Engine Fuctions TRIZ Cases

Internal cavities filled with flowing damping material replace mechanical springs, eliminating wear and extending component lifetime.

Segmented shroud cooling circuits tailor temperature and pressure profiles to specific plate portions, reducing overcooling and fuel consumption.

A closed-loop system extracts industrial waste heat via heat exchangers to expand fluid and rotate a turbine, recovering energy without complex active controls.

Adaptive foil members adjust pitch and speed via feedback loops, resolving efficiency losses caused by static turbine designs in variable tidal currents.

Acoustic sensors detect pericritical fluid phase changes while a controller adjusts temperature and pressure to maintain stability.

Elastic return device compensates for radial and axial displacements in the interface, maintaining leak tightness to limit pressure losses.

The apparatus predicts rotor blade erosion thresholds by calculating future erosion based on regulated load operating conditions, enabling timely replacement scheduling.

Chevron trip strips generate turbulence in cooling channels to eliminate stagnation regions and improve heat transfer efficiency.

Segmented oil injection and radial drain outlets manage excess fluid, preventing sensor interference and coking on hot surfaces.

Redirection tubes route cooling air through spokes to bypass the torque box, preventing oil leaks into the structural cavity.

A prediction controller fuses current component parameters with historical fault data to generate an overall predictive score for industrial turbine systems.

Planetary gears decouple stage speeds from turbine rotation, resolving efficiency limits caused by single-speed constraints.

Centring pins isolate bearing rings from centrifugal loads to prevent ovalization and wear.

A rotor hub ventilation arrangement directs cool air into the interior space through a manhole cover and pipe system.

Vent vanes in a tail bearing housing direct bleed air parallel to core engine flow, reducing shear noise and bypass duct damage.

A gas turbine engine exhaust nozzle guide vane includes a passage directing airflow from an upstream turbine row to a downstream blade row.

Resilient return means force grille fins apart axially, ensuring reliable deployment despite inconsistent aerodynamic forces.

A compact low pressure turbine section uses an epicyclic transmission to decouple fan and turbine speeds.

Refractory metal exterior walls resist extreme heat while support frames provide structural strength, eliminating bleed air cooling needs.

A pistonless rotary engine design converts combustion energy directly into shaft rotation using a turbine and eccentric chambers.

A pressurized gas vessel surrounds the turbine in this fluid power plant, reducing friction losses and improving energy conversion efficiency.

Counter-rotating fan blades in a geared turbofan aft shroud use pitch change mechanisms to resolve turbine speed and thrust reversal complexity.

A particle collection device uses aerodynamic lensing to focus airborne particles into a dedicated chamber via aligned orifices.

Radial spacing between the disc spring and heat shield reduces thermal stress on the spring, maintaining mechanical impact on the vane ring.

A translating sleeve mechanism drives a gear and screw shaft to actuate aircraft blocker doors without external drag links.

Extracting power from fan autorotation maintains reduction gear lubrication when the high-pressure shaft stops rotating during breakdowns.

A turbomachine couples electric machines to a motor shaft using a power transmission angle gear device housed in a single case.

A conical rotor hub extension decouples blade bearing scaling from the main rotor hub structure.

A baffle insert with curved divoted segments directs cooling air through multiple columns of holes to focus flow at common locations on an airfoil.

A compressed air energy storage system uses constant volume heating to raise gas pressure before expansion.

A helical turbine system channels water through a funnel throat valve to generate rotational force via vortical movement.

Segmented heat shield inserts eliminate windage generation during gas turbine rotor balancing by engaging surface features.

Merging compression units onto one intermediate gear eliminates extra gears, reducing occupied space while maintaining constant rotational speed relationships.

A turbine bypass housing uses fillet radii and boss apertures to manage structural stresses.

Remote actuation moves a block along an internal ramp to eliminate clearances and reduce vibration wear.

Axial support pins replace cantilevered hooks in blade outer air seal assemblies to provide rigid structural coupling.

Clearance holes in unibody brackets decouple localization from load paths, resolving resonant vibration frequency responses in aircraft engine casings.

Lifting gears on a second conveyance jack up the intake assembly and exhaust duct to dock with the first conveyance, reducing installation time.

A turbomachine accessory drive gearbox uses a main shaft with circumferential bevel gears to transmit rotational movement to multiple independent pinions.

Stress dissipation masses on radial struts dissipate thermal and mechanical stresses, resolving low cycle fatigue in gas turbine engine intermediate cases.

An adjustable pendulum damper in the final tower section counters vortex-induced vibrations, enabling safe construction without waiting for calm weather.

Fan-shaped cooling holes discharge air through ceramic matrix composite airfoils to manage heat in hot gas flowpaths.

Replacing hydraulic servomechanisms with an electric drive reduces turbine weight and eliminates oil leakage risks.

Segmented annular bearing support aligns countershaft bevel gears to prevent tooth damage from thermal expansion and manufacturing tolerances.

A geared turbofan engine design with a high bypass ratio and specific compression section geometry.

Dual flow paths in the heat exchange assembly direct cooling fluids to mitigate thermal gradients and prevent dry gas seal overheating.

Translatable bleed valve ring extracts particles via mechanical scooping, reducing pressure losses at low engine power.

A humid air turbine exhaust gas reheater uses cooled water recovery unit coolant as a heat medium to raise discharge temperature.

A planetary gear train transmits power from low-pressure and high-pressure shafts to a turbojet engine fan for adjustable rotational speed control.