Engine Fuctions TRIZ Cases

Segmented oil passages use ejector effect to maintain drainage while reducing exhaust pressure loss.

Boreholes in the flow splitter dissipate ESS interaction tone noise, reducing engine acoustic pollution.

Reversing cooling fluid flow removes particulates from turbine passages, preventing blockages that cause overheating and premature failure.

Self-adjusting impeller blade rotates to optimize tidal current alignment, eliminating hydraulic drive reliability issues.

A turbine engine assembly integrates a cryogenic fuel delivery system with a vaporizer heat exchanger to manage phase transitions.

Attaching an inner casing-side member to a radial protrusion avoids contact surface obstruction, facilitating easy connection of the upper half inner casing.

Removable aerodynamic smoothing elements fill nacelle recesses to maintain airflow continuity when acoustic panels are detached.

Active vane pivoting prevents high-impact collisions with limit stops, reducing wear and extending maintenance intervals.

A heat exchanger in the bypass duct cools high-pressure air tapped from the low pressure compressor, reducing thermal stress on turbine blades.

Segmented concentric fitting prevents oil coking and blockages by maintaining fluid separation and minimizing heat transfer to bearing lubricant.

Anti-icing heat recovery system transfers exhaust heat via intermediate medium to prevent compressor ice formation while maintaining acid dew point.

Segmented fitting isolates inner and outer fluid paths via interference fit, preventing lubricant coking in gas turbine bearing systems.

A clad drive train wraps around a rotor blade rotary bearing ring to transmit power, enabling easy replacement without dismantling the blade.

Sliding baffle inserts with nested flanges anchor within vane cavities to distribute cooling air, resolving insertion conflicts and boosting heat transfer.

Shroud assembly directs loads through a dedicated hanger and support member to minimize stress on the ceramic matrix composite structure.

A removable core opening allows low-density liquid alloy to flow through a turn portion, preventing surface freckling caused by restricted fluid movement.

Variable steepness angle in an hourglass buoy maintains resonance across varying sea states, boosting power generation without external storage.

Variable cross-sectional baffle inserts maintain consistent Mach numbers and heat transfer coefficients across gas turbine vanes.

Segmented tilting pads with pivot housings absorb high radial loads in gas turbines, resolving bearing failure under heavy stress.

Electrical machine components drive rotatable inlet guide vanes to resolve the contradiction between precise airflow control and mechanical complexity.

Radially offset gas generating cores integrate a generator assembly via a gear system, reducing high-speed spool size and improving efficiency.

Refrigeration system cools combustion products and compressed air to maintain constant power output in hot weather.

Resilient seal limits air infiltration into acoustic chambers, improving noise attenuation and mechanical strength.

Segmented cooling passages meter flow to seal radial gaps and reduce localized heat flux on turbine blade tips.

Axial adjusting disk rotates fan blades to optimize angle of attack, reducing vibrations and noise without increasing weight.

An enlarged second shaft region creates an interference fit with the first shaft to impede rotor separation and absorb kinetic energy during blade loss events.

Contoured discharge regions in an inducer assembly generate high swirl to guide fluid flow into the exit cavity.

Temporarily ablated restrictors enable reliable altitude ignition without increasing permanent engine weight.

A brazed locking tab secures a turbine belly band seal within rotor disc counter-grooves to prevent circumferential sliding.

External tie-rods link the sliding control sector to pivoting flaps, removing aerodynamic losses from internal flow path obstructions.

Differentiating clearance between leading and trailing surfaces reduces gas leakage and prevents thermal trapping in turbocharger turbines.

A flexible shaft connects the turbine accessory gearbox to an external power source to rotate the rotor after shutdown.

A dedicated cooling passage delivers medium to the seal pin region of a gas turbine bucket assembly.

One-piece acoustic panel eliminates separate rear skin to reduce mass and cost while maintaining sound attenuation.

A gas turbine blade outer air seal support assembly uses a rail and groove mechanism to align the cover plate with the inner support.

Segmented circular elements anchor into concrete to eliminate welding risks and idle crane time during tower installation.

Nozzles increase fluid velocity to entrain fresh coolant, maintaining temperature difference along the flow length.

Separating ceramic airfoils from metal platforms reduces attachment pull and simplifies geometry while enabling independent component replacement.

A bypass duct diverts particles away from the engine inlet, preventing pressure losses and flow distortions in aircraft engines.

Segmented spring mechanisms reduce displacement while maintaining stiffness in wave energy converters.

A segmented inlet guide vane distributes heated air through impingement holes to maintain thermal energy along the leading edge.

Segmented platforms bound the hot gas path and distribute mechanical stress concentrations while managing internal cooling flows through integrated baffles.

Intermediary pins resolve the incompatibility between ceramic heat resistance and metal force transfer reliability.

A hollow baffle with a specific opening area fluidly connects the vane cavity to the baffle interior.

Air passage orifices in the metal shroud vent cooling air to reduce mechanical stress on CMC attachment tabs.

Segmented swept surfaces on turbine nozzle sidewalls align with stiffening members to accommodate hot deflections and minimize stress concentrations.

A rotatable turbine casing aligns its inlet with incoming fluid flow to capture kinetic energy from any direction.

A variable area fan nozzle adjusts its opening to maximize airflow across the fan during engine startup.

A gearbox converts multiaxial ocean motions into unidirectional rotational motion for power transmission.

Centrifugal force rotates the lock plate projection away from the blade root, reducing parasitic loading and cooling air leakage paths.