Propellers TRIZ Cases

A wet compression system injects vaporizable fluid through distributed orifices to enhance evaporation and cooling within the compressor duct.

Symmetric radial arms and counterweights distribute aerodynamic loads on the rotary ring, reducing sealing interfaces and preventing jamming.

A divided rotor blade design features leading edge holes to manage fluid flow through the structure.

Stationary linear actuator drives downstream propeller pitch through external bearing linkage, minimizing fluid leakage and manufacturing complexity.

Conical guide surfaces align the front plate with impeller blade tips, eliminating radial displacement during vibration-assisted fusion.

Segmented noise reducers adapt across multiple operating points, reducing acoustic noise while maintaining kinetic energy capture.

A sequencing cam props first rotor blades to prevent interference during second rotor deployment.

Light control module activates warning lights only during aircraft approach, reducing visual disturbance to residents and extending lamp service life.

Segmented partial ring gear design distributes wear across replaceable components, reducing maintenance complexity and costs for wind turbine pitch systems.

Converging trip strips form apex portions that generate turbulence, eliminating thermal mismatches across the entire cooling surface.

Segmented hub structure with positioning protrusions allows individual blade replacement, lowering manufacturing costs while maintaining thrust performance.

A fan wheel with a nonrotationally symmetrical shroud stabilizes fluid flow through the inlet port.

Radial fins emit parallel heated air jets to form a protective boundary layer on gas turbine fan blades.

Dual contact faces on a turbine blade coupling member shift engagement states to suppress high-speed vibrations while preventing excessive stress at low speeds.

Segmenting the retaining mechanism into two nested rings prevents disengagement under thermal stress and eliminates precise machining requirements.

Exit drag curtain enhances air flow efficiency by re-entraining discharged air back into the prevailing wind stream.

An asymmetric foolproofing element on a turbomachine blade shim prevents back-to-front installation, eliminating axial movement and rotor disk damage.

A logic control unit sets the angular position of opposed rotor blades to minimize airflow disruption over fixed wings during cruise flight.

A composite airfoil assembly uses cladding with controlled surface roughness to improve bonding strength between layers.

An extended blade transition area resolves the contradiction between aerodynamic work and structural stability by shifting stabilization to the axial dimension.

Segmented edge shell portions wrap around leading and trailing edges to eliminate weakness lines while enabling fluid conveyance in gas turbine engines.

Removable cooling plate creates a dedicated channel between disc posts and outer surfaces, preventing coolant mixing while enhancing heat transfer coefficients.

Vertical walls and mats dissipate high-velocity water spray energy, reducing secondary losses without increasing casing complexity.

Centrifugal force splays retractable fan blades while elastic fabric expands a protective cage, reducing shipping volume without compromising blade safety.

Radial lowering of drive train components through a side opening eliminates axial displacement and external crane requirements.

Contoured downstream surfaces decorrelate sound source phases within propeller wakes, reducing unsteady acoustic interactions and aerodynamic losses.

Recesses filled with stiffer material increase blade rigidity, reducing elastic deflection and high cycle fatigue in geared fan blades.

Rim trenches segment continuous structures to relieve hoop and principal stresses, preventing fractures in gas turbine engines.

Replacing point-to-point wiring with networked clock synchronization reduces weight and complexity while maintaining reliable propeller phase alignment.

Blending rare earth stabilized zirconia with secondary ceramic particles creates a composite coating structure.

Thermal expansion of a dedicated seal tab maintains tight contact with rotor wheel slots, preventing cooling air loss through dovetail gaps.

Segmented stiffness rings reduce shear losses and part complexity in wing-mounted ducted fans while maintaining geometrical accuracy.

Self-contained bearing generator eliminates slip ring wear by producing electric power directly on the rotating hub.

A distributed thrust array with rotatable motor mounts provides independent pitch, roll, and yaw control across flight modes.

A wind turbine control system uses an impulse generating device to validate rotary encoder azimuth readings against reference signals.

Stowing propeller blades into nested configurations reduces aerodynamic drag during forward flight.

An integral hollow cuff merges with rotor blade tapes to transmit centrifugal loads directly to the hub.

A thrust-lift wing integrates axial and centrifugal fans on a single drive shaft to generate vertical lift and horizontal propulsion.

Counterweights and a spring forcer switch rotor pitch states based on angular velocity, eliminating electronic components.

A fan blade uses a planar metal inlaid part enclosed by plastics to distribute centrifugal forces.

Segmented effectors actuate at 2/rev to 6/rev frequencies, resolving the weight versus noise reduction trade-off in rotary-wing aircraft.

A disposable impeller cover protects compressor rotors using a removable body that matches the front face profile.

Centrifugal pumping transfers motor thermal losses to rotor blade cavities, preventing ice accretion without adding dedicated deicing power or weight.

Pitching wind turbine rotor blades to zero angular acceleration reduces tower root bending moments and prevents structural failure.

Locally reversed airfoil curvature at the tip surface redirects inlet flow inboard, reducing over-tip and tip-vortex losses in unshrouded turbine buckets.

An inclined winglet expands the squealer tip cavity width to improve sealing effectiveness while reducing mechanical stress on the rotor blade.

Prefabricated leading edge segments join to shell components along the blade length, creating a continuous unbroken surface.

An integrated guiding assembly between the nacelle and radiator allows safe positioning from inside, eliminating dangerous external manual intervention.

A hydraulic machine shroud uses a perforated cover wall to enclose rotating components while allowing air flow.