Engine Fuctions TRIZ Cases

Passive extraction passages divert exhaust gas to sensors, resolving measurement precision versus device complexity trade-offs.

A detachable extension shaft integrates power transmission and auxiliary unit mounting within a jet engine gear drive.

Cardanic suspension isolates wind-induced bending loads from the drive train, reducing constraining forces on bearings.

Sensors monitor thermal conductivity to detect invisible hydrogen leaks, enabling early isolation of fuel system faults.

Logical command processor parses speech inputs against predetermined grammars to determine command completeness and execute valid instructions.

A disposable elastomeric plug eliminates complex shutter assemblies and silicone cleaning by obstructing fixing orifices to prevent corrosion.

Dynamic valve control modulates fuel circulation using sensor feedback, preventing degradation while maximizing heat absorption.

A submersible pump uses a top slit and cycling control to expel trapped air from the impeller housing.

Automated fan speed monitoring detects uncontrolled high thrust conditions without crew intervention.

A dead-end tip flag cavity linked to a serpentine channel reduces thermal stress on tip cap materials while maintaining airflow through the airfoil structure.

Logic gates cross-verify fire, fluid, and electric sensor anomalies to eliminate false alarms while maintaining rapid response times.

A segmented seal assembly uses impingement cooling to reduce thermal stress in gas turbine engines.

A dual valve fluid metering system maintains selected delta pressure and flow rate to resolve accuracy challenges in jet engine fuel control applications.

Protrusions on the cast inner housing radiate heat away from sheet metal joints, suppressing thermal stress and preventing crack generation.

Inflatable streamlined fairing lowers air resistance to cut power consumption and equipment wear in blade fatigue tests.

Dual sumps and a configuration plate enable external adaptation of the lubrication system, eliminating gearbox disassembly for different assembly orientations.

Interlocking CMC blade track segments prevent movement and leakage in high-temperature gas turbine engines.

Drilled bore in expansion tube allows hose extraction of excess corrosion protection oil, preventing leakage contamination in wind turbine tower lower regions.

Replacing metallic disk assemblies with ceramic matrix composite materials reduces spinning mass and deflections in a cantilevered aft bearing configuration.

Annular recesses in turbine diaphragms collect condensate for discharge through tubular members, preventing seal face erosion.

A turbine airfoil cover extends into a trench to direct cooling medium flow, reducing manufacturing difficulty of complex film holes.

Stiffening device counters slipping and bending moments at rotor blade flanges, preventing screw loosening despite reduced torque or low friction.

A hybrid actuator combines electric and hydraulic power sources to drive gas turbine engine components reliably.

Equidistant cross-over holes and arcuate transitions ensure uniform airflow distribution, eliminating hot spots in turbine blade trailing edges.

Segmented linear passageways and plugs delay cooling until target locations, reducing pressure drop while maintaining thermal durability of turbine blades.

Segmented acoustic liners with tailored cavity depths dampen targeted noise while minimizing pressure drop and engine footprint.

Rigid movement transmission parts connect adjacent levers in variable cross section nozzles, eliminating hyperstatism and mechanical imbalance during operation.

A pump assembly integrates the controller between the motor and pump elements to utilize pressurized fluid for active thermal management.

Integrated diffuser bleed baffle directs boundary layer flow to a port while dampening acoustic instabilities in gas turbine engines.

A dual-flow turbofan engine uses a planetary reduction gear to drive the central shaft from a low-pressure rotor.

Segmenting primary and augmenting powerplants allows the core engine to optimize cruise efficiency while supplemental thrust supports takeoff.

A collapsible water mass enclosure harnesses vertical wave acceleration to drive a generator via tethering means.

Segmented variable guide vanes and an epicyclical gear train reduce mechanical complexity while improving thermal efficiency.

Converging cooling holes block hot gas ingestion at turbine blade tips, reducing tip leakage losses.

Segmented turbine blade tip isolates the squealer from trailing edge heat, preventing damage while maintaining thermal efficiency.

Closed intermediate heat transfer loop isolates power cycle fluids from primary heat sources, eliminating contamination risks and component stress.

An air outlet hole in a turbine manifold sector enables protective coating deposition on cavity walls while circulating cooling air to reduce hot corrosion.

Integrates centring and air injection to resolve space constraints in small turbomachine separators, increasing de-icing airflow volume.

Portable maintenance tool removes planet wheel pins on-site, eliminating costly gear relocation.

Wire EDM pilot slots relieve residual stresses in gas turbine rotor discs, simplifying blade mounting and extending component life.

A pilot unit with a bias link maintains windage shield alignment in gas turbine engines.

A ring-shaped coil wraps around a claw stator core to drive an electric pump with minimal axial footprint.

Rotatable louvers in the bleed conduit inlet disrupt resonance patterns to minimize tonal noise generation.

Using a valve drainage line for cooling fluid supply eliminates specialized tools and accelerates turbine rotor cooling.

A convex cam pivots convergent petals through a follower roller, reducing axial load on the unison ring while maintaining thrust efficiency.

Interconnected struts apply uniform pressure to eliminate paste voids and ensure structural integrity during trailing edge assembly.

Joint structure accommodates thermal expansion differences between nozzle and thrust chamber materials, eliminating active cooling systems.

Rear inner fairing precooler absorbs heat from hot air via thermal contact with the cold fan stream, eliminating aerodynamic drag and disturbances.

Elastic nacelle coupling dampens tower oscillations without adding weight or structural complexity.