Engine Fuctions TRIZ Cases

Heat exchangers gasify liquid hydrogen for combustion or fuel-cell use, improving turbine fuel efficiency while enabling water recovery.

A removable crank gear inserts through a gearbox port to rotate a gas turbine rotor without permanent gearbox features, cutting weight and cost.

Heat exchangers pre-cool turbine cooling air, cutting component stress so turbofan engines can run at higher temperatures while holding thrust.

Pivoting support arms hold thrust reverser sections at stable angular positions during engine core removal and towing to prevent seal damage.

Controlled spoke sliding triggered by destabilizers limits fan blade-off loads and vibration while preserving bearing support fatigue life.

A fixed-open thermal reservoir balances footprint, resource state control, and operating flexibility to improve PTES round-trip efficiency.

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

Spaced outer hole regions and a curved connection passage help turbine airfoils maintain coolant momentum and prevent flow separation.

Steam recovered from turbine exhaust preheats hydrogen fuel and drives a turboexpander, improving aircraft engine efficiency and fuel use.

Curved, segmented cooling holes improve film cooling in turbine airfoils by preserving coolant momentum and limiting flow separation.

Integrated scoops, a sump, and strut flow channels scavenge lubricating fluid in tight fan frame space while reducing diffusion loss and weight.

Specific feather seal tabs and fillets block rotor secondary air leakage while avoiding blade-removal interference and excess heat-up.

Cracked ammonia and supplemental hydrogen are metered through switchable valves to improve turbine startup and steady-state combustion.

Multiple shafts and generators split CO2 turbine-compressor speeds, enabling feasible aircraft power output and staged pressure ratios.

A removable blade attachment forms an air channel ahead of the leading edge to divert airflow and reduce parked wind turbine vibrations.

Inlet precooling and a movable cowl-plug nozzle let turbine propulsion avoid overheating and over-expansion drag across high-speed flight.

Staggered shaft holes mix hot seal leakage with upstream airflow to reduce thermal asymmetry and rotor operating stress.

A separate closure initiator helps a thrust reverser overcome aerodynamic jamming and chattering, enabling easier closing with smaller actuators.

A two-piece resilient masking boot exposes target turbine areas for grit blasting while reducing attachment damage and removal difficulty.

Precomputed multi-dimensional maps replace iterative bleed-off valve tuning, cutting gas turbine maintenance time and fuel use.

A bypass circuit and mixing valve tailor lubricant temperature for the electric machine, geartrain, and propulsion components while reducing space and material degradation.

Multiple dampers integrated into an engine thrust link broaden vibration coverage across LPT and HPT ranges to prevent resonant damage.

Exhaust heat drives refrigeration liquid to pre-cool turbine inlet gas, helping maintain mass flow and power in high ambient temperatures.

A split front housing and multi-orientation gear train raise aircraft accessory power transfer while allowing flexible generator placement.

Relocating the fan aft of the core with geared drive shafts and bearings eases large-fan packaging and improves thrust in gas turbines.

Staggered shaft holes mix hot seal leakage with native airflow to reduce turbine rotor thermal asymmetry and stress.

Using blade-angle and rotor-position sensors, this case detects wind turbine rotor mass imbalance from stop positions without extra equipment.

A pendulum lever linkage converts low rotor torque into usable generator drive, improving quiet residential wind power at low wind speeds.

Centrifugal traps built into a gas turbine diffuser capture particles before they block cooling features and damage hot-section components.

An integrated gearbox cradle pivots on engine brackets while an adjustable link sets belt tension with fewer mounts and lower stack-up error.

Raised pedestals and destabilizers trigger spoke slip above an FBO threshold, limiting bearing loads and vibration while preserving fatigue life.

A gearbox lets the low-pressure turbine run faster than the fan, improving thrust and efficiency while managing turbine stress and drag.

Parallel bleed ports and an eductor nozzle remove debris from the engine core flowpath while supporting stable operation and cooling.

Phase-change fluid circulation driven by centrifugal force cools turbine blades efficiently while reducing thermal stress, corrosion, and wick complexity.

Transverse bolts with axial preload tabs press spar end faces together, enabling transportable segmented blades with strong, precise assembly.

Transverse bolts and fastening tabs join the blade root to the bearing ring, cutting bearing ring height while maintaining load capacity.

Selective use of compressor bleed air and bypass air improves gas turbine oil cooling while cutting heat exchanger size, weight, and aerodynamic losses.

A turbomachine uses working-fluid heat to drive thermal transport flow, cutting electrical pump losses, weight, and waste heat.

A breakable joining portion preserves blade geometry during manufacture while isolating thermomechanical stress and maintaining cooling airflow.

Offsetting the tip shroud knife edge from mid-chord shifts blade modal response outside the operating range to reduce flutter and fatigue.

A multilayer BOAS coating uses an EBC and a porous abradable layer to resist CMAS attack while preserving blade tip clearance control.

Cooled compressor bleed air lowers turbine and exhaust temperatures, allowing higher pressure ratios with improved thrust and efficiency.

Separate seal base and fin materials improve labyrinth clearance control, reduce oil leakage, and simplify fin repair in aircraft gearboxes.

Radial struts reinforce the fan case-core housing connection, enabling longer low-pressure compressors while acoustic guide vanes cut noise.

Varying parietal and central channel heights improves airflow uniformity and heat exchange while limiting pressure loss and thrust reduction.

An eductor-driven bleed layout uses parallel core air paths to clear debris, cool components, and maintain turbine engine stability.

A tuned fan blade and outlet guide vane spacing range reduces gas turbine noise while maintaining propulsive efficiency and structural durability.

Synthetic jet actuators sustain airfoil flutter at subcritical wind speeds, enabling simpler low-wind energy harvesting and rapid flight control.

Choked throttle points let fuel and oxidant flow at sonic speed, stabilizing rocket thrust control while keeping mixture ratio constant.

Multiple rotating discs and a balanced transmission raise generator speed for dam-free hydro power with lower ecological disruption.