Engine Fuctions TRIZ Cases

A separator piston and pressure intensifier turn unused storage tank hydrostatic pressure into compressed fluid for energy generation.

A pendulum mass enclosed within the rotor blade cuts vibration without the drag penalty of external dampers at higher flight speeds.

Temporary lifting elements preload the fastener, then spacers lock the gap to create a maintenance-free wind turbine tension connection.

A transfer gear on the epicyclic reduction gearbox drives accessories while shortening aircraft propulsion system axial length.

A retainer carries radial loads from an internal unbalancing weight, enabling accurate aircraft engine unbalance testing without hardware changes.

Sealing cavities in a planet gear plain bearing blocks air and oil movement, cutting rotation noise while keeping bearing mass low.

A star gear speed-change mechanism lets the turbofan fan run slower than the spool, improving thrust efficiency while reducing stress.

A defined gutter-to-gearbox volume ratio improves lubricant scavenging while limiting gearbox weight, footprint, and windage losses.

A spline-linked sun gear and second-stage planet carrier cut stress and improve torque transfer flexibility in two-stage wind turbine gearboxes.

A six o'clock auxiliary reservoir and pump keep turbine engine rotating components lubricated when primary oil pressure is lost.

Rotation and pressure sensing trigger backup oil flow to a geared turbine when main lubrication is inadequate, sustaining operation in extreme conditions.

A two-part nacelle liquid cooler uses bypass valve control to avoid over-cooling, high viscosity, clogging, and component damage.

Heat treatment after coating restores alloy depletion around airfoil cooling holes, reducing oxidation and extending turbine airfoil life.

Differently shaped recesses in a wind turbine gearbox bell spread vibration frequencies, damping structure-borne noise and limiting resonance.

A dipstick-mounted piston vents trapped air in an aircraft engine oil filler tube, preventing false level readings and easing oil replenishment.

A self-biased butterfly bleed valve increases startup bleed flow area in gas turbines without the size and weight penalties of poppet valves.

Multiple pressure-matched auxiliary tanks and turbines sustain generation without frequent pressure restoration while reusing excess electricity.

A scroll deaerator and flow splitter separate air from gearbox oil fast enough to keep tank dwell time under five seconds and limit foaming.

A two-part planet carrier cage uses axial brackets and fasteners to ease satellite assembly while preserving alignment and load transmission.

Alloy-coated journal bearing surfaces cut friction and wear in aircraft engine gearboxes, improving transmission efficiency without major bearing complexity.

Curved annular plates and full-length diffusion-bonded fins raise layer density in curved passages while improving heat transfer and pressure drop.

An internal rib channel stiffens the duct locally to cut thermal and vibration stresses while allowing thinner, lighter duct walls.

Selective gear engagement with brake and reverse motor control lets a turbine pump gearbox adapt to variable torque and pressure with lower maintenance.

Separate woven fiber sleeve duct sections are joined around sidewall openings to improve structural integrity while keeping complex aircraft duct shapes manufacturable.

Hydrophobic or lipophobic gutter surfaces speed oil evacuation in aircraft turbomachines, enabling quicker cooling and recycling.

A KOH-based core removal bath with corrosion inhibitor dissolves turbine blade ceramics faster while preventing airfoil etching and oxide formation.

Bond and top coatings plus heat treatment restore alloy depletion around airfoil cooling holes, improving oxidation resistance and service life.

Variable shaft thickness and bearing placement raise turbomachine critical speed to avoid first-order bending vibration at redline.

Partial rotor-bearing immersion in an integrated oil sump enables hydrodynamic lubrication without pumps or oil lines, cutting nacelle complexity.

Woven fiber sleeves formed on mandrels create joined duct sections that handle complex aircraft duct geometry while supporting acoustic and anti-icing features.

Angled oil delivery targets the tightest bearing clearance, displacing hot oil to improve load capacity while cutting power losses.

A reduced-clearance plenum routes lubricant from the support structure into the rotating shaft to stabilize bearing lubrication and damp speed-change loads.

Separate lubricant outlets target the gear mesh and out-of-mesh zones to cut windage losses while maintaining cooling and lubrication.

A clutch-coupled ultra low-speed motor rotates the high-pressure body after shutdown to limit bowed rotor thermal gradients without adding gearbox bulk.

An annular oil recovery channel shields ring gear fasteners from airflow, improving centrifuged oil capture and reducing gearbox power loss.

A two-piece annular pivot routes oil through axial and radial passages to cool reducer bearings, cut mass, and preserve load capacity.

Neural residual correction improves gas turbine inlet condition estimates during transients, enabling more accurate adaptive engine control.

A grooved bolt clip and annular chamfer keep fasteners from dislodging in blind flange assembly, avoiding costly disassembly.

Journal bearing clearance, oil temperature, and pressure are tuned to cut aircraft gearbox power loss under maximum take-off loads.

A secondary lubricant reservoir keeps turbine gearbox gears and bearings lubricated during windmilling or pressure loss without extra pumps.

Closed-loop ring gear actuation corrects reduction gearbox misalignment under load, improving alignment accuracy, efficiency, and fuel use.

Independent oil supply and discharge channels in hydrodynamic planet bearings cut power loss, improve oil evacuation, and shrink gearbox size.

Gravity-fed internal channels collect oil from the sun pinion and evacuate it away from recirculation, cutting gearbox ventilation losses and heating.

Internal flow guides and hollow passages turn engine conduit plumbing into a heat exchanger, cutting bay blockage, pressure loss, and cooler size.

Multiple engagement surfaces and indexing features hold engine structures in fixed spacing during transport, reducing movement and wear.

Quasi-steady-state averaging and residual checks help turbomachines detect noise, spontaneous deviations, and long-term damage earlier.

Solid-solid phase change material in the oil tank absorbs peak heat from turbine oil, lowering component temperatures without complex cooling.

By coupling accessories to the gear carrier, the fan drive transmits power efficiently while allowing fan and turbine sections to run at different speeds.

Interconnected planetary gears split and manage rotor power and speed, helping aircraft transition between vertical and horizontal flight.

An intermediate damping module applies force at the blade shear centre to attenuate edgewise vibration in modular wind turbine blades.