Engine Fuctions TRIZ Cases

A rotating device adjusts revolution surface angles relative to fluid flow direction.

Acoustic shield reduces noise emissions by 4 dB while maintaining aerodynamic performance.

Nested epicyclic gears and oil transfer bearings reduce device complexity while enabling compact packaging for high bypass ratio engines.

Compliant grommets isolate turbine vane tips from shroud slots, preventing foreign object damage while maintaining airflow continuity without adhesives.

Nested modular chambers target fan flutter modes, absorbing acoustic energy within constrained nacelle space to enhance engine reliability.

A captive bolt and spring assembly allows a mounting boss to move relative to the fastener, accommodating component displacement.

Slotted curved shroud interfaces react circumferential loads to enable pitch-wise blade rotation, reducing root deflection and mitigating 1P loading effects.

Retaining projections on the sealing element enable axial displaceability to compensate for thermal expansion without inducing bending stresses.

Segmented optical probes and dynamic feedback distinguish knife edges from shroud reflections to resolve axial shift measurement errors.

An integrated attachment protrusion engages a retaining ring, reducing manufacturing complexity while maintaining structural strength.

Segmented washers and spherical attachment ends accommodate thermal growth and misalignment while simplifying assembly.

Stoichiometric exhaust gas recirculation reduces excess oxygen in turbine exhaust to enable effective NOx reduction and carbon capture.

A monitoring system calculates torque by comparing blade and shaft arrival times using non-contact sensors.

Coordinate-based measurement system acquires rotor blade pre-twist by correcting shroud spreading dimensions against axial misalignment.

Predicting rotating stall via compressor exit pressure fluctuations replaces crude temperature thresholds to reduce engine start times.

A transport frame uses locating fingers and recesses to enable secure stacking of wind turbine blades.

Opposing wind wheels on a tower column generate counteracting torques that stabilize the frame while reducing manufacturing complexity.

Gear reduction decouples fan and compressor speeds, allowing selective use of integrally bladed rotors to reduce leakage and maintenance costs.

Piezoelectric actuators drive sliding seal segments to maintain optimal clearance, resolving thermal expansion trade-offs in gas turbine engines.

A gas turbine controller drives the compressor with a motor to maintain rotational speed during idle operation.

A gas turbine seal carrier uses axially resilient jaws to clamp a rope seal element for stable component engagement.

A bleed air heat ejector uses vortex generators and angled jets to mix ambient and heated streams.

Segmented tabs and a split ring prevent axial disengagement in gas turbine engines, eliminating loose fastener risks.

A control process monitors turbomachine cooldown to enable safe restarts.

Segmented impingement and film cooling zones manage high heat loads on turbine airfoils, maintaining structural integrity under combustion temperatures.

A passive fuzing system initiates additional pulses in a multi-pulse propulsion unit using sensor data.

Asymmetric journal pin rim aligns maximum thickness with load vectors to distribute combined forces, preventing gear tooth edge touchdown and bearing failure.

Contoured pre-swirler end walls reduce pressure loss and aerodynamic drag, enabling efficient ambient air induced cooling for gas turbine engines.

Interchangeable platform adaptors engage diverse case configurations on a rotatable support platform, resolving fixture versatility constraints.

Rotor disc merges blade retention into radial walls with ventilation channels, eliminating complex retaining rings and reducing gas leakage.

Radial spacers shield gas turbine disks from thermal damage while transmitting compressive preloads.

Offset jet holes generate swirling flow along turbine blade inner walls, reducing pressure loss and improving heat transfer uniformity at the leading edge.

Clamping device connects turbocharger bearing and compressor housings via force fit.

A casting core design orients groove axes along the die pull direction to facilitate convective cooling in gas turbine engine components.

A hydraulic axial piston engine uses detachable cylinder-piston units to control displacement volume.

A thrust reverser drive unit uses a movable clutch to connect manual rotation to the motor shaft.

Segmented airfoil portions with interchangeable inserts resolve manufacturing complexity while maintaining cooling efficiency under high temperature stresses.

A protective sleeve directs cooling air along a thermal control cable to lower ambient temperature and prevent damage.

Segmented cavities shield each other to balance temperature distribution and structural robustness at the tip.

Pressure vessel displaces trapped air from honeycomb cells to eliminate false readings and reduce inspection time.

A monolithic cellular metal filtering baffle traps particulate matter in aircraft engine cooling air using a non-stochastic lattice structure.

An interlocking seal structure with integrated damper elements reduces airflow leakage between circumferentially arranged rotating components.

Thermal barrier coating in a shallow blade tip recess reduces temperature while preserving aerodynamic efficiency and preventing erosion.

Internal cavity fillers reduce radar cross sections by 20-25 dB, enabling wind turbine deployment near airport monitoring systems.

An asymmetric slot and oblong opening in the mounting rail relieve concentrated stresses, reducing cracking risks while maintaining structural integrity.

Integrating the impeller and rotating component before final assembly eliminates repeated balance adjustments, reducing total manufacturing time.

Integrating cooling channels and primary rim holes reduces hot gas leakage while managing thermal resistance at the blade tip.

A counter-rotating low pressure turbine design rotates final stage blades opposite to preceding stages.

High-pressure jets from upstream splitters create a fluid barrier that resists core pressure leakage into the bypass stream.

Machined web surfaces with mismatch plateaus reduce stress concentration at intersections, extending component lifespan.