Engine Fuctions TRIZ Cases

Segmenting the annular chamber extends effective flow length via centrifugal force, resolving low separation efficiency in aircraft engine lubrication systems.

Porous plugs inserted into IBH feed pipe orifices absorb acoustic energy from sonic jets, enabling upstream positioning and reducing system complexity.

Deriving an equation from manufacturer data for variable NPSHr prevents unnecessary shutdowns caused by constant threshold values.

A hybrid wind turbine gearbox integrates planetary and fixed-axis stages to reduce axial length.

A double circumferential lap joint seals gas turbine heat shield segments using an interference fit between an outer cover and alignment tab.

Gear reduction mechanism drives fan rotor co-rotating with turbine to resolve volume versus power density contradiction.

Dual cameras track light-emitting markers on wind turbine rotor blades to calculate curvature while ignoring vibration errors.

A turbine housing wall restricts coolant duct surface area relative to the exhaust passage to manage thermal loading.

Piezoelectric fins absorb wave forces through flexible deformation, reducing structural loads and manufacturing costs.

An axial blind-hole in the rotary shaft lowers pressure on the rotor back face, reducing thrust force and eliminating large thrust bearings.

A gas turbine fuel flow control system estimates metering valve discharge using differential pressure error signals.

An annular damping part absorbs vibrations from the low-pressure body, protecting bearing supports and extending service life.

Movable spiral conduit sections manage thermal expansion while methanol injection prevents ice blockage in aerospace heat exchangers.

Turbine engine drives shaft and gas lift fans to generate vertical thrust, reducing energy wastage from high-velocity exhaust flow.

A sensor validation method calculates deviation between measured data and reconstructed values to signal faults.

A rotating transport frame switches a wind turbine blade orientation for land and sea transit, eliminating costly realignment operations.

A dual bypass filter cascade uses nested coarse and fine mesh filters with pressure-responsive valves to maintain continuous lubricant flow.

Elastomeric flaps convert bidirectional wave flow into unidirectional turbine rotation, improving energy capture efficiency.

A combustion dynamics prediction system compares sensor signals with predicted frequencies to detect gas turbine engine flashback events.

Dynamic torque switching resolves incident and reflected wave energy mismatch for improved efficiency.

Ceramic-matrix composite heat shields protect metallic nozzle guide vane structures from high temperature gas flow.

A twisting damping guide link stabilizes a gas turbine bleed valve ring through elastic deformation.

Integrating the compressor diffuser with turbine vanes eliminates bleed cooling needs, reducing engine axial length.

A gas turbine vane uses a segmented internal flow path to direct cooling air precisely to high-heat regions.

Nested blocker doors eliminate bypass duct gaps that cause flow losses, while translating cascades expand acoustic treatment areas.

A passive valve assembly manages airflow in a gas turbine nozzle using a differential thermal expansion band.

A heavy hammer wave power device uses a chain ring and sprockets to convert bidirectional swinging into unidirectional rotation.

A bushing with frangible tabs and coupons breaks off to signal mechanical overload in variable stator vane actuation systems.

A gas turbine bearing compartment fluid trap design maintains lubricating oil levels in scavenge lines during shutdown.

A preloaded spring within an elastomeric filler resists flutter and shifts inherent frequency away from resonant ranges.

Segmented impellers harvest bidirectional tidal currents, eliminating complex pivoting mechanisms.

Integrating exhaust devices into trailing edges reduces acoustic impact and casing weight by preserving structural integrity.

Segmented disk and circumferential pins distribute stress at blade attachment points while resisting thermal loads.

Spring mounts accommodate thermal expansion differences between ceramic matrix composite flow path rings and metallic cases to maintain radial position.

Mechanical coupling accommodates different thermal expansion rates between dissimilar materials, minimizing stress during high temperature exposure.

A controller applies a correction factor to nominal fuel flow using mass flow meter feedback for accurate combustion control.

A turbine case cooling system manages metallic vane support temperature to control ceramic matrix composite vane movement.

An analog electronic pre-processing device synchronizes sensor signals before digital conversion to streamline measurement workflows.

Heat recoverer transfers thermal energy from turbine discharge gas to compressed air, improving output efficiency without increasing entry temperature.

A tapered boss design reduces stress concentration on gas turbine cases by attenuating low-cycle fatigue loads through elastic deformation.

Clocking second-stage airfoils relative to first-stage members intercepts low-momentum wakes, reducing bow waves and enhancing backflow margin.

A vane assembly merges a nozzle tube with its support platform to deliver cooling air through the spar leg.