Engine Fuctions TRIZ Cases

Segmented moulding core forms de-dusting conduit through second cavity to evacuate dust, minimizing blade mass and enhancing cooling efficiency.

A seal panel uses a cantilever structure to position the seal closer to the rotor.

A rotor blade discharge unit uses a deformable roller contact to maintain electrical conductivity.

Upstream positioning of streamlined connecting members minimizes vortex development and aerodynamic loss while maintaining structural integrity.

Hydraulic attenuators control barrier movement to improve energy conversion efficiency and durability.

Removable locating structures engage fasteners to secure fan casings, preserving structural strength while improving positional tolerance.

Bushing and washer anchor system accommodates differential thermal expansion between windage shield and fan disk to reduce fastener stress.

Printed circuitry on the core merges with a reflector layer to reduce wind turbine radar signature without adding weight.

Nested acoustic elements inside the cellular structure expand the absorption bandwidth without increasing panel weight or surface area.

A selective thermal barrier coating protects gas turbine stator vanes from high temperatures while preserving trailing edge geometry.

Directly mounting the low shaft bearing support flange to the front frame assembly creates a rigid structural connection.

Nesting pitch driving units in unused three-dimensional space eliminates structural interference, allowing effective downsizing of the hub and nacelle.

An alignment device adjusts lifting leg lengths to orient drive train components, reducing maintenance downtime.

A monolithic flow structure integrates diffuser and deswirl passages within hollow tubes to manage compressor fluid dynamics.

Evaluating dew point parameters to modulate heating and cooling, preventing airfoil degradation from moisture condensation in recirculated exhaust gases.

A bearing life determination device updates statistical values using momentary rating calculations from operational parameters.

Positioning a weaker shear section aft of the thrust bearing prevents uncontrolled overspeed damage during shaft failure.

Radially outwardly biasing springs mount arcuate panels to the engine casing, reducing manifold weight and fatigue damage from vibratory stresses.

A condition monitoring method for pump assemblies estimates system curves using operating point data to detect operational state changes.

Nested concentric fairings with Helmholtz resonators reduce drag while containing fire hazards, eliminating separate acoustic treatment components.

Connecting the centrifugal oil separator to the high-pressure shaft increases separation capacity while removing the dedicated accessory gearbox drive.

Segmented turbine shrouds use tandem seals to accommodate thermal expansion differences between metallic and ceramic components.

A turbine blade trailing edge cooling circuit redirects coolant to pressure side cavities for internal heat transfer.

Hybrid metallic sheath and composite core airfoils enable controlled flexing for vibration management.

A breather assembly baffle redirects oil droplets and pressurized air to prevent impingement, reducing static pressure imbalances in the oil tank.

Adjustable inlet guide vanes control air mass flow during gas turbine engine startup to maintain emission-compliant firing temperatures.

Segmented radial fins with internal cooling passages remove heat from the seal and blade interface, resolving cooling difficulty in complex geometries.

Deploying a deformable wall increases the acoustic treatment area to attenuate compressor noise during approach.

Decoupled gear architecture allows maintenance access while engine remains mounted, reducing operational downtime and costs.

Shape memory polymer diaphragms adjust resonator depth to modify acoustic impedance across wide frequency ranges.

Segmented cooling modules scale in three dimensions to overcome structural limits on panel height and width, expanding cooling area without redesign.

Internal fluid channels within turbine component coatings circulate cooling media to extract heat, eliminating aerodynamic mixing losses from film cooling.

Independent tip and hub segment rotation matches distorted inlet airflows, resolving fan operability issues caused by pressure fluctuations.

Internal disc cavity cooling enables higher working temperatures by evaporating liquid and condensing vapor to reduce thermal loads.

A turbine exhaust case uses distinct alloys to resist high temperatures.

Thermal recovery stores compression heat to pre-heat the turbine, eliminating external energy input and enabling fast start-up.

Segmented hollow portions connect base and tip elongated holes, simplifying machining while preserving blade strength against single-space hollow weakness.

A damped adapter system mounts a fuel flow divider valve using Belleville washers to absorb dynamic energy.

Dual fluid biasing apparatuses load a damper block onto an inner shroud, reducing blade tip clearance without relying on temperature-sensitive springs.

Opening guide vanes at 50% maximum prevents swirling flow damage while bypass valves equalize pressure for rapid rotation.

An auxiliary wheel with a bayonet mount locks the turbine rotor while providing a dedicated interface for accurate rotational speed detection.

Internal housing channels and fins transfer friction heat away from dry clutch discs to maintain service life.

A turbomachine fan shaft cover seals an annular lubrication bath, preventing fluid stagnation that causes dynamic imbalance.

Shroud assembly hanger uses interference fit seal member to maintain radial footprint.

A shaft shoulder groove produces uniform axial deflection, preventing contact face misalignment and reducing wear in turbomachinery seals.

Tuning movable mass frequencies matches ocean waves, resolving low power density and calm sea instability.

Unmanned aerial vehicle gathers high resolution images to build accurate digital surface models, replacing outdated satellite data with current terrain details.

Variable thickness in the outward part accommodates large cooling channels while allowing deformation to reduce heat stress.

Automated tuning controller adjusts fuel distribution and injection timing using real-time sensor data.