Engine Fuctions TRIZ Cases

An epicyclic train reducer dynamically adjusts speed reduction ratios to limit starter maximum speed, reducing bowed rotor risk without increasing mass.

Bonding pre-inserted retainers avoids costly in situ casting, reducing assembly time while maintaining joint strength.

Segmented covers with integrated heat shields isolate bolted flange joints from high temperatures, maintaining tight clearances and reducing engine leakage.

A single mechanical coupling connects an electrical machine to a free turbine shaft via an accessory gearbox.

A dual oil circuit system with separate reservoirs and heat exchangers manages distinct operating temperatures for gas turbine engine components.

Curved bypass wall surfaces stabilize flow paths in centrifugal compressors, suppressing vortex generation and noise at inlet connection points.

Segmented parallel turbines with dynamic controllers handle flow deviations, preventing overload and pipe damage.

A steam turbine thrust control system dynamically adjusts high and intermediate pressure extraction valves to balance rotor forces.

A destructible tubular guide channels propellants along the axis of symmetry, absorbing detonation energy to reduce lateral loads on rocket engine components.

Varying cooling channel cross-sections reduces hydraulic resistance and improves bottom part heat transfer without increasing mass flow.

An asymmetric wedge seal adapts to thermal expansion and operational variations, maintaining a consistent sealing interface that prevents hot gas penetration.

Epoxy adhesive bonding eliminates mechanical fasteners, preserving structural integrity and reducing weight of composite gas turbine engine fan cases.

Segmented sealed bearing assemblies with sintered inlet headers reduce oil consumption and weight by localizing lubrication within a dedicated cavity.

Segmented fixture system positions turbine buckets using nested insertion grooves, reducing installation time and manufacturing costs.

Heat exchanger design integrates thermal management with acoustic attenuation to resolve noise and heat transfer trade-offs.

A conformal manifold delivers hot bleed air to heat the inlet lip, reducing weight and preserving engine efficiency.

A turbine vane fillet employs a baffle structure to redirect cooling gas from an impingement tube, resolving high stress without increasing coolant consumption.

Directional mounting clips accommodate thermal expansion in gas turbine exhaust diffusers, reducing stress on insulation components.

A single-piece composite blade root merges pitch and drag damper attachments, reducing rotor mass and aerodynamic drag.

Normalized wall thickness profile for gas turbine rotor blades improves internal heat transfer and mechanical load distribution.

Independent platform and airfoil circuits with a seal plate reduce pressure loss while maintaining structural integrity at high temperatures.

An oil flood retention tank with elevated inlet ports collects exhaust oil from turbomachinery assemblies.

Segmenting curing and bonding operations reduces expensive mould occupancy time while maintaining manufacturing precision.

A single lube pump supplies synthetic oil to rolling bearings, eliminating dual pump complexity and reducing weight.

Relocating the cooling passage outlet to the suction side reduces heat pickup and extends component lifespan.

Calculating flange displacement from open-state coordinates reduces calculation load and preparation time compared to finite element modeling.

A turbine steam system extracts water from combustion gases to generate steam for injection into the core air flow path.

Fluid transfer pipes pass through the planet carrier to dispense lubricant externally, reducing sleeve size and easing integration.

Multi-axis pivoting in a universal support fixture accommodates varying blade curvatures, eliminating custom fixture costs during rail transport.

Thin sheet forming defrosting channels in axial turbomachine splitter nozzles ensures homogeneous defrosting while reducing manufacturing costs.

Inclined crossover passages link internal airfoil cavities, managing pressure drop to prevent combustion product ingestion.

A linear actuator drives a carrier along a fixed track to deploy thrust reverser doors via linkages.

Specific airfoil dimensions align vibrational modes away from engine excitation frequencies, preventing resonant stress.

Submerged grooves eliminate protrusions that reduce structural strength, allowing retaining rings to secure cover plates without occupying space.

Segmented primary and secondary contacts in a wind turbine lightning transfer unit reduce wear from bouncing while ensuring reliable discharge of high currents.

A discrete damper spring biases a stator subassembly radially inward against an outer case to stabilize the vane array.

Segmented heat exchange manifold distributes thermal fluid through plenum extensions to reduce pressure loss in gas turbine engines.

A segmented vane assembly uses differential thermal expansion between inner and outer rings to maintain radial compression on the vanes.

A turbine vane assembly uses sliding interfaces between metallic spar segments and ceramic matrix composite vanes to accommodate thermal expansion differences.

An annular flange with a particle filter prevents obstruction of injection holes, ensuring reliable cooling air flow for ceramic matrix composite shrouds.

Segmented rail shield protects sealing surfaces from thermal stress while maintaining radial proximity to blade tips.

Merging lock-nuts with a split carbon seal ring reduces assembly volume and leakage in tight gas turbine engine spaces.

Segmented ceramic matrix composite platform inserts lock into secondary disk cavities, reducing disk stress by 20% while preventing gas infiltration.

Segmented impingement systems meter coolant flow through varying hole densities, reducing thermal resistance and bleed air extraction in gas turbine engines.

Sequential magnetic engagement of accumulator members transfers low-inertia motor drive to high-inertia loads, reducing system efficiency losses.

A gas turbine fan shaft uses a reduced sensor gap to detect forward movement before thrust bearing failure causes damage.

Segmented safety apparatus containing high-energy releases from tension stud failures avoids costly redesigns and extensive non-destructive testing protocols.

Internal shield divides housing volume to limit breach and leakage while maintaining design temperature limits.

Segmented bore baskets isolate cavities to match blade thermal expansion, resolving efficiency losses from uneven temperature distribution.