Engine Fuctions TRIZ Cases

Radial webs and recesses create bayonet kinematics for gas turbine rotor clamping, reducing axial length and local screw connections.

An auxiliary combustor heats hydrogen fuel while a fuel turbine powers the pump, controlling pressure and temperature for combustion.

Segmented nozzle panels and elastomeric inter-panel members vary the outlet area to improve propulsion efficiency across operating conditions.

A leading-edge passage, fanning branch passages, and rib-separated plenum distribute cooling air while supporting vane stiffness.

Periodic actuator-fluid pressure fluctuations dislodge contaminants around piston rings, helping maintain precise bleed-valve operation in gas turbine engines.

Solenoid valves regulate parallel micro-turbines and pressure to stabilize electricity generation across varying domestic water flow.

Axial and radial passages with impingement holes improve vane heat transfer while limiting cooling flow and pressure-driven bulging.

Tuned inertial elements damp floating seal resonance in gas turbines, reducing leakage while preserving rotor tracking and tight clearances.

During taxiing and idling, switching valves route fan-stream or compressor-bleed gas through a boost compressor to support heat rejection.

Integrated nacelle or tower electrolysis avoids long cable runs and complex conversion stages, reducing power loss and capital cost.

Air pressure and spring bias move seals radially inward against the blade track segment, supporting high-temperature gas sealing.

Temperature, pressure, and flowrate monitoring in the heat exchange fluid flags gas turbine airflow faults and supports cooling reconfiguration.

See how primary and secondary fans create a third airflow stream to improve propulsive efficiency while addressing fan size, weight, and packaging constraints.

Staged 3D simulations test repair blend profiles on damaged IBRs against aerodynamic, structural, serviceable, and deterministic criteria.

Monitor pump speed and motor frequency to detect hydraulic shock without fluid-contact sensors, reducing false positives.

Exhaust heat recovery heats cryogenic fuel while reducing mechanical energy use and turbomachine mass and dimensions.

A clutch selectively links independent gearbox power paths to adapt accessory power transfer across flight phases and reduce component wear.

Boundary layer separation at gas turbine heat exchanger inlets and outlets is reduced with interior dimples that lower pressure loss.

A buried depressurizing reservoir and deformable pressurizing reservoir use water-column pressure to increase storage capacity and reliability.

Cooling compressor airflow before it reaches critical components supports higher engine temperatures while limiting cooling-system size and weight.

A recirculation line sends excess fuel through cooling while a heat exchanger rejects engine thermal loads, reducing added interfaces.

Removable acoustic closure elements seal panel cavities while preserving sound attenuation.

Removable deflectors disturb spanwise airflow, promote turbulence, and decorrelate vortex shedding during parked or idling operation.

This case uses flanged sleeves to mount bearings and seals, reducing shaft machining, damage risks, and maintenance difficulty.

This case uses forward and aft bearings around the low-pressure compressor to distribute loads and stabilize geared spool rotation.

This turbine blade case uses smaller suction-side and larger pressure-side radii to limit vortices and aerodynamic losses.

An annular casing and jaw clutch use an oil film to damp vibrations, absorb stresses, and preserve gear-train torque transmission.

A split annular cavity and diffuser guide cooling air through the turbine disc bore to limit flame stabilization.

A pressure strip and zoned heating cure wear strips on gas turbine blades while limiting adhesive spew and blade damage.

This case uses slip joints, flanges, and channels to route connection means through a wind turbine tower without drilling.

An adjustable inserted ring restores turbine packing seals incrementally, avoiding full component removal during refurbishment.

Monitor compressor pressure ratio and spool speed during acceleration and deceleration to detect slow bleed-off valve response early.

A multi-arm linkage reduces reverser-flap mechanism size while preserving coordinated movement and improving nacelle aerodynamics.

A ventilation ring places openings into adjacent wall bases, enabling support-free additive manufacturing and easier depowdering.

A shared central hot-air path and lateral cold-air paths improve cooling while fitting the exchanger into the pylon.

This turbine engine condenses exhaust water, evaporates it into steam, and injects it upstream to boost power with hydrogen fuel.

Single-sided CMC vane platforms simplify fabrication while managing interlaminar stress.

A variable-width inserted ring fits a packing segment groove, enabling seal refurbishment without removing the full assembly.

A portable test device controls the pump and valve to diagnose wind turbine lubrication units on-site without disassembly.

This case uses cryogenic fuel as a heat sink to increase temperature difference and improve bottoming-cycle heat recovery.

Angled impingement jets target cast chevrons inside the turbine trailing edge, increasing turbulence and heat transfer.

A bolt and two-wrench kit pulls inlet guide vane segment pins through tight access, avoiding rotor removal during maintenance.

This case uses a condenser, evaporator, and superheater to recycle exhaust heat into steam injection for higher turbine power.

This vane arc segment uses an integrated pin fairing to limit leakage, guide cooling air, and support CMC airfoil durability.

This case uses internal cooling conduits and shaped holes to improve turbine blade cooling while preserving aerodynamic efficiency.

Radial and axial dampers stabilize turbomachine seal gaps, reducing vibration-induced contact, wear, and lubricant leakage.

A multi-spool gas turbine selectively engages the boost spool for cruise OPR while managing speed and hot-day thermal limits.

This case uses engine-power rules and electronically controlled valves to keep aircraft bleed-air flow below an over-extraction threshold.

Compare PMV pressure across normal and modified fuel flow to detect AC Nozzle calibration loss and protect turbine durability.

A swirling separator uses centrifugal force to remove particulates before they obstruct turbine cooling components.