Propellers TRIZ Cases

Circumferential slots and pins create an interference fit that prevents axial and rotational movement, eliminating airflow losses.

A bearing support employs a fuse pin that fractures under severe loading to protect engine components from damage.

Cartesian coordinate-defined airfoil profile reduces flow separation to maximize work transfer and thrust capability in single stage high pressure turbines.

Segmenting the hub and blades from the annular shroud reduces tooling complexity while maintaining structural integrity through brazing or welding.

Segmented external parts bond to create a hollow blade root, reducing costs while maintaining fine microstructure quality.

L-shaped fluid receiving parts erect impeller blades to capture forward flow pressure, reducing backward resistance and boosting torque.

Hydraulic connection means equalize actuator chamber pressure to constrain blade pitch angle at a predetermined limit.

Segmented wire shields under spinner fairings disperse bird strike energy across wider areas, reducing structural loads and replacement costs.

Accelerometer data identifies resonant speeds causing lateral motion, allowing the controller to exclude those parameters and maintain stable operation.

External cog collars and a dual-button release system allow angular adjustment of paddle blades while preventing accidental disconnection in sandy environments.

An open rotor airfoil section shapes its meanline to create near-uniform chordwise pressure distributions on the suction side.

Passive aerodynamic tilting of ducted rotor assemblies eliminates heavy actuators, reducing weight and drag while maintaining propulsion efficiency.

Multiple lifting points distribute loads across the blade center of gravity, preventing damage to delicate trailing edge structures during handling operations.

Interlocking splined and castellated bushings allow rotor blade folding without heavy automated mechanisms, reducing assembly weight.

A composite fan blade root uses a segmented cavity and blocking part to secure the structure against vibratory loads.

A composite rotor blade shell absorbs centrifugal loads without internal spars, reducing manufacturing complexity.

A hybrid airfoil spar combines a metal core with composite outer layers to enhance structural rigidity while reducing overall weight.

Vertical flow guides balance pressure at margins to reduce spanwise fluid flow, minimizing induced drag from wing tip vortices.

A channel houses a driveshaft within a fuel tank, using a movable panel to provide direct access without emptying the reservoir.

Transverse stitching threads anchor metal strips to composite blades, preventing impact detachment while preserving aerodynamic performance.

Asymmetric lockwire groove profile constrains circumferential rotation, preventing axial bucket movement and cooling flow blockage.

Laminated rubber thrust bearings replace rolling elements to eliminate friction torque variations and ensure accurate passive pitch control.

Asymmetric triangular connecting wall reduces air flow disturbance and noise by 5.4 dB while maintaining sealing effectiveness.

A computer adjusts deicing power based on ambient conditions and shaft speed to prevent ice accumulation without reducing turbomachine efficiency.

Stationary blades connect to a motor case bottom wall positioned closer to the air suction opening than their discharge-side edges.

Solid elastomeric dampers replace hydraulic systems to maintain vibration damping across wide rotation speeds without centrifugal force interference.

Aligning column boundaries with gas flow reduces molten sand infiltration and porosity, increasing hardness and durability of the thermal barrier coating.

A compressor blade airfoil profile with variable thickness along the span to enhance structural stiffness and rub tolerance.

A gas turbine control system limits engine power using blade angle and thrust direction thresholds to manage rotational speed.

Synchronized rotatable wing extensions reduce download forces from rotorwash and dampen structural vibrations via active oscillation.

Increasing leading edge radius and modifying intermediate segments extends the negative stall angle, reducing power consumption during reverse flight.

Static drive and control gears regulate an epicyclic gear system to displace propellers, removing slip rings and rotating hydraulic couplings from the design.

Varying blade radii along the fan width disperses air flow uniformly, preventing flow separation and reducing energy loss.

Dynamic valve control adjusts cooling air delivery to the wheel space, resolving performance losses from excessive coolant usage.

A movable test stand applies forces along a predetermined axis to wind turbine rotor blades using clamping devices.

Asymmetric stator vanes separate root chords to ease hub attachment while overlapping tip chords maintain flow straightening efficiency.

Segmented louvers adjust dynamically to reduce flow separation and turbulence during vertical takeoff transitions, minimizing drag.

Replacing mechanical gears with a magnetic coupling eliminates vibration and weight while transferring torque between contra-rotating propulsion stages.

Varying blade lengths on the upstream propeller strike downstream rotors at different radial positions, reducing interaction noise without compromising thrust.

A rotor blade extension uses a cutaway mounting portion to attach flush against the pressure or suction side of the wind turbine blade.

Segmented annular oil guides prevent leakage during radial shaft movement while enabling non-destructive disassembly in cluttered turbine zones.

Intermediary rigid ring distributes radial loads across rotor flanges to reduce fastener interface wear and stress concentrations.

A variable-pitch fan system manages turning-moment forces via a counterforce mechanism, enabling efficient pitch variation for fuel optimization.

Multiple power generator systems with counterrotating propellers provide redundancy against single rotor failure, ensuring stability during VTOL operations.

A geared gas turbine engine uses an epicyclic gear assembly to rotate the fan section at a speed different from the turbine section.

A propeller blade pitch control device uses a heat insulation element between the radial shaft and pivot to reduce thermal conductivity.

Joining front and rear rotor head segments at planes intersecting the rotation axis reduces cross-sectional area while maintaining structural reliability.

Curved trailing edges on Francis pump-turbine runners reduce secondary flow loss and prevent backflow during partial load operations.

Wrapped pre-preg lamina around contoured block distributes stress at the rotor blade root, preventing rapid failure propagation and detachment.