Engine Fuctions TRIZ Cases

A sealed plug fills most of the stator vane platform core aperture to suppress recirculation, improve cooling flow, and protect structural integrity.

A selective clutch decouples or reconnects the low-pressure compressor and turbine to cut losses, vary power flow, and simplify disassembly.

A three-tank gravity cycle uses gas springs, braking, and a water turbine to generate electricity with less land use and no fossil fuel input.

Independent leading, primary, and secondary tip flag channels improve turbine blade tip cooling while limiting pressure drop and thermal stress.

A bypass flap and linked fluid control cut turbine engine pressure losses and thermal cycling by running cavity heat exchange only when needed.

A biasing member keeps turbocharger nozzle vane units in contact, limiting vibration-driven movement and preserving exhaust gas flow efficiency.

Closed-loop control keeps corrected inlet flow and rotor speed in range so aircraft waste heat can be converted into useful mechanical power.

A decoupling device transfers gearbox torque to the rotor bearing support while limiting vibration and reaction loads in compact wind turbine nacelles.

Pressure-loaded linear seal segments and spring preload help turbomachines limit air and gas leakage while accommodating thermal growth.

A heat-exchanger cooling air system lowers turbine cooling airflow temperature, enabling higher compressor exit temperatures without major weight growth.

Low-pressure compressor bleed cools hotter high-pressure air through a CCA heat exchanger, improving turbine blade cooling with less engine interference.

Controllable valves shift oil between air-oil and fuel-oil exchangers to match fuel properties, improving cooling and thermal efficiency.

Magnets and an absorbent arcuate tray capture excess yaw-bearing grease, limiting splatter, contamination, and maintenance risk.

Fuel-driven actuator control uses heat exchange and selective bypass to handle high-SAF fuel without raising thermal degradation risk.

Acoustic tuning in an annular-duct heat exchanger balances heat dissipation, pressure drop, and engine noise across flight conditions.

A tandem cold-side and hot-side bleed layout uses a heat exchanger to cool high-pressure air for turbine blade temperature control.

Separate nacelle and electrolysis container units enable hydrogen production while simplifying wind turbine transport, service, and reconfiguration.

Waste-heat and auxiliary tank heaters keep compressed hydrogen at stable delivery pressure and temperature without added fuel pumps.

A corrugated stiffening member expands cavity area at panel edges to cut acoustic losses while preserving structural support.

Exhaust heat is transferred to bleed air through a heat exchanger, driving a power turbine to add shaft power and improve gas turbine efficiency.

Single-sided CMC vane platforms bear on adjacent segments to simplify fabrication while improving load transfer under thermal and mechanical stress.

Controlled airflow to inner and outer cavity zones protects turbine discs while limiting radial clearance growth that hurts turbomachine performance.

Magnetic coupling lets a cross-flow turbine generate sensor power in water pipes without shaft seals, high pressure loss, or complex geometry.

An integrated retaining nut oil scoop redirects lubricant radially inward to bearings, improving under-race lubrication in tight aircraft engine spaces.

Water stored on separate tower floors limits wall pressure while enabling gravity-driven electricity generation for steadier renewable grid delivery.

A dedicated cooling-air stream and booster fan cool the condenser while limiting bypass-flow resistance that can reduce engine efficiency and thrust.

External tubing, a needle valve, and a smart gas monitor enable safe LEL sensor calibration in inaccessible gas turbine compartments.

A heat exchanger and controlled partial-admission turbine recover aircraft waste heat for mechanical loads while maintaining corrected flow and speed.

Environmental, health, and maintenance data guide adaptive gas turbine starting procedures, accounting for degradation to improve efficiency and reliability.

Fins in a heat-exchanger mixing chamber disrupt boundary-layer growth and promote turbulence to sustain heat transfer over longer conduits.

A convergent mixing chamber disrupts boundary layers in aircraft engine heat exchangers to sustain heat transfer and limit pressure drop.

Protrusions in a heat exchanger mixing chamber break boundary layers and boost aircraft engine thermal transfer without fully redesigning conduits.

Balancing slots and a discontinuous lower crown portion guide leakage flow parallel to the main flow, reducing hydrodynamic losses and mechanical loads.

An idle shaft-speed ratio above 6.05 and proportional oil flow help limit bearing and gear wear in a gas turbine engine.

An internal baffle separates oil volumes and redirects airflow, keeping air away from the pump outlet during zero- or negative-g flight.

A flexible sealing membrane redirects secondary flow toward movable cascades, avoiding inner-wall recesses that disrupt aerodynamics and acoustic-panel installation.

An air-injection exhaust bias adjusts fuel flow for stable gas turbine firing temperature as compressed air changes compressor conditions.

A parallel shut-off and non-return device supports pump-turbine startup, preventing reverse flow and vibration.

Motors and generators supplement fuel power in compressor and turbine sections to improve efficiency and reduce fuel consumption.

An aft electric machine transfers heat to incoming intake air, addressing packaging and thermal-management constraints in reverse-flow turbines.

Mixing chambers with wall-mounted protrusions disrupt boundary layers in aircraft-engine heat exchangers, sustaining heat transfer while limiting pressure drop.

Four-waveband radiation sensing identifies combustion loss and triggers fuel-valve shutdown before dangerous fuel accumulation.

A friction-fit damping element between the disk and platform suppresses airfoil vibration while allowing pitch changes without centrifugal loading.