Engine Fuctions TRIZ Cases

An electric boost compressor draws air from the engine flowpath to maintain continuous, regulated ECS pressure across varying flight conditions.

Attachable multi-material fins improve gearbox labyrinth seal clearance control, reduce leakage, and simplify repair in hot aircraft oil systems.

Multiple platform cores separated by ribs improve turbine blade cooling flow, core stability, and durability under manufacturing constraints.

Porosity matched to abradable-layer hardness helps BOAS coatings resist rub damage, thermal attack, and CMAS infiltration.

A removable segmented duct wall lets the bypass heat exchanger be serviced without full engine duct disassembly, cutting maintenance time.

Adjustable balance weights on a circumferential spool track correct turbine imbalance through access ports, cutting vibration and wear.

Bayonet flange webs and recesses enable axial insertion plus rotation, improving force flow and torque transfer without extra screw connections.

Skewed stiffeners brace divider plates and act as radial fins, removing the outer frame to cut weight, drag, and airflow blockage.

A constant speed drive between the engine shaft and accessory gearbox keeps accessories near constant speed despite turbine speed variation.

Embedded abradable sensors track coating wear and blade rubs through electrical changes, improving true tip-clearance monitoring in turbines.

A float, linkage, and counterweight turn short wave cycles into continuous seawater pumping, improving ocean energy conversion beyond tidal limits.

A primary-secondary fan with a third stream balances higher thrust, airflow ratios, packaging, weight, and thermal management.

Selective clutching shifts excess low-spool power to the high spool or accessories, cutting idle fuel flow and thrust while preserving compressor stability.

Composite fan blades and a reduction gearbox enable larger fans with fewer blades, improving thrust efficiency without metal blade size limits.

Adaptive standby-exit timing switches between normal, accelerated, and rapid engine reactivation to limit damage while maintaining flight safety.

A clutchable transmission shifts power between turbine spools to drive aircraft accessories while lowering idle thrust, fuel flow, and compressor risk.

A third-stream fan layout uses split airflow, a movable flow blocker, and heat exchange to raise propulsive efficiency without oversized fan penalties.

Mechanical connectors transfer and absorb vertical and transverse loads between stacked rotor blade frames, reducing lashing and increasing shipment capacity.

Radar sensing tracks blade adjustment via shaft and cantilever-arm distance while also monitoring shaft vibration with less mechanical complexity.

Heated airflow inside the blade prevents ice buildup without external add-ons, reducing aerodynamic loss and de-icing energy use.

Cooling air from holes beside a metallic wall seal keeps CMC gas path seals below temperature limits and improves turbine durability.

A split fuel and electric machine controller corrects thrust errors faster in turbofan and turboprop engines, cutting fuel waste and wear.

Clutched spool-to-spool power transfer lets turbine engines support accessories or spool loading while reducing ground-idle fuel flow and thrust.

Selective clutch and transmission routing shifts spool power to sustain bleed-air accessories while lowering idle thrust and fuel flow.

Guided spacer assemblies limit blade flexion and blade-to-blade contact, enabling denser wind turbine blade transport and storage.

Restricting a nacelle bypass outlet boosts engine windmilling during fire shutdown, keeping the oil pump circulating oil as a heat sink.

By disabling heat extraction and running enclosure fans, this case dries condensed air in wind turbine units for faster restart.

Adding a second starter on the low-pressure shaft improves compressor operability, cuts start time, and reduces airflow demand.

A protrusion-and-recess support layout lets turbine parts move and rotate into place, reducing galling while keeping assembly stable.

A float in a water reservoir stores potential energy and drives a generator without pumped-storage terrain limits or high environmental impact.

A fan-shaft-driven electric machine powers an auxiliary pump to keep the reducer and bearings lubricated during startup and shutdown.

A blade tip timing sensor detects icing in TOA mode, then switches to higher-power heating to prevent tip ice, imbalance, and vibration.

Adjusting variable stator vane incidence before thrust crossover raises axial thrust, reducing HP rotor vibration and bearing deflection.

Cooling guide vanes and a channelled cooling ring cut hot-gas leakage while limiting seal thermal stress in rim-rotor turbines.

Transversely elongated impingement holes spread airflow across the airfoil leading edge while easing ceramic core molding.

A segmented tie shaft uses threaded release and shoulder engagement to separate tight-fit rotating structures without disturbing stacked couplings.

A nacelle panel link uses a free inner enclosure and local reinforcement to mount actuators in tight panel space without overstress.

High-pressure fuel and H2O2 jets enable rocket engine ignition and continuous detonation without catalyst beds or cryogenic storage.

Cooling nozzles in compressor struts inject airflow to limit rotor thermal bowing, cut restart delays, and reduce engine wear.

A soundproof cabin with intake and ventilation noise reduction helps turbine-driven fracturing pumps cut site noise while keeping compact high-power drive.

A torsional spring stores energy in normal operation, then drives an auxiliary pump during windmilling to keep turbine bearings and gearboxes lubricated.

Deep nutrient-rich water is pumped and warmed to ambient temperature, sustaining phytoplankton, CO2 uptake, and fishery growth.

Upstream vibration inhibition devices on intersecting duct vanes cut airflow-induced fatigue, prevent plate disintegration, and reduce duct servicing.

Angled deflector walls in the engine plenum capture and melt ice particles before they reach the core, limiting damage and aerodynamic loss.

Dynamic control adjusts bottoming-cycle heat, pressure, and flow to match core engine conditions and recover more shaft power.

Stacked plates, spacers, and fasteners secure turbomachine liner joints to spread loads, limit wear, and accommodate thermal expansion.

A semi-closed cryogenic fuel loop uses staged heat exchangers and a turboexpander to recover exhaust heat as shaft power while vaporizing fuel.

An axially adjustable inserted ring restores turbine packing seals in place, cutting downtime and outage cost without full ring removal.

Thermostatic valves and dual heat exchangers passively route oil and fuel to hold fuel temperature without heavy active controls.

Buffer air pressurizes discrete shroud seals in angled channels to maintain sealing under differential thermal expansion and reduce gas leakage.