Engine Fuctions TRIZ Cases

An inclined flange bearing face decomposes excessive axial pre-tension into radial efforts, preventing rotor disk distortion under centrifugal expansion.

Segmented magnesium and aluminum alloy closures with v-band flanges manage cantilever vibration loads while reducing overall housing weight.

Segmented pin and cover plate mounting accommodates thermal expansion differences between ceramic and metallic components while preventing gas leakage.

A CO2 medium shutoff valve interrupts flow between the regenerative heat exchanger and combustor to manage turbine rotation.

Segmented brackets with expansion slots absorb thermal stress from temperature gradients, reducing tilting moments and wear on the distributor foot.

A multi-stage bleed air system extracts compressor air to a turbo-compressor, using heat exchangers to manage temperature and pressure for environmental control.

A hydraulic motor control system manages valve timing to produce precise torque contributions for shaft positioning.

Current sensors on ground conductors detect lightning strike currents, enabling real-time monitoring and immediate operational decisions for wind turbines.

Low restitution coatings on inlet separators prevent particle rebound into the compressor, reducing wear and maintenance costs.

A wave-generating system mounted on weather hoods emits ultrasonic energy to repel flying insects from gas turbine inlet air filtration units.

An annular blade outer air seal assembly with a stator flange prevents rotor overspeed by engaging stationary vanes during high shaft failures.

Fastening grooves and stops fix turbine vane airfoils against circumferential movement, reducing vibration and improving torque transmission.

Shape memory alloy dampers absorb high loading energies to reduce rotor deflection in gas turbine engines.

Centrifugal force within the rotor arm boosts cooling air pressure, enabling flow into remote cavities without significant pressure drops.

Hub suction ports capture fine particles below 80 microns via inertia and suction, preventing engine performance degradation from ingestion.

Segmented planetary gear stages with dedicated idler gears reduce planet bearing loads and heat generation in aircraft gas turbine engines.

Non-parallel axis gearing distributes accessories over wider angular sector without increasing accessory drive case mass or bulk.

Angled walls direct cooling fluid through impingement channels to reduce pressure losses and support outer walls during thermal expansion.

A crank and link assembly synchronizes pivot door thrust reverser operation via a single actuator.

Multiple securing segments distribute centrifugal forces to the disc wheel while interacting with rotor blades.

A compliant bushing and collar assembly secures ceramic skin panels to metallic structures.

Concentric annular accumulator drains oil into scavenge tubes during shutdown to prevent coking and reduce pressure loss.

A hydrostatic plain bearing assembly supports wind turbine blades using a pressurized fluid film between inner and outer members.

Segmented seal plates enable independent blade removal without lifting the casing, resolving assembly complexity while maintaining retention security.

Radar-absorbent material coatings on the polygonal tower structure reduce electromagnetic reflections from vertical axis wind turbines near airports.

Flexible membrane shrouds reduce structural stress from side gusts and tower complexity by diffusing wake area to enhance mass flow.

Modular root and tip frames adjust inter-blade spacing to balance structural stability against transport height restrictions.

A variable transmission decouples the low pressure compressor rotor from the spool to maintain optimal rotational speeds across varying power demands.

A lightning current transfer unit uses a spark gap between movable blade and nacelle connections to maintain electrical coupling during rotation.

A gas turbine bearing replacement support mechanism uses a wedge and moving bolt to adjust tie rod position.

Strategic notch geometry on flange portions reduces thermal stress concentration at bolt holes, extending casing service life.

Radial interference fit transfers ultimate loads via the fan shaft, reducing engine diameter while maintaining structural strength.

Geometric intrusions in the rotor rim surface reduce vibrational bending stresses while maintaining lightweight design constraints.

An electro-pneumatic starter rotates gas turbine components at selected speeds to prevent rotor bowing.

A geared turbofan generator drives a sun gear via a flexible shaft to increase rotational speed, resolving low spool power constraints.

Segmenting two-phase fluid via an intermediary separator enables independent liquid and gas flow rate measurement to verify proper drain removal.

Segmented exhaust nozzle centerbody support transfers loads via rods while accommodating thermal expansion to maintain structural integrity.

Varying land widths along the span direction optimizes coolant distribution to reduce thermal stresses and extend turbine blade lifespan.

A self-regulating water turbine runner uses an upstream sub-runner to adjust main blade angles via hydrodynamic energy.

A bi-stable valve toggles between closed positions to manage liquid fuel pressure in turbine engines.

A sound insulation flap rotates via a turnover mechanism to expose the combustion air intake interface.

A diffuser removal tool uses a lead screw assembly to axially displace an exhaust diffuser from a gas turbine engine.

Segmenting the airfoil into vapor and film zones resolves trailing edge space constraints while redirecting spent bleed air to eliminate mixing losses.

Helical deformable blades adapt to varying swell conditions, reducing drag and improving energy conversion efficiency.

A partial height rib in a radially recessed tip pocket strengthens the trailing edge against thermo-mechanical fatigue without impeding cooling airflow.

Alternating radial bias film cooling holes direct coolant inward and outward to optimize airfoil surface coverage.

A ceramic matrix composite vane assembly with a locator flange and pin maintains airfoil position.

Segmented leaky feeders provide 360-degree yaw coverage for blade inspection, resolving the trade-off between measurement precision and device complexity.

Metallic spar transfers aerodynamic loads through ceramic matrix composite turbine vanes to the engine case, resolving structural strength deficits.