Engine Fuctions TRIZ Cases

A pin assembly with a spring housing and boot transfers force to align turbine airfoil vanes.

A drive shaft and electrical cordset pass through a single firewall opening to connect a cold-side motor to a hot-side mechanical component.

A cantilevered vane with a J-shaped airfoil guides cooling fluid through internal channels to stabilize the turbine hub.

Pre-pressuring component raises air-oil mixture pressure to reduce separator unit pressure drop and prevent gearbox oil leakage.

Detergent delivery mechanism injects reagent through baffle plate apertures to clean internal turbine engine cooling circuits.

Axial retaining ring tab placed between adjacent blade roots constrains azimuth movement on turbine wheels.

A shroud hanger directs cooling fluid tangentially into an annular cavity to cool gas turbine engine segments.

This airfoil design uses a segmented plenum and flared tip to resolve the contradiction between reducing moving object weight and preserving aerodynamic strength.

A borescope plug base uses offset mounting apertures to prevent upside-down installation.

A steam turbine hollow stationary blade uses partitioned chambers to manage internal pressure and reduce surface water droplets.

An accessory gearbox buffer air pump pressurizes bypass air via an impeller, eliminating external heat exchangers and reducing system weight.

A turbocharger back plate incorporates a low thermal conductivity heat shielding portion between the flange and bearing housing.

A rotor design maintains blade-disk contact using a lifting part within the cooling cavity, preventing root spring damage during low-speed rotation.

Movable bodies within cup cavities counteract resonance amplitudes caused by manufacturing frequency shifts.

A submersible electrical actuator with a waterproof housing and push-pull rod controls hydro turbine wicket gates.

An external combustion chamber separated from the turbine maintains high pressure and temperature, resolving efficiency losses from low running conditions.

A silicon carbide discharge switch couples a rechargeable energy source to pulse-forming networks in gas turbine ignition systems.

A unison ring with offset rigging holes aligns with a casing to set the initial angle of variable stator vanes in gas turbine engines.

A trailing edge trench with angled cooling passages directs coolant air downstream to insulate turbine blade tips from hot combustion gases.

A turbine nozzle uses a coolant distribution plenum to supply fresh fluid to subsurface cooling channels, resolving limited coolant distribution efficiency.

Randomly varied serrations on wind turbine blade trailing edges disrupt vortex formation to lower aerodynamic noise levels.

Alternating blade eigenvalues create a specific mistune distribution to suppress resonance response amplification.

Flight control system calculates minimum altitude based on descent rate and restart time to resolve single-engine failure recovery risks.

Optimized airfoil cooling holes balance structural strength against cooling effectiveness to extend blade durability.

Floating barge drives offshore hydraulic pump via rack gear to generate electricity while avoiding offshore electronic corrosion.

Multi-prong retaining elements engage with collar features to prevent foreign object damage from improper installation.

Resiliently biased hangers suspend liners via elastic biasing forces, eliminating manual shimming and accommodating thermal expansion tolerances.

Acoustic drivers excite airfoil vibratory modes to shed ice, reducing imbalances and vibrations caused by asymmetric shedding.

Cooling channel protects elastomer O-ring from heat, reducing outgassing and permeation leaks while lowering device complexity.

Insulating elements in the annular duct and exhaust discharge region thermally isolate the turbine housing from hot exhaust gas mass flow.

Impingement cooling manifolds with adjustable holes deliver uniform heat transfer across heavy-duty turbine casings.

A multi-shaft gas turbine uses a sub-electric motor to adjust compressor rotation speed and increase air mass flow rate.

Cooled compressed air directs flow adjacent to the rotor to constrain thermal expansion, minimizing blade tip clearance and gas leakage.

Elastomeric tabs absorb thermal strain to maintain sealing reliability while preserving aerodynamic continuity in turbomachine exhaust assemblies.

A nacelle cooling valve regulates airflow into equipment compartments using a pressure-responsive regulating member.

A hydroelectric channel system uses a one-way gate to accumulate water and drive power generation units via a siphon effect.

Injecting steam upstream of the diffuser plenum reduces combustion temperatures and thermal stresses while lowering NOx emissions.

Segmented blade tracks use keystone geometry and metallic splines to prevent gaps between adjacent segments.

An annular support fixture with axial and radial protrusions secures a steam turbine rotor, eliminating temporary bearings and pressure boundary breaches.

A tubular shaft with rotational coupling decouples the rotor from drive means, absorbing mechanical loads and preventing gear damage during maintenance.

An axially divided inner ring with screw-mounted segments absorbs structural loads and minimizes relative movements between components.

A portable load device uses a motorized cable to apply tension directly to wind turbine blades from the nacelle.

A brushless asynchronous electric machine converts DC voltage into three-phase power to drive an aircraft gas turbine shaft.

A scupper directs lubricant through a shaft cavity to engage splines, eliminating continuous flow risks during gas turbine engine operation.

Segmented baffle with perforated flange and recovery gutter slows churning oil to release trapped air, enabling effective scavenging.

A gas turbine casing heating chamber directs hot cooling air through internal walls to rapidly expand the structure during acceleration events.

Hydraulic injection drives continuous rotation to increase energy density without requiring expensive composite materials or vacuum chambers.

A turbine blade root design using ceramic-matrix materials and a segmented stem structure for secure attachment to metallic disks.

Segmented conductive paths arranged in a specular pattern reduce radar reflectivity while maintaining electro-thermal deicing effectiveness.