Propellers TRIZ Cases

A multirotor aircraft wing integrates shrouded thrust units to enhance energy efficiency and reduce system complexity.

Upstream grids capture supercooled water droplets before they freeze on rotor blades, eliminating electrical de-icing power requirements.

A ring-type fan impeller uses a stop section to block air backflows from interfering with inflow.

A γ-TiAl alloy with controlled β-phase proportions enables reliable forging using conventional methods.

Pitch modification repositions blades into a guide vane assembly when accelerometer-based imbalance detection triggers braking means to secure the rotor.

Segmented disk design with axial holes distributes stress concentration while maintaining flexural and torsional inertia.

Segmented cover shells replace damaged sections without stripping multiple layers, cutting repair time and material handling complexity.

Rainflow counting algorithm analyzes torque variations at the low speed shaft for fatigue assessment.

Sectorized crown interlocks with annular groove to distribute centrifugal forces, preventing rapid deterioration of fragile screw threads.

Spacer inlets pump cooling air into radial passages, reducing thermo-mechanical fatigue while minimizing weight and energy loss.

A variable pitch fan uses asynchronous blade pitching to adjust angles across a wide operational envelope.

A rotor assembly annulus filler uses a biased securing arrangement to mechanically retain the component on the disc.

Centrifugal fan blades incorporate alternating projections and recesses on dorsal and ventral sides to minimize exfoliation and reduce turbulent flow noise.

A flush-mounted weight box inside the rotor-blade spar holds balance weights on guide rods for tip access.

Self-regulating control blades pivot under fluid flow to adjust turbine blade angles, eliminating complex hydraulic mechanisms and maintaining optimal thrust.

A rotor assembly connection separates locking from rotation to simplify propeller attachment.

Self-regulating duct covers eliminate actuators, reducing aircraft weight while maintaining reliable lift generation.

Patterned coatings direct fluid flow and reduce leakage between stages, resolving the trade-off between seal lifetime and turbomachine performance.

An adaptive flight control system modifies feedback gain to adjust propeller blade pitch angles in hybrid helicopters.

Segmented rotor blade sections join via vacuum infusion to reduce transportation costs and maneuverability constraints.

Seven rotary blades paired with eight stationary blades optimize air volume and static pressure in compact axial flow fans.

A turbine blade rotor assembly uses ceramic matrix composite platforms separate from nickel alloy blades to guide airflow and support the airfoil perimeter.

Segmented cross webs increase buckling margins and torsional stiffness without adding blade weight.

Passages through vanes redirect secondary flow to reduce hydraulic losses and enhance pumping efficiency in electric submersible pumps.

A centrifugal fan uses continuous circumferential air channels to move cooling gas through a rotating machine.

Three linear actuators drive a summing member to control rotor position through electromagnetic conversion.

Segmented balancing weights offset from blades minimize stress concentrations while maintaining vibration acceptance for advanced materials.

A helical groove wind deflecting structure accelerates airflow, resolving insufficient wind velocity in conventional collection devices.

Segmented sub-actuators and electromagnetic hold devices resolve reliability complexity trade-offs by enabling automatic takeover during motor failures.

Selective disengagement of the aft fan via a clutch assembly alters blade pitch to minimize rotor-to-rotor interaction noise during critical flight phases.

Offset circumferential bearing surfaces on compressor blade roots improve retention while reducing peening pressures.

A single-piece composite propeller uses a resin-transfer-molding process to encapsulate a polyurethane foam core within a structural laminate skin.

Radial retaining structure within the propeller hub contains blade debris fragments to protect adjacent turbomachines and fuselage components.

An asymmetric pocket recess shifts natural frequencies away from acoustic pressure oscillations, reducing aero-acoustic coupling and enhancing blade durability.

A hydraulic bending device with a fixing element and punch actuates plates in compressor intermediate spaces.

Replacing mechanical shafts with electrical drives allows the augmentor fan to operate independently, resolving redundancy issues during core engine failure.

An elastomer abutment element sits between the retention ring and disk flange crenellations to dampen vibration.

Integrated heterogeneous materials reduce vibration in turbine nose cones without increasing assembly complexity.

Resin-bonded reinforcement rods in a composite fan blade core resist crack propagation while reducing manufacturing costs.

A mechanical stow abort mechanism uses a cam-driven pawl to lock ram air turbine blades during deployment.

Nested aircraft turbine vane cores with shock-absorbing coatings resolve strength versus mass trade-offs by absorbing projectile impact energy.

Spanwise load concentration minimizes exit swirl and kinetic energy loss, reducing design complexity compared to contra-rotating systems.

Segmented impeller blades eliminate welds and notches, enabling easy removal while maintaining contaminant separation efficiency.

A pneumatic actuator system uses centrifugal air pressure to move rotor blade control surfaces.

Pulsing electric discharge deposition limits the repair area on turbine components, reducing elongated welding times and preventing excessive material buildup.

Form rolling produces variable thickness blanks for hollow turbomachine blades, reducing material waste and machining costs through diffusion bonding.

A bearingless rotor system uses a flexbeam assembly to transmit pitch input directly to the blade spar.

Axial tongues direct cooling air over tooth crests, reducing radial thermal gradients and preventing side plate deformation.