Engine Fuctions TRIZ Cases

Exit guide vanes in a hydrogen turbine separator remove condensed water, recovering steam for injection to improve propulsive efficiency.

Segmented open-section composite support structure reduces thrust reverser mass and manufacturing costs without sacrificing mechanical strength.

Injection moulded chopped carbon fibre containment shell eliminates eddy current losses while lowering manufacturing costs compared to manual lay-up processes.

Vertical stacking of blade shell half parts via separator elements reduces overall transport height and handling costs for large wind turbine components.

A passive blade tip clearance control system manages the gap between turbine blades and the shroud ring using pressurized bleed air.

Thermal expansion of elastomeric pads seals tolerance gaps in swage joints, preventing relative motion and local deflection.

Positioning an annular exit ventilation nozzle aft of the bypass duct exit plane reduces drag on the bypass exhaust flow and lowers specific fuel consumption.

Distinct filler materials tune hollow fan blade stiffness and damping properties within internal channels, resolving vibration management challenges.

Segmenting the coupling with a flexible pivot absorbs irregular wave impacts, protecting fragile gearing from mechanical damage.

Segmenting diffusion barrier and corrosion-resistant layers resolves the trade-off between oxidation resistance and coating ductility in harsh environments.

Asymmetric casing elements inhibit vibratory modes to prevent contact-induced instability during reduced clearance operation.

Inclined nozzles direct liquid longitudinally along screw rotor grooves, expanding the heat transfer region and reducing compression power.

Segmented heat exchangers with dedicated control valves adjust intake air temperature to extend operating range at partial loads.

Radially movable blade outer airseal segments prevent excessive rub during rapid acceleration while maintaining optimal clearance during cruise conditions.

Geodesic flow housing cover creates a water reservoir below the impeller to prevent ice bridge formation in fuel cell blowers.

Horizontal conduits create a vertical heated air curtain to resolve temperature gradients and reduce energy losses from complex vertical manifolds.

A gear system mounted to a turbine exhaust case drives counter-rotating low pressure compressor and turbine rotors.

Internal cooling cavity distributes coolant throughout tip shoe mass to eliminate deformation from thermal gradients.

Compliant pins modify stiffness via localized features to compensate for manufacturing tolerances and operational twisting, reducing gear load.

Internal acoustic sensor arrays detect blade cracking by analyzing abnormal sound data patterns, preventing safety hazards from undetected structural damage.

A compact actuator assembly uses short shape memory alloy wires to drive precise movable part positioning with reduced power consumption.

Curved nozzle edge reduces hull clearance needs while improving lubrication supply and stress management.

An impingement plate with apertures directs cooling airflow to dissipate thermal energy, maintaining sealing integrity under extreme temperature conditions.

An integrated ejector valve assembly combines low and high pressure fluid controls into a single unit to regulate aircraft bleed air.

An operative head applies axial force to turbine blade bases while a support gantry positions the actuator vertically above the component.

Segmented air cavities with labyrinth seals reduce pressure gradients in counterrotating rotor blades, minimizing energy loss from airflow leakage.

Seal members isolate conduit sections for ultrasonic scanning, enabling accurate defect detection without extensive disassembly.

Intermediary trays capture oil spills from the gearbox to prevent environmental contamination and reduce cleaning time.

Tapered heat exchanger plates with uniform wave amplitude fins combat resonance while improving cooling effectiveness in gas turbine engines.

Pivotable thrust reverser vanes minimize radial thickness in the stowed position, reducing aerodynamic drag while maintaining effective airflow turning.

Tailoring the cold flow nozzle outlet area to theoretical isentropic expansion values eliminates shock waves and noise during cruising flight.

Movable control surfaces pivot on an inner cowl to vary the exhaust nozzle cross-sectional area, resolving complexity trade-offs in variable geometry designs.

Interlocking projections on the ring gear and casing constrain axial displacement during bearing failure, maintaining torque transmission.

Arcuate lacing bar clamps vane units through through-holes, resolving fit variability and improving damping characteristics.

Optical sensor measures sediment concentration in water turbines using a pressure-reducing device to lower flow velocity.

Plasma actuators maintain cooling air attachment on turbine blades, preventing jet lift-off and enhancing film cooling effectiveness.

A transfer bearing assembly channels pressurized oil through rotating shafts to lubricate planetary gear components.

A ceramic matrix composite gas turbine blade integrates a capture feature to mechanically restrain the platform portion from radial movement.

Porous honeycomb absorber and annular chambers dampen noise while reducing thermal stress and construction complexity in the exhaust cone.

Tuned vibration tabs in a honeycomb structure attenuate low frequencies without increasing panel mass or thickness.

An oil scoop rotates with the shaft to deliver lubricant radially outward, minimizing leakage through a controlled gap between end walls and duct.

Interconnected pressure and suction side passages transfer heat from adjacent turbine blade platforms using a single cooling medium flow path.

A steam diffuser mounts on a rigid hub fixed to a turbine frame, separating flow guidance from structural load bearing.

Double pinch criterion optimizes bleed extraction in feedwater heaters, resolving heat transfer limitations by establishing dual temperature constraints.

A turboshaft engine monitoring system detects freewheel slippage by measuring torque and rotational speed during start-up.

A slide bearing set diverts lubricant via a radial bearing transverse groove, preventing axial bearing dryout and ensuring reliable hydrodynamic operation.

A turbine blade projection directs cooling air along the surface, preventing flow separation and mixing loss in thin sections.

A perforated mid-turbine frame structure directs cooling air through internal channels to mitigate hot gas damage while minimizing aerodynamic resistance.

Segmented stationary vane fillets minimize combustor distance to block acoustic transmission and suppress combustion vibration.