Engine Fuctions TRIZ Cases

A central hub trap with an annular air recovery channel filters foreign objects from the intake airflow.

Curved connection arrangement distributes loads across wind turbine nacelle support structure, reducing mechanical stress and material usage.

Segmented blade cavities with independent heaters resolve uneven heat distribution, improving deicing efficiency and extending component life.

Remote filling orifices and overflow evacuation conduits resolve access difficulties in dense interflow compartments while preventing lubricant leaks.

Controller distributes electrical power demand across multiple generators to reduce mechanical stress on gas turbine engine shafts and minimize degradation.

Segmented metallic carriers with axial stop pins reduce axial space requirements while maintaining structural integrity in gas turbine shrouds.

Star gear mechanism enables independent speed control between fan and low-pressure spool, resolving structural complexity trade-offs to enhance power density.

Annular sealing ferrule covers circumferential spaces between fixing lugs in a turbine ejection cone assembly.

Placing a ceramic insert on a mandrel before wrapping fiber layers maintains design geometry accuracy and eliminates post-processing steps that alter shape.

Asymmetric cooling port distribution reduces thermal stress on the platform, maintaining fatigue strength during high-temperature operation.

Segmented inserts extend cooling reach into the aft portion, resolving limited insertion depth.

A tang removal tool with a pushing member and keeper captures the helical insert driver tang during extraction.

A pressurization device uses a hydrodynamic transmission element to transfer torque from a main turbine output shaft to a fluid operating machine.

Segmented blade design uses compliant seals near hot gas path to minimize differential deformation forces and extend working life.

A coaxial cylindrical air guide rotates within the outlet shaft to minimize rotational velocity differences and reduce air friction.

Segmented shrouds direct cooling air around the engine to resolve bypass issues caused by muffler position changes.

Segmentation and inversion principles resolve low efficiency and high water volume requirements in existing storage systems.

Self-driven fan modules circulate air through a wind turbine hub to dissipate heat.

A monitoring method reconstructs fuel flow rate from valve position and density to detect hydro-mechanical unit degradation.

Turning unit rotates compressor components via reduction gearbox to prevent thermal bowing.

Axial expanders replace radial units in geared turbomachines, reducing construction volume and material costs while handling higher fluidic loads.

Segment linkage extracts the nut before bearing heating, eliminating parasitic thermal damage during assembly.

Segmented resonance chambers with localized perforations reduce low-frequency noise emissions while maintaining structural integrity of the gas turbine engine.

A cooling system controls bearing clearance by managing thermal expansion in direct drive wind turbines, preventing inner ring overheating.

A turbine blade platform features a localized depression near the trailing edge opening to direct cooling air for film cooling.

A metallic shield encloses the ceramic matrix composite rib inside a gas turbine airfoil cavity to block direct cooling air contact.

A turbine blade tip shroud features a trident-shaped cooling passage system that delivers coolant to the airfoil for convective heat transfer.

Schedule prediction module generates scheduled rate output using historical performance data and current system dynamics to adjust control signals ahead of time.

Integrating the abradable element with the acoustic panel eliminates aerodynamic disturbances from functional clearances.

Segmented composite casing manages centrifugal forces while reducing engine weight.

An electric turbocharger stator housing integrates an oil supply passage and nozzle to cool the shaft directly.

A differential sensing circuit uses board stiffeners and traces to detect high temperature exposure via voltage differentials.

Radial offset between hub and blade flanges reduces crimping moments, allowing smaller bearing diameters while maintaining structural strength.

An electromagnetic tag on the blade surface distinguishes ice from water using power thresholds, eliminating false alarms from indirect measurement techniques.

Bypass line diverts oxidant to combustor, resolving turbine speed constraints for efficient CO2 power plant startup.

A bell-mouth rotary main shaft connects directly to the hub, accommodating misalignment through local deformation.

Segmented heat shield radial tabs engage intermittent slots to maintain axial retention while reducing initial radial interference fit for easier assembly.

Air pressure sensors detect supersonic shockwaves within wind turbine blades to identify bypass lightning strokes.

A turbofan low-pressure shaft uses four strategically positioned bearings to constrain flexural deformation modes and maintain structural integrity.

A resilient washer in a deflectable engine mount provides biasing force to re-center the shaft, preventing disengagement under axial loads.

A recirculating heat pump turbine uses a turbocharger to compress working fluid for superheating.

An expansion valve reduces bleed air pressure and temperature in an auxiliary power unit.

An air mixing device combines compressed and bleed air to generate regulated anti-icing flow.

Segmented platform cooling circuit distributes fluid through feed and cooling cavities for efficient thermal management.

A gas turbine engine uses an inertial particle separator to remove fine particulate matter from cooling air, preventing blockage of narrow rotor passages.

A helical spring in the biasing assembly maintains a fixed gap between adjacent coaxial gears, preventing contact during variable speed operation.

Adjustable annular inserts position internal weights along the shaft axis to counteract first-order beam bending vibrations and whirl instability.

A geared turbofan engine decouples fan and turbine speeds using a star gear mechanism to achieve high power density.