Turbine/Propulsion Engine Cooling TRIZ Cases

See how a vortex tube separates bleed air into hot and cold flows to boost thermoelectric power

See how multiple intercoolers and supercritical refrigerant compound cycles improve part load e

See how a vapour compression system raises ancillary waste heat temperature to enable transfer

See how a vortex tube separates bleed air into hot and cold flows to enhance thermoelectric gen

See how integrating an air-cycle machine into the generator housing enables compact, shaft-driv

See how a turbine-generator cooling assembly reduces ambient air from 1800°F to 100°F–300°F whi

See how phase change materials absorb heat from high-power directed energy systems in aircraft

See how an external pod gas turbine integrates power generation and phase-change thermal condit

See how a variable cross-sectional area adjustment device optimizes cooling air flow to aircraf

See how a pod-mounted gas turbine and phase change material thermal system enable independent p

A heat exchanger plus vortex cooler conditions compressor air for self-cleaning filters when warm climates limit air-to-air cooling.

A gas-turbine pod uses bleed air, refrigerant cooling, and phase-change storage to power and cool aircraft payloads across flight conditions.

Cooling inlet air below dew point and reheating it with energy recovery boosts turbine output while preventing filter caking and retrofit downtime.

Liquid coolant pipes and conductive potting move heat from stator windings to cut resistance and preserve electric machine life.

Dual airflow buffer cavities and pressurized cooling air protect an embedded gas turbine electrical machine from extreme heat while preserving service access.

Flowpath air is routed through internal machine passages to improve heat dissipation and avoid startup surge in turbine engine powerplants.

Engine intake air is routed through electric machine passages to improve cooling without adding a separate motor cooling circuit.

Overlapping main lobes with varied side-lobe shapes help separate target returns from clutter and reduce false recognition in radar detection.

Dual heat exchangers cool aircraft power electronics during startup without bypass air, then switch to air cooling once engine airflow is available.

Dual heat exchangers and coolant flow keep aircraft power electronics cool during engine start and flight without relying on fuel cooling.

A stator tube confines cooling fluid to the stator and bearings, improving heat removal while avoiding rotor contact and excess loop complexity.

Monolithic annular supply and return conduits cut engine-bay blockage and pressure loss while improving gas turbine heat rejection.

Pressurized dual airflow paths and buffer cavities cool an embedded electrical machine and limit post-shutdown heat soakback in gas turbine engines.

Upstream compressor air is boost-compressed and heat-exchanged for turbine cooling while a dual-speed starter generator improves operability.

Using high- and low-pressure bleed air, a turbine generator stabilizes aircraft ECS airflow and pressure while supplying onboard power.

Coolant passages built into outlet guide vanes capture exhaust heat for reuse while supporting electrical machine cooling in gas turbines.

An electric circulation pump heats and moves oil in shared aircraft lubrication circuits, preventing freezing while cutting hydraulic weight and bulk.

Combined coolant and electrical routing cools generator connections in hot turbine sections while reducing size, weight, and maintenance disruption.

An extruded annular heat exchanger uses a partial closure in defrosting ducts to limit oil-circuit overpressure when the matrix freezes.

Inert gas injection stabilizes foil bearing lubrication in sCO2 pumps, reducing vibration and blocking liquid CO2 entry.

Cold reference air cools the diaphragm and sensitive regulator elements while maintaining hot air flow control in severe thermal environments.

Separate lubrication and control pressure paths help a wet clutch engage predictably while reducing heat, wear, and debris buildup.

A radially outward oil tank with a thermal break mount cuts heat transfer from the engine core while preserving compact nacelle packaging.

Parallel plates, arcuate manifolds, and external fins improve gas turbine heat transfer while stabilizing flow and pressure.

A nickel body with sacrificial-filled cooling passages forms a joint-free heat exchanger that withstands high temperature and pressure.

A dual-loop oil circuit uses valve flow splitting and intermediate temperature control to overcome long-pipe delay in turbomachine lubrication.

Diffusion-bonded curved fins let a conformal annular heat exchanger add more layers without separation, cutting weight and pressure drop.

Semi-spherical datum features on a gas turbine baffle create stable reference points, reducing dimensional errors, re-work, and scrap.

An actuator housing and shell gap transfer heat from hot engine oil to fuel, improving thermal efficiency without adding a separate exchanger.

A regulated generator voltage lets the electromagnetic air valve hold set tool speed under load and drop safely to minimum speed on failure.

Independent annular oil circuits improve lubrication and cooling in aircraft turbine reduction gears while limiting oil recirculation and vibration.

A dual-circuit lubricant layout routes scavenged oil through inlet guide vanes to keep journal bearings fed during in-flight windmilling.

A divided-outlet non-return valve redirects large liquid oil overflow away from the gearbox, preventing bearing overheating and overfilling.

A spring-loaded adjustable damper lets a gas turbine heat exchanger move with friction damping to cut thermal stress and vibration loads.

Embedding a heat transfer device in the power gearbox casing improves oil thermal management while freeing bypass-duct space.

Embedded heat-transfer structures in the power gearbox casing use engine airflow to improve thermal control without bulky external exchangers.

Relocating the oil tank near the turbine shortens feed lines and cuts nacelle bulk while thermal breaks limit heat transfer to the oil.

Independent annular oil circuits and guided flow paths improve reduction gear lubrication, cooling, and oil evacuation in aircraft turbine engines.

A dual-circuit lubricant layout keeps journal bearings fed during windmilling, protecting the power gearbox when spool speed is too low.

A fuel-air heat exchanger cools pneumatic control air and heats servo fuel upstream, cutting head losses and removing the servo fuel heater.

Dedicated lubrication channels and manifolds cool the clutch pack, clear debris, and maintain reliable torque transfer across wide speed ranges.

Cooling air is routed through the bushing and hollow frame structure to limit fastener creep while improving bearing load distribution.

Hollow passages and internal flow guides turn engine piping into a heat exchanger, improving heat rejection while reducing bay blockage and pressure loss.

A variable valve blends high- and low-pressure compressor air to smooth buffer pressure changes and reduce engine component wear.

Two semi-spherical datum features hold a gas turbine baffle in a fixed position, improving drilling accuracy and reducing dimensional rework.

A regulated generator supply lets the microcontroller hold set speed under load and drop the air tool to a safe minimum on power failure.

Multi-chamber platform cooling with pin fins, pedestals, and trip strips improves convective heat transfer and reduces turbine blade thermal fatigue.

Co-mingled spiral or helical channels pre-cool engine cooling air to improve heat transfer while minimizing pressure loss.

A direct communication passage replaces the turndown extension to cut pressure loss while preserving blade strength and cooling near the gas path.

A floating valve member creates an annular minimum flow gap to keep turbine case cooling active despite wear and radial clearance changes.

Angularly offset enclosure bars let curved heat exchanger segments join without voids, reducing pressure drop and welding-related defects.

This compressor assembly uses overlapping bleed cavities and stage-specific scoops to manage flow rates without enlarging the engine.