Engine Fuctions TRIZ Cases

Differential thread tie bolts eliminate axial load bearing surfaces to reduce assembly torque in gas turbine engines.

Cooling air shrinks a movable clearance control ring, reducing system weight and improving fuel consumption.

Segmented cooling air lines attach to gas turbine manholes, maintaining compressor flow stability while enabling CO emission reduction.

Angled trailing edge slots minimize flow separation and pressure loss while enhancing convective heat transfer in gas turbine airfoils.

A vane arc segment uses a metallic baffle secured to a support platform to limit rotation of the spar pin mount.

Segmented tension turbine blades attached to a peripheral rim reduce structural stress while increasing visual deterrence for birds.

Segmented framing channel with varying cross sections reduces cooling fluid flow rate to prevent core unzipping during casting.

A rib and tip baffle system creates a segmented plenum to laterally constrain cooling air flow along the gas turbine engine airfoil.

Single 3D sensors track animal trajectories to resolve the trade-off between measurement precision and device complexity.

Face-to-face modular pressure vessels reduce manufacturing complexity while increasing stability for underwater pumped storage.

Relocating the clutch system below the rotation axis reduces axial bulk and improves maintenance accessibility for turbo-alternator shafts.

A spring-loaded tip bolster clamp maintains consistent force on wind turbine blades, preventing slippage and collision risks in curved railroad sections.

Alternating oxygen-to-hydrogen mass mixing ratios in a rocket propulsion system prevents excessive thermal loading while maintaining high specific impulse.

Electric machines accelerate turbine shafts through critical speeds, eliminating resonance damage without adding mechanical damping weight.

Vent holes enable passive gas escape and active purging to prevent fugitive fuel accumulation and detonation risks.

A heat exchanger in the tertiary flow vein cools turbomachine oil using a divergent upstream section.

Surface hardening treatment on the bolt male screw improves fatigue resistance against repetitive stress without increasing manufacturing complexity.

Radial nozzles eject fluid jets to energize the boundary layer, reducing flow distortion and pressure loss at engine fans.

A steam turbine exhaust chamber uses a radial protruding portion to deflect vertical vortices away from the diffuser flow passage.

Viscous damper system reduces vibrational inputs transmitted from the gear train to the static structure by creating a fluid damping chamber.

Segmented ceramic cores create distinct internal cavities that deliver cooling fluid to high-thermal-load regions, resolving uneven heat distribution.

A nozzle with a movable part directs lubricant into the turbo machine chamber.

A convertible Wirtz pump uses collapsible fins and a swivel mount to rotate flexible tubing.

A heat barrier shields the rotor disk from direct coolant contact.

An integrated panel merges distribution ducts and impingement chambers to reduce pressure drops and minimize air leakages in turbine casings.

Selective cooling via impingement plates and baffles reduces thermal fatigue on high-exposure vanes without increasing total fluid consumption.

A turbine shroud ring retention system uses a support ring and alignment pin to maintain concentric positioning.

Longitudinal vortex generators enhance convective heat transfer in rocket combustion chambers.

Circumferential mounting apertures in a tie-rod nut flange distribute loads to prevent tilting and fluid leakage under bending forces.

A controller estimates air compressor rotational speed using torque command history to calculate precise control values.

L-shaped sealing members bridge segmented crown and deflector rings to stop hot gas leakage without thickening the structure.

Insulating elements separate heated generator air from cold housing walls, preventing condensation corrosion that damages underwater turbine reliability.

Horizontally extending ribs define radially spaced internal cooling channels that alleviate local thermal stress loads near the trailing edge.

Telescopic cylinder assemblies rotate nacelle components via pin engagement, reducing structural weight while maintaining installation stability.

Gaseous fuel flows through a thermal management system to transfer heat from lubricant and hydraulic subsystems.

A turbine cooling circuit routes fluid through a central tie bolt to deliver air to second-stage blades.

A flow union member routes utility working fluid in a circumferential path around an internal passage to merge separate streams.

Aircraft engine flow channel valve incorporates a friction damping system that absorbs vibrations, extending service life against fatigue damage.

A control system derives coherence and phase differences between combustor outputs to detect impending lean blowout events.

Integrating electroformed fluid channels into guide vane airfoils reduces fan air drag and manufacturing complexity while maintaining efficient oil cooling.

Tensioning means apply controlled force to holding means, preventing hub movement and paint damage during transport.

A bleed air turbo extracts work from engine bleed air to drive the accessory gearbox and augment the engine drive shaft.

Segmented plenum passage directs cooling air through embedded ribs to manage temperature gradients while preserving downstream flow volume.

Segmenting the bearing arrangement into forward and rearward units mounted on an intermediate case controls shaft slope by minimizing off-axis displacement.

Silicon-coated aluminum powder mixed with phosphate binder forms a stable anti-corrosion layer without toxic chromium(VI) ions.

A flexible container collapses for compact transport and expands to hold liquids beneath wind turbine equipment.

A blade outer air seal uses a carrier with inward-facing dovetail hooks to support ceramic segments.

Centrifugal force drives free-floating inserts against shroud surfaces, maintaining consistent contact load across varying rotational speeds.

A cross-stream heat exchanger system uses a flow metering device to control airflow between air streams in a gas turbine engine.