Engine Fuctions TRIZ Cases

Bushing mediates fastener clamping load to prevent composite bumper fatigue cracking and extend service life.

Non-uniform circumferential spacing between alternating nozzle vanes mitigates resonant vibrations caused by blade-to-vane interactions.

A composite coating with optimized carbon filler volume prevents particulate overlap and rust, reducing interference with air traffic control radars.

Merging separate oil circuits into a single exchanger reduces equipment mass and air flow disturbances while enhancing thermal regulation.

Pressurized gas flow through vent holes forms a compressed gas layer between the pin and lug, reducing vibration and fretting wear in propulsion systems.

Automated sensor arrays replace manual inspections by measuring rotor displacement and thermal anomalies, reducing wind turbine downtime.

A turbine vane assembly uses a compliant layer between metallic and ceramic components to distribute pressure loads.

Flexible turbine vane cover plate wings accommodate tolerance variations across multi-tiered mounting structures, ensuring reliable pressure sealing.

Controller establishes usage baselines for inlet guide vanes to detect actuator degradation via sensor data analysis.

Segmenting the vacuum pump on the drive shaft reduces centrifugal forces, preventing rotor-stator contact and improving energy storage efficiency.

A non-pulsating pump adjusts plunger stroke length to match inner chamber pressure with discharge line pressure.

A wind turbine blade load sensor system estimates blade temperature using existing parameters to correct load measurements without extra hardware.

Varying bore hole gaps in the support ring allow the transition duct to shift during thermal expansion, reducing stress on the connection.

A turbine stator assembly uses sliding pins in oblong openings to decouple the sealing ring from the guide vane assembly.

An air mixing system uses heat exchangers and onboard injectors to condition cooling gas for turbine components.

Thermally unconstrained pins decouple metallic leaf seals from composite walls, preventing leakage caused by thermal expansion mismatch.

Reducing cover plate thickness via a localized groove decouples thermal loads at the trailing edge transition, extending gas turbine service life.

An eductor mixes turbine extraction gas with suction flow to heat the intake stream, maintaining thermal efficiency during low-load turndown operations.

Segmented inner partition wall intercepts water drops to protect outer casing from erosion while enabling compact drain discharge without external piping.

A planetary gear mechanism uses radial and axial slide bearings with an oil distributor ring for pressure lubrication.

Segmented baffle chimneys distribute cooling air without disrupting impingement flow, resolving thermal stress in gas turbine engines.

A dual cavity baffle system separates cooling air into distinct flows to cool stator vanes and outer platforms.

Discrete clamping projections along the strip seal length alter natural frequency to prevent fatigue failure.

A condensable working fluid energy storage system uses direct contact with an unvaporizable liquid for isothermal compression.

Segmented trailing edge flats enable hole production while maintaining a small radius of curvature to minimize aerodynamic losses.

Asymmetric anti-rotation pins prevent inner shroud twisting under high air loads while accommodating thermal expansion.

A turbine module merges a heat exchanger within the flow duct to transfer thermal energy directly to the working fluid.

A bearing bumper assembly engages the housing during blade out events to transfer impact forces away from primary attachment members.

A shaft break mitigation system introduces fluid into the turbine exhaust to reduce nozzle effective area and limit mass flow rate.

Open-loop rectifier vane adjustment resolves high bypass ratio inertia trade-offs, enabling precise thrust regulation without propeller speed variation.

Segmented web geometry with opposing inclinations improves load distribution and stiffness while maintaining compact diameter.

Nested adapter design minimizes airflow disruption and leakage by replacing large inspection holes with a sealed intermediary interface.

Piezoelectric actuators adjust airfoil leading and trailing edges to resolve adaptability complexity trade-offs in gas turbine engines.

A movable fin at the wind turbine blade tip deploys as an aerodynamic stabilizer to reduce edgewise oscillations during non-operational modes.

Fixed and variable critical flow nozzles automatically adjust fuel distribution based on pressure, preventing rotating pressure waves in gas turbine engines.

Integrated rotor shroud reduces acoustic emissions and weight by merging aerodynamic liner functions with aeroacoustic absorption capabilities.

A tapered tip flag cavity core transitions radial height to define metering pedestals within the cooling circuit.

Spring-loaded metal clamping rings accommodate thermal expansion differences between ceramic and metal components, reducing localized stress on brittle vanes.

Deflector plate spreads heated fluid across gas turbine filters, resolving cold spots and reducing nozzle count for uniform heat distribution.

Internal damping beam dissipates tower wall oscillation energy through friction, eliminating heavy external shells that strain the structure.

Staggered plates inside rotor disc slots increase heat exchange surface area, resolving low thermal transfer efficiency in high-temperature gas environments.

Segmented carrier segments with impingement apertures manage turbine casing temperature, maintaining optimal tip clearance during transient power increases.

Resilient mounting of the annulus gear at both ends reduces axial divergence and oil leakage while maintaining radial load capacity.

Angled openings in widened attachment portions distribute stress to prevent concentration while maintaining aerodynamic properties.

Aligning the squealer tip with the centroid curve reduces vibrational stresses and cracking risks while maintaining aerodynamic efficiency.

Varying coil fin density across gas turbine air intake systems achieves uniform outlet temperatures and reduces condensate carry-over.

A blade outer air seal platform incorporates a radially outward boss feature to establish a solid material pathway.

Conical concrete foundation base distributes tower loads evenly while reducing tower segment diameter for easier transportation.

A variable volume device adjusts thermal transport bus pressure to manage heat exchange fluid flow in gas turbine engines.

Varying blade root tooth spacing increases base-side first tooth thickness to manage centrifugal loads.