Engine Fuctions TRIZ Cases

A gas turbine fan rotor assembly transmits torque through frictional forces between tapered shaft and wheel surfaces.

A clutch mechanism switches power sources between high and low speed spools in an accessory gearbox.

A turbine control system biases fuel demand signals using calculated combustion efficiency factors to stabilize operation.

Radially extending mass-region increases inertia for effective damping while seal surfaces maintain platform gaps without costly material removal.

Segmented U-channels and a serpentine platform purge system reuse cooling air to dissipate heat from both pressure and suction walls.

Segmented platform trenches and nested cooling holes distribute bleed airflow to mitigate thermal stress and prevent hot spots.

A rotor blade tip uses a slot in the suction side rail to direct gas flow and disrupt vortex formation near the airfoil surface.

Segmented manifold assemblies deliver targeted cooling to blade outer air seals, maintaining consistent tip clearance across varying engine power settings.

A lubrication system oil tank integrates an electric generator to convert flowing oil kinetic energy into auxiliary electrical power.

Segmented impingement and film channels break down debris via impact force, preventing channel clogging and ensuring reliable thermal energy removal.

Composite exhaust cone uses modular resonators to attenuate noise without increasing mass.

A flow guidance device captures and directs the planet gear lubricant stream through an outlet region to manage fluid distribution.

GTPOS system predicts surge and choke conditions using dynamic modeling to maintain operational stability with greener fuels.

Negative pressure relief line prevents suction line deformation and maintains pump suction capacity by relieving negative pressure after engine shutdown.

A detection system monitors aircraft engine bleed air using forward and rearward sensor packages to identify oil presence in the airflow.

A gear mechanism drives a compressor at higher speeds than the turbine to accelerate air entering an air turbine engine.

A radially adjustable ring stiffener expands inside tubular wind turbine structures to engage the inner surface via friction.

Maintains constant shaft acceleration to prevent ignition window entry failure in cold weather by dynamically adjusting starter torque.

Streamwise passageways provide localized cooling to resolve coating interference gaps and ensure uniform thermal barrier application.

Annular chamber around planet gear carrier reduces pressure loss and dampens fluctuations for reliable lubricant supply.

Segmented inner band vane mount segments interlock without compression, preventing permanent deformation during installation.

A metal blade creates a thermal bridge between a set-back heat exchanger and the leading edge to transfer heat.

Power interruption and position monitoring detect broken push-pull cables in turbine engines.

Offset outer diameter platform axes extend beyond inner platforms to enhance temperature uniformity across high pressure turbine assemblies.

Separate actuating and connecting elements lift the anchor cage upper flange without contacting anchor bolts, resolving leveling inefficiency.

Angled interplanetary vanes redirect oil axially to prevent overheating and hydraulic lock in stationary ring gear configurations.

Metallic collar distributes loads across large areas of ceramic matrix composite turbine nozzles, eliminating line contacts and reducing mechanical stress.

A ground plane uses frequency-dependent conductivity to reflect radar signals while insulating against lightning discharge frequencies.

Monitor system detects freewheel slip by measuring torque and rotor speed, preventing mechanical damage during engine startup.

Graded aluminum layers limit interdiffusion between substrate and coating, extending component lifetime in high-temperature environments.

Segmented protrusions and a capillary porous layer suppress the Leidenfrost effect, achieving sub-second droplet evaporation across 200-1,200°C temperatures.

A turbine airfoil tip shelf directs cooling fluid through shaped film holes, reducing required flow by 50% while maintaining high-temperature coverage.

A wind turbine rotor blade incorporates a breakaway tip portion designed to detach upon impact.

A fiber optic current sensor detects lightning parameters via Faraday rotation of a radiation beam.

An annular plenum chamber delivers coolant into a turbine inter-stage cavity through controlled outlet holes.

Segmented end-wall design with sliding seals mitigates thermal expansion cracking while maintaining aero load transfer and sealing efficiency.

An inflatable bladder secures repair tools within a gas turbine engine, preventing overspray damage during in situ maintenance.

An enlarged corner fillet extends film hole length, resolving cooling gaps in high-pressure turbine components.

Blades overlap to block wind infiltration, reducing braking effect on vertical axis turbines.

Tailored trailing-edge thickness reduces required cooling flow to lower specific fuel consumption while maintaining component lifetime.

A boiler plant cooler transfers heat from a cooling medium to supply-water using segmented paths and an intermediary temperature regulator.

Low expansion clearance control bands limit ring segment radial movement, eliminating hot gas leakage while preventing blade rub during startup transients.

A nozzle mounting assembly uses a retaining ring with an anti-rotation pin to secure the gas turbine component.

Equalizing cavities balance flow between wall and skin sub-circuits, reducing cooling air requirements by 30-50%.

Radial journals extend from platform plates to stabilize guide vanes, eliminating complex bearing bushes that increase weight and assembly complexity.

A rotor blade heating strip conducts electrical energy to reduce ice adhesion on the surface.

A wedge-shaped locating component positions between a gas turbine engine strut and fairing sheath to establish precise axial spacing.

A stationary blade endwall chamber directs cooling fluid through segmented passages to manage thermal energy transfer.

Helmholtz resonator cavities within the cascade structure tune specific sound frequencies to maximize acoustic absorption without increasing radial bulk.