Engine Fuctions TRIZ Cases

See how one hydraulic power unit supplies common pressurized fluid to main and bypass valves, reducing space, cost, and maintenance complexity.

Bidirectional wave motion drives opposite toothed rails and rail gears, converting float movement into continuous generator rotation.

An acoustic black hole assembly absorbs resonance in variable bleed valve cavities, reducing vibration and protecting compressor components.

A tangential spring retracts seal segments during low delta pressure, reducing rotor scrub and wear before inward sealing as pressure rises.

Plasma-sprayed rare earth silicate layers seal gas turbine CMC coatings against volatilization while removing the need for added glassy layers.

Targeted impingement cooling directs air between the CMC shroud wall and pins to manage thermal gradients and extend pin life.

Heat-exchanger vaporization and expansion-turbine recovery improve hydrogen engine efficiency while limiting carbon emissions.

This case links high-pressure shaft speed rating and engine-core proportions to higher-bypass operation without excessive vibration.

SAF-sensitive fuel routing drives gas-turbine actuators hydraulically or bypasses them to limit thermal degradation.

Angled impingement passageways diffuse cooling air across a ceramic matrix composite shroud to limit localized thermal gradients and degradation.

Field analytics and rotor overspeed distributions replace deterministic burst limits for turbine disks, supporting lighter, lower-cost designs.

Uneven post-shutdown cooling can bow a gas turbine rotor; targeted heating and fluid heat transfer support faster restart without seizing.

Segmented core and bypass flows address fan-diameter installation, weight, and thermal constraints while supporting propulsive efficiency.

An analysis module identifies the most advanced fatigue indicator and adjusts power transfer between turbomachine shafts to postpone maintenance.

A circumferential heat exchanger uses acoustic length and porosity considerations to attenuate noise while preserving heat transfer in an annular duct.

Cooling holes carry fluid through a turbine blade wall, balancing hot-gas heat removal with smooth airflow and aerodynamic performance.

Radial passages in a bypass TOBI system redirect HPC air to cool turbine components and use leakage flow productively.

Splitting accessory drive hardware between the inner cowl and hollow fairing helps limit outer-cowl thickness, drag, and added engine weight.

A cooled cooling air system uses a heat exchanger to cool compressor airflow before supplying turbine components for higher-temperature operation.

Conventional shaft alignment is slow and error-prone; paired rotating tools speed accurate gas turbine gearbox coupling.

High compressor pressure ratios can drive compressor-exit and exhaust temperatures upward; a heat exchanger cools turbine air to protect components.

Fuel supply selectively drives or bypasses gas turbine actuators according to SAF content, limiting thermal degradation and supporting reliable operation.

A cooling passage draws low-pressure air upstream of the compressor through a heat exchanger to cool accessories while limiting work loss.

A power plant drives a ventilator for ambient-air CO2 adsorption, then shares energy through an exchange path to release captured gas.

An internal plenum fans cooling airflow through rib-separated passages to cool the leading edge while supporting vane stiffness.

Integrating the starter reduction gear and freewheel into the casing reduces axial space and helps accommodate oil pumps or electric motors.

Separate fin groups and distribution structures route two airflows without crossing, improving cooling while limiting pressure loss.

A centered shaft joint and compressive tie shaft enable controlled spool separation to test gas turbine containment performance.

Electrically driven supply and scavenger pumps maintain bearing-compartment pressure and lubrication when spool speed falls during power transfer.

A cooling circuit directs coolant to stator vane braze joints, supporting separately additively manufactured subcomponents and reducing high-temperature joint failure risk.

A faster secondary controller manages hydrogen flow and ignition dynamics for stable turbine-engine combustion.

Bolted turbine models can distort strain measurements and lack continuity; a single-block runner supports hydraulic and mechanical testing.

A tapered acoustic black hole uses localized thickness or curvature to strengthen fatigue-prone tips while preserving flexural-wave attenuation.

Thermal expansion can shift turbine blade tip clearance; a flexible inner substrate and tension belt adjust the casing flowpath.

Separate turbine-generator and control modules improve maintenance access while routing combustion and cooling air through the station.

Bypass and recirculation conduits redirect engine fluid around the heat exchanger to stabilize temperature for downstream components.

A two-stage end-stop system combines hydraulic deceleration and spring-like extension to hold the buoy through large-wave crests while shortening the heave system.

Vents and air scoops purge fugitive fuel gas from an aircraft engine accessory box, reducing ignition and detonation risks.

Interconnected airfoil, platform, and rail passages use cooling air to film-cool the inner platform and reduce thermal stress.

Mass-flow feedback helps position compressor variable geometry elements more accurately, reducing conservative margins while preserving surge and stall avoidance.

Exhaust heat generates steam to preheat hydrogen fuel before combustion, while a turboexpander recovers shaft and electric power.

Carbon members accommodate differential thermal expansion in heat exchanger tubes, helping limit resonant behavior while preserving structural support.

Optimized diameter, length, and wall thickness position shaft critical speeds above operation while reducing bending-mode vibration in turbine engines.

Hot compressed air limits blade cooling and creates uneven temperatures; a vortex tube and biaxial fluidic jets improve surface coverage.

A carrier-mounted gear train routes motor torque to healthy bearing teeth, avoiding full replacement and reducing wind turbine downtime.

Uneven shaft cooling causes bowing and startup vibration; movable balance weights realign the center of gravity and shorten motoring time.

High-temperature compressor bleed air is cooled with lubrication oil in a shaft-mounted exchanger to extend seals and prevent oil leakage.

Rising compressor pressure and exit temperature are managed with a heat exchanger, shutoff valve, and propulsor to protect turbine components.

An inboard slider travels around the core casing to block bleed openings, divert airflow, and simplify gas turbine valve sealing.

Liquid hydrogen conditioning demands high power; an auxiliary combustor heats fuel to drive the pump, while bypass flow supports pressure and temperature control.