Engine Fuctions TRIZ Cases

Variable threaded connections maintain spoke tension across thermal cycles, reducing axial engine length and mechanical fatigue.

Ultrasonic anemometer on a power kite measures apparent wind velocity.

Modifying the chord-wise pin location and spar cap orientation reduces vibration and noise caused by load-induced structural deviations.

Infrared thermography detects surface temperature changes to calculate intrinsic dissipated energy in wind turbine blade spars.

A wave power device uses a hollow air compression pipe to convert tidal flow into stored compressed air for generation.

Integrating a dry cooler into the nacelle contour eliminates on-site assembly errors by enabling pre-production testing of the cooling system.

Segmenting the inner heat shield eliminates material-to-material bonding, preventing fretting damage while maintaining effective thermal protection.

An insert directs cooling air through channels between pressure and suction side chambers to enhance internal heat transfer.

A flexible bladder on a rotating compressor tip uses centrifugal force to dispense de-icing fluid through calibrated orifices.

Axially compressible pressure bolts with disk springs maintain radial pretension on guide vanes while accommodating thermal expansion.

Segmented hinged tabs on a gas turbine panel restrict door opening and dissipate energy during overpressure events.

A steam turbine startup method applies controlled temperature transients to manage thermal expansion during initial heating phases.

Integrating a capacitor within a hollow compressor drum provides direct power to an electric machine without external transmission components.

An aircraft nacelle air inlet lip features an inwardly oriented beveled contact surface that integrates with the inner wall to eliminate assembly gaps.

Centralized nacelle pressure source drives cooling flow through outer heat exchangers, eliminating exhaust ducts and reducing noise.

Integral lattice structures increase surface area for mechanical interlocking, preventing ceramic coating spallation under extreme heat loads.

Computer vision algorithms analyze 3D fan models to determine blade orientation and rotational direction automatically.

A manual override mechanism adjusts a gas turbine starter air valve to intermediate positions for precise motoring speed control.

Segmenting the cooling channel into a separate groove and cover reduces wall thickness for better heat transfer while maintaining manufacturing reliability.

A day-ahead wind power prediction system uses k-means clustering and robust auxiliary classifier generative adversarial networks to generate labeled scenes.

Radial arm inclination reduces axial casing extension and bearing spacing, minimizing system mass while maintaining mechanical stability.

A LiDAR sensor assembly scans the gas turbine inlet volume to identify and track foreign object debris with high spatial precision.

Water injection into the bypass flow passage increases mass and velocity to augment thrust without increasing fuel consumption.

Segmented platform and aerofoil cooling chambers lower feed temperatures while minimizing aerodynamic losses.

A porous and malleable applicator tip delivers dye penetrant to gas turbine components.

Optimizing the gear reduction ratio to 3.0-4.0 balances fan speed against compressor stage pressure ratios for improved thrust-to-fuel efficiency.

Metallic carrier transfers aerodynamic loads from ceramic matrix composite turbine vanes to the engine case, minimizing leakage and chemical interaction.

Shield holes mix hot live steam with cooling flow to moderate rotor temperature and reduce thermal stress during system faults.

Dual parallel apertures in the connector segment rotational constraints to prevent platform rotation while maintaining compact size.

Multiple injection points deliver lubricating liquid into subsequent compression chambers, improving sealing and cooling efficiency at high pressures.

Segmented ceramic matrix composite blade outer air seal reduces thermal gradients and structural loading via carrier cavity impingement cooling.

Adjustable turbine blades align with marine currents to generate power without reservoirs, resolving structural stability issues from variable flow speeds.

A clutch mechanism disconnects the speed increaser from the compressor shaft during steady operation.

Direct mechanical coupling between a turboexpander and a rotating load eliminates electric machines, reducing conversion losses and system complexity.

Kidney-bowl suction wall passages reduce stress concentrations and thermal fatigue in gas turbine aerofoils by enhancing heat removal via dual vortices.

Cutouts in axial turbomachine casing flanges allow centering means to extend through the structure.

Bracket fuse mechanism with sacrificial notches breaks away under extreme loads to protect the gearbox structure.

A movable spraying member transitions between retracted and expanded positions within a gas turbine engine core flow path.

Flexible interior ribs with circumferential grooves allow hot exterior walls to expand, reducing thermal mechanical fatigue life in gas turbine engines.

Hafnium silicate and BMAS coatings resist CMAS attack, preventing spalling and delamination in gas turbine engine components.

Companion samples replicate rocket propellant aging to enable continuous service life tracking, eliminating costly and risky destructive testing procedures.

Redundant cooling channels protect metallic components from overheating when ceramic matrix composite sections fail, extending service intervals.

Sacrificial fasteners fracture to absorb excess loads, preventing engine mounting pad damage without adding weight.

Resilient biasing in the probe body ensures consistent contact pressure, enabling reliable defect detection in complex turbojet disc cavities.

Shape-memory alloy valve interrupts fluid flow to allow lighter fire-resistant components instead of heavy fireproof ones.

A braced cable bundling device rotates with the nacelle to absorb torsion, protecting the cable slack from mechanical wear and power losses.

A planetary gear system with a stationary carrier mount absorbs vibration to enhance turbomachine efficiency and fuel economy.

Rotational fluid flow enhances heat transfer at the leading edge, resolving insufficient thermal distribution in cold climates.

Frequency-dependent fiber composite edges create reflection minima in the 1 to 10 GHz range, eliminating spurious radar targets from wind farms.