Propellers TRIZ Cases

NCMN superalloy turbine blades withstand corrosive geothermal vapours, eliminating washing operations and preserving enthalpy.

Embedded flap propellers increase airflow over extended wings, reducing runway length requirements for short takeoff and landing operations.

Stud bolts remain installed in the interior support while clamping nuts allow repeated removal of the cone tip, eliminating self-locking thread replacement.

Compressor airfoil tip dihedral redirects weak airflow inward to delay flow propagation, mitigating blockage and improving stall margin without efficiency loss.

A UAV propulsion system with a detachable propeller that separates from the rotation shaft upon external force.

A gas turbine rotor blade design incorporates a truss aperture to remove material from the neck section.

A concentric turbomachine uses nested inner and outer fans to produce primary and secondary pressurized flows.

Segmented heavy and light material rings tune vibrator force without housing changes, preventing hopper stress fractures.

Variable pitch fan blades adapt to non-uniform boundary layer ingestion, resolving efficiency losses from suboptimal blade incidence angles.

An elastomeric joint deforms under shear stress to adjust rotor blade twist angles for helicopter and airplane flight modes.

Aircraft with counter-rotating ring wings driven by tip-mounted engines enables vertical take-off and landing.

Weaving composite material through metallic airfoil openings creates a unified structure that resists foreign object damage and prevents disbonding.

Shorter notch blade dovetail radial lengths prevent circumferential interference during insertion, ensuring secure assembly and vibration control.

Variable throat dimension distribution across turbine static nozzle airfoils creates hybrid vortexing flow.

Adhesively bonded guide grilles in wing-mounted ducts resolve the trade-off between flight versatility and device complexity.

A barrier wall prevents bond paste migration into the internal cavity, reducing weight and damage.

Segmented wing feathers rotate independently to simulate bird flight, resolving the trade-off between lift generation efficiency and structural stability.

Segmented blade tips prevent axial walking without adding retention device complexity, reducing gas leakage and weight.

Merging separate control units reduces system complexity and weight while maintaining reliability through independent protection processors.

A hybrid aircraft propulsion system uses a jet engine generator to power electric propellers for efficient flight.

A propeller apparatus with independently foldable blades adjusts configuration to improve energy efficiency during air mobility operations.

Viscoelastic and rigid layers within composite blade walls dissipate vibrational energy through shear deformation.

A processor combines rotor blade and tower bending measurements to calculate real-time clearance distances between components.

Optimized airfoil profile geometry balances aerodynamic loading and mechanical stress on high-pressure turbine blades.

Angled end walls and radial play in a turbine rotor channel enable blade root over-rotation, eliminating shims and reducing assembly time.

Angled drive pinions optimize lever arms to resolve the trade-off between lightweight hub design and sufficient blade adjustment torque.

Gradient SiC-reinforced aluminum layers reduce blade leading edge weight and centrifugal stress without sacrificing impact strength.

Radial openings and a compression tube create a vortex that cools blade roots, reducing weight and extending lifetime.

Asymmetrical root portion generates lift closer to the rotation axis, reducing bending moment stresses on control mechanisms without increasing radial size.

Tilting rotor assemblies on M-wings generate variable thrust vectors to resolve runway length constraints during vertical takeoff.

A spherical cap pivot assembly enables three-axis airflow direction adjustment through friction-based positional maintenance.

Segmented leading edge slits with specific peak-to-trough ratios reduce broadband noise while minimizing drag and manufacturing complexity.

Discharging gas at propeller blade tips disrupts airflow to reduce acoustic output, mitigating noise pollution during low-altitude aerial vehicle operations.

A pitch control device adjusts blade angles during rotation using connecting rods linked to a tilting second part.

Composite coating with porous spray and fluorocarbon resin resists silica adhesion while maintaining durability against centrifugal forces.

Splitting the support ring into aluminum and steel sections resolves weight versus load capacity trade-offs in gas turbine fan assemblies.

A turbine rotor blade platform cooling arrangement distributes coolant through segmented plenums to enhance heat exchange across the platform region.

Fluid pressure differential drives an inclined plate on a bent shaft, reducing mechanical complexity and moving parts.

Segmented labyrinth chambers and a shaft vacuum bore evacuate moisture to prevent bearing damage.

Local heating of the suction pipe reduces thermal mass, preventing pump damage and cutting startup energy.

Propeller controller disables shaft shear detection logic during unfeathering, preventing false positives from torque drops while maintaining engine protection.

Winglets extending from the pressure sidewall form a channel that increases tip leakage path resistance.

A centrifugal blower incorporates an anti-leakage element extending from the inlet edge into the casing to partially cover rotating blades.

A rotating inlet cowl plug encloses fasteners within an aerodynamic shell to maintain external surface continuity.

A cylindrical foot with a locking ring secures variable pitch propeller blades against centrifugal stress and vibration.

Varying propeller blade geometry distributes acoustic energy across a broader frequency range, reducing noise levels inside and outside the aircraft.

Segmented rotor system with variable-pitch blades reduces power consumption during sustained flight by separating lift and thrust generation.

Merges auxiliary power and ram air turbine roles into one system, reducing aircraft volume while maintaining emergency energy supply.

Gravity-driven pivotable vanes minimize opposing drag while maximizing wind force application for higher rotation efficiency.

Merges multiple bearing rings into a single hub body to maintain rigidity without increasing mass or device complexity.