial aft skirt on a gas turbine blade reduces weight by shortening the shank while maintaining attachment security.

Varying leading edge blade angles along the span reduces three-dimensional losses, flow separation, and tip leakage in axial compressors.

Segmented retention disk sectors merge into one unit with integrated cooling channels that dissipate heat from the annular groove edges.

A turbine bucket airfoil uses a specific nominal profile defined by Cartesian coordinate values to enhance gas turbine efficiency.

A propeller assembly with interconnected blades enables passive pitch adjustment around a common axis to homogenize lift distribution.

Flexible canvas rotor blades enable wind turbines to start rotating in weak winds using inertial power without external motors.

A variable pitch fan module uses a centrifugal flyweight lever to impose a feathered blade position within the rotor annular space.

Variable radius bearing races with relief regions retain propeller blades, reducing weight and stress concentrations while maintaining load capacity.

A radially extendable tailboom assembly retracts during forward flight and extends to form a stable ground contact base.

Autonomous electric aircraft operate from distributed SkyNests to provide rapid on-demand passenger transport.

Optimized thick airfoil shapes minimize wake production and reduce aerodynamic drag by 17% to 25% in rotary wing aircraft.

Actuated joints transition a moveable duct portion away from the rotor assembly in cruise mode, minimizing drag while maintaining thrust efficiency.

Ball screw and hydraulic actuators retract blades without uncommanded extension under centrifugal loads.

A vertical axis wind turbine adjusts blade pitch angles via detection units to optimize energy conversion efficiency.

Dual blade accelerometers generate differential signals to detect fractures, compensating for common mode errors and pitch variations.

Arcuate blade geometry stabilizes airflow in forward swept centrifugal fans, doubling the operating regime while cutting sound intensity by 4 dB.

Unique blade tilts distribute acoustic energy across frequencies, reducing tone components and EPNL levels while maintaining aerodynamic efficiency.

A turbine rotor design uses an inverted fir tree blade root structure with a concave innermost circumferential rotor hook to distribute stresses.

Dynamic cyclic control mitigates non-axial strain forces from edgewise flight, reducing stress and wear on rotors while maintaining maneuverability.

Segmenting the hub into a truss space frame and shell reduces weight by eliminating stress concentrations from large cutouts.

Segmenting the platform cooling channels into a removable cartridge reduces manufacturing costs while allowing flexible redesign of coolant configurations.

A flexible shafting cord synchronizes twin pitch adjustment handles on ride-on power trowels.

A gas turbine rotor rim uses dovetail slots and circumferential channels to anchor annulus fillers through clearance holes.

Centrifugal flow impellers in a volute duct direct air upwardly, resolving bulkiness from axial fans while maintaining efficient cooling.

Corrugated blades on elastic supports improve starting properties while a weathercock stabilizing mechanism maintains downwind stability against strong winds.

A concealed fan mechanism uses a curved link gear to drive oscillation and airflow direction without manual adjustment.

A turbine airfoil trunnion incorporates a stress relief groove at the spar junction to distribute mechanical loads.

Icephobic coating on propeller blades sheds ice via centrifugal force, eliminating electrical deicing systems.

A scissoring mechanism positions lift fan blades at near-zero speed using a dedicated positioning structure.

STOL airfoil profiles reduce drag while safety brackets prevent falling components.

Dispersing particles on airflow surfaces creates targeted surface roughness to enhance aerodynamic lift in gas turbine components.

Merges the balancing flange into the blade retention ring, isolating fixing holes from airflow to cut drag and weight.

Sequentially changing blade outlet angles along the axis increases rotation number differences at varying pressures for constant air volume control.

Nested bevel gears in a shaft coupling minimize envelope size and component count while transmitting power at different angular speeds.

Segmented backing plates and clamps form root seats for blade retention, simplifying manufacturing and repair processes.

Positioning stators aft of the duct ring trailing edge increases rotor blade spacing to reduce noise and vibrational instability in ducted-rotor aircraft.

Segmented fan blades with variable setting angles broaden the high pressure gradient region, reducing aerodynamic noise and flow separation.