Engine Fuctions TRIZ Cases

Self-driven refrigerant pumps cool operating liquid in wave power systems, preventing overheating during power outages.

Internal radial screw access eliminates external covers, reducing aircraft nacelle mass.

A supercritical CO2 bottoming cycle recovers thermal energy from exhaust streams using dedicated recuperators to preheat core airflow.

Movable spoilers on the fan cowl redirect bypass airflow near the aft edge, reducing flow separation and pressure losses during reverse thrust operations.

An epicyclic gear train drives two fans at different rotational speeds, resolving blade tip speed control difficulties while maintaining structural simplicity.

Segmented deep cavity center plugs dissipate low-frequency noise below 800 Hz while maintaining structural integrity.

Radial spokes link the inner case to hollow struts, reducing weight while maintaining structural strength.

A pivot-mounted holding element blocks turbine blades during extraction, preventing falls and enabling single-operator maintenance.

Decoupling the low pressure turbine section speed from the fan enables a compact design with high bypass ratios, reducing engine weight and fuel burn.

An aft-mounted epicyclic gearbox decouples fan and turbine rotational speeds, resolving the trade-off between propulsive efficiency and device complexity.

Inclined spray nozzles inject water counter to rotor rotation, reducing spray consumption and blade erosion during low load operations.

Auxetic stress reducing structures in turbine blade roots generate compressive forces that minimize tensile principal stresses at fillets.

Segmenting the airfoil from the platform simplifies manufacturing of complex ceramic matrix composite turbine blades while maintaining structural integrity.

Nickel-chromium coatings on movable ring teeth mitigate fretting wear from axial retaining hooks, extending rotor component lifespan.

An unbalanced motor applies counter-vibration to a gas turbine exhaust duct to cancel low frequency sound.

A shoulder bolt and spacer assembly connects gas turbine flanges to maintain structural integrity under extreme operational loads.

Radial partitions divide the distributor wheel into sub-cavities, enabling dynamic overflow control that adapts lubricant pressure to varying operational needs.

Continuous detonation waves rotate the axial drive shaft to generate electricity, reducing land use and pollution from conventional power plants.

A geared turbofan engine design featuring a scalable fan-to-compressor diameter ratio exceeding 4.5 and optimized gear reduction.

Curved axial end portion of turbine sealing member reduces friction and wear on casing rails by distributing contact stress, enabling repairable assembly.

A flow rectifier converts bi-directional hydraulic fluid from an articulated barge into unidirectional flow for a rotary-vane pump.

Geometric interlocking features replace ultrasonic welding to stabilize oscillation position and reduce production costs.

Shape memory alloy fire shield elements in aircraft engine oil coolers automatically close airflow passages to protect heat transfer matrices from fire damage.

Adjusting the minor span between rearward bearings relative to turbine length shifts resonance frequencies away from operating ranges.

Oblique gears and free-wheels drive the aircraft lubrication pump in one direction, ensuring continuous oil flow during windmilling.

Detachable root frame interfaces enable seamless mode transitions, reducing handling damage risks during wind turbine blade logistics.

Unpressurized diaphragm chamber isolates fluid while delivering cooling air, reducing diverted airflow and enhancing gas turbine efficiency.

Bypassing the catalyst bed after ignition reduces system mass and volume while enabling reliable detonation of liquid hydrogen peroxide with fuel.

A modular wind turbine support structure uses shared ballast and articulated connections to maintain verticality across multiple units.

Foil gas bearings enable oil-free direct drive operation, removing gearbox complexity and preventing process gas contamination.

Injecting oxidizer and coolant into the turboshaft gas path increases power output by 20-30% without adding engine weight.

Segmented flow diverters redirect cooling fluid into platform cavities to improve heat management while managing device complexity in gas turbine vanes.

Variable ratio yttrium and magnesium oxide inhibitors form refractory compounds to reduce ash deposition while maintaining flame temperature.

An evacuation valve opens a diverted airflow pathway to vent hot exhaust gas away from the heat exchanger during shutdown, preventing temperature damage.

Nested evaporator and condenser modules extract heat energy and water vapor from combustion products to recycle steam into the core.

A control system calculates a bias to adjust oxidant temperature entering the compressor.

A variable guide vane modulates fluid flow into a heat exchanger positioned within a second vane to enable adaptive thermal management.

A gravity energy storage system uses massive concrete weights suspended by links to store and release electrical power through vertical movement.

A turbine blade trailing edge cooling circuit recovers coolant for reuse across multiple airfoil sections.

Detection logic evaluates input signals to monitor solid state semiconductor device conductivity in real time.

Segmented bracket design with arcuate flanges and rail-slot interfaces minimizes tangential load transmission to bolts, reducing breakage risk.

A variable area nozzle assembly uses a translating ejector sleeve to axially adjust the exhaust passage for gas turbine engines.

Opposing beams in the journal bearing pin maintain gear alignment under load, resolving misalignment issues in fan drive gear systems.

Segmented baffle pockets capture surplus oil while slots allow drainage, reducing gear churning windage and friction heat.

Dual modulation valves control airflow through a double wall compressor casing cavity to manage thermal distribution.

Rub strips generate counteracting torques to control deceleration rates, reducing structural loads during fan blade out events.

Intermediary guides stabilize thrust reversers during installation, eliminating crane swaying and reducing safety risks.

Planetary gears separate fan and turbine speeds, resolving compressibility losses while maintaining high thrust output.

A processor detects current amplitude variations to adjust excitation frequency and maintain resonant operation of oscillation blade devices.