Engine Fuctions TRIZ Cases

Axial oil injection through an annular port boosts centrifugal lubrication in planetary gear bearings while avoiding impeller clogging and shaft interference.

Unequal oil supply to compressor- and turbine-side bushings shifts film viscosity and natural frequencies to improve rotor stability and NVH.

Integrated pinion nozzles use centrifugal force to deliver lubricant at the gear mesh, reducing jet deflection and excess oil use.

Nested epicyclic stages let a turbomachine gear assembly handle counter-rotating inputs, reach high gear ratios, and stay within engine size limits.

Three independently actuated pistons give an aircraft anti-ice PRSOV redundant shut-off and pressure regulation without the weight of dual valves.

Periodic web geometry aligned with gear teeth reinforces tooth roots, raising stiffness and load capacity without adding unnecessary weight.

High-rate shaft speed sensing and counter-torque damping suppress torsional resonance in gas turbine engine spools to extend shaft life.

Localized tensile stress zones steer cracks from critical loading areas into safer regions, avoiding added thickness, weight, and efficiency loss.

High-precision timing and dynamic averaging improve turbine speed sensing at low speeds while avoiding false shutdowns from load unbalance.

A sealed housing and dual plate assemblies isolate hydrogen from a secondary fluid, reducing leakage, mixing, and double-wall circuit needs.

Balanced compressor and expander placement on opposite pinions cuts thrust imbalance, simplifies sealing, and lowers mechanical loss.

A high-conductivity rib element draws heat from CMC airfoil walls to cut thermal gradients and reduce thermally induced stress.

A dual-diameter planet gear layout raises aircraft turbomachine reduction ratio while limiting planet moments and radial bulk.

A contoured planet pin preserves gear rim clearance under torque, reducing wear and maintaining lubrication in turbine engine gearboxes.

Rows of openings between adjacent oil basins balance turbomachine lubrication, preventing overflow, unbalanced mass, and vibration.

Fluid pressure deforms a compliant flow path to hold flow rate constant, replacing complex valves and improving test reliability.

Starting uses heated supercritical fluid and venting instead of a high-speed motor, while staged cooling slows shutdown and protects bearings.

Internal layshaft passages route lubrication lines through the gear assembly to cut gearbox footprint, improve oil distribution, and reduce windage losses.

A fixed-axis gear train replaces epicyclic gearing to improve turbofan mechanical efficiency and enable rigid housing mounting.

Axial oil injection into an annular impeller cavity raises lubrication pressure, improves bearing oil distribution, and avoids nozzle-shaft interference.

A rotatable stop member secures a flanged hub in operation, then applies axial disassembly force to cut maintenance time and stress.

Axial lubricant pockets and circumferential grooves improve plain-bearing film formation in wind turbine planetary gears at low pump pressure.

A partial arc gutter captures oil slung from the seal plate, drains it efficiently, and reduces churn-related heat in gas turbine bearing compartments.

Frustoconical flanges form annular oil cavities in a turbomachine reducer shaft to improve cooling, lubrication, and oil evacuation.

Rectangular radial fins reshape the tower boundary layer to suppress vortex-induced vibration in tall conical wind turbine towers.

Continuous sensor data and load skewness analysis replace fixed service schedules, improving gas turbine maintenance timing and availability.

Local and global gutters capture oil flung from epicyclical gears, limiting accumulation, churning, and windage loss in turbine gearboxes.

Longitudinal pin-guided intermediate hinges let long fan cowls be assembled, opened, and removed more easily for nacelle maintenance.

Helical journal pin grooves separate hot and cold oil in planetary gear bearings, cutting frictional loss and thermal seizure risk.

A defined interference-fit range helps turbine gearbox journal pins resist fan-drive torque without slippage or plastic deformation.

A circumferential nozzle delivers controlled airflow to cool gas turbine rotor stacks faster without disturbing roundness and squareness during assembly.

A single plate with aligned holes links multiple oil lines through one cavity, cutting transmission assembly errors and production cost.

A shaped recovery trough redirects radially ejected gearbox oil into axial discharge paths, reducing clogging and oil return in turbomachines.

Semicylindrical resilient bodies fold for easy tube insertion, then expand into a snug seal that blocks debris during assembly or maintenance.

Dual ring gears and split planet toothings raise turbomachine gearbox reduction ratio without increasing overall dimensions.

An elevated gravity rundown tank supplies backup lube pressure during pump switchover, avoiding separate accumulators and unnecessary trips.

Porous ceramic layers and machined fiber batting cool high-temperature panels while cutting weight and preventing surface distortion.

A variable-force latch holds an aircraft generator disconnect in the open state under vibration while still allowing later reconnection.

A porous ceramic composite panel uses transpirational cooling and ceramic stitching to cut weight, thermal stress, and surface distortion at high temperatures.

Triple-toothing planet gears cut turbomachine transmission mass and size while preserving flexible dual-output torque paths.

A bonded nickel-chromium-molybdenum insert in a repair slot helps curb thermal-stress cracking and extend turbomachine component life.

Multiple rings, swirl vanes, and serrations stage pressure drop inside a gas turbine bleed valve to cut venting noise.

A switchable planetary gearbox changes pump ratios without a torque converter, cutting waste heat and handling variable fracing torque.

Optical scale markings and image processing enable repeated ring gear-pinion backlash checks, helping track wear and plan timely wind turbine maintenance.

A cavity-inserted retaining member secures engine components without bolt seizure, reducing radial movement, weight, and assembly time.

Flexible shaft sections let floating sun gears self-align radially, balancing planet gear loads while reducing gearbox size, weight, and wear.

Vertical ribs segment liquid motion in a toroid tower damper, preventing rotational modes and maintaining low-frequency damping during use and assembly.

Multiple damping fluid films in separate bearing cavities broaden vibration-mode damping across turbomachine shaft speed ranges.

Electromagnetic support impedance counters shaft radial motion in real time, cutting critical-speed vibration and bearing wear.

Unexpected sensor data from one aircraft test is reused with analytic models to expose cross-system effects and coverage gaps.

Radial fluid routing minimizes temperature differences across the rotor disk, extending cycle fatigue life under high pressure ratios.

A porous metal seal with a protective shell manages oil leakage at rotating shaft interfaces.

A frequency modulated continuous wave radar system scans wind turbine blades using synthetic aperture analysis to generate focused images.

Radial slits in the cooling sleeve reduce mechanical stress on the bearing while maintaining thermal conduction to the housing.

Retaining ring with lower thermal expansion coefficient secures aircraft engine components against support flange.

An electrically powered fan adjusts cooling air pressure and flow to resolve inefficiencies caused by fixed area designs in gas turbines.

Segmenting core flow around a recuperator recovers exhaust heat for fuel heating while maintaining propulsive efficiency.

A fabric damper sheet and rigid plate assembly dampens exhaust duct vibrations.

Carrier scoop directs lubricant through passages to spray bars, ensuring effective lubrication under high loading conditions.

A blade outer air seal assembly uses cooling passages and a thermal barrier coating to manage heat loads.

An active clamping system uses sensors and actuators to dynamically adjust clamping force on wind turbine blades during transport. This approach prevents slippage from vibrations while avoiding compressive damage to the blade structure.

Hollow turbulence generators on a curved baffle wall create localized mixing to boost oil cooling efficiency while minimizing pressure losses in the airflow.

Tower-mounted acoustic sensors feed spectrograms to ML models, resolving reliability and complexity trade-offs in wind turbine maintenance.

Integrated inlet air heating coils use hot water from the power plant to warm gas turbine intake air.

A sensor and controller system calculates compressor bleed valve operational values from sensed parameters to enable predictive maintenance.

Notched elongated fasteners engage locking rods to distribute pulling forces across the composite thickness, resolving root connection strength limits.

Monitoring water pressure and quantity in a hydrogen turbine recovery loop reduces heat loss by ensuring optimal steam injection.

Embedded colored strips in abradable liners reveal wear patterns to prevent premature replacement costs during harsh operating conditions.

A geared fan assembly gearbox couples a fan rotor and booster rotor to independent transmission paths within a single structural housing.

Sintered electrographitic carbon bushings prevent composite delamination at high temperatures, maintaining vane angle accuracy and extending component lifespan.

Oil-based thermal management cools pressurized air and heats flow air without bleeding engine airflow, preserving thrust.

Asymmetric ear configurations and centering pins decouple bolt loads, preventing seizing under high temperatures.

Dual strut attachment configuration distributes loads across multiple paths to mitigate axial and torsional deformation under aerodynamic forces.

Buffer manifold directs air between seals to reduce pressure drop and prevent lubricant leakage.

Modular chambers absorb acoustic energy at specific frequencies to mitigate fan flutter.

Accumulating lubricating fluid in the seal gap creates hydraulic pressure that prevents leakage into airflow streams, resolving complexity trade-offs.

A hybrid nozzle segment assembly combines ceramic matrix composite fairings with metallic struts to support gas turbine engine components.

Opposing discharge passages in a dual reservoir system maintain uninterrupted lubricant supply during sudden engine attitude changes.

A self-lubricating carbon lattice element creates a liquid film between rotating and stationary seal components.

Segmented fittings with angled sealing faces prevent housing damage from manufacturing errors, avoiding costly rework.

Dynamic heat dissipation ratios between air and fuel lubricant exchangers minimize energy waste while preventing fuel thermal degradation.

Heat exchangers recover expander cold energy to cool compressor oil, eliminating external cooling needs.

A conical feed ring channels lubricant through a circumferential gap to gear coupling teeth, preventing insufficient flow in planetary transmissions.

Spacers positioned between washers and the hub surface distribute contact pressure, preventing washer embedment and maintaining bolt integrity.

Riveting-free insertion into pre-formed recesses resolves production complexity and vibration risks.

Circumferential bore hole orientation reduces thermal pinching stresses and improves hot gas path sealing efficiency.

Offset metal sheets bridge sleeve-shaped pressure pieces to establish electrical continuity between segmented rotor blade sections.

Angled panels extending from the tower surface utilize ambient wind flow for passive heat dissipation, eliminating powered fans and reducing operational costs.

A control system manages antisurge valve position during turbocompressor startup to minimize energy consumption.

A turbine shroud assembly uses a compliant mounting system to secure ceramic matrix composite blade track segments to a metallic carrier.

Dual pumps on the fan shaft supply lubricant to gearbox components, ensuring reliability during windmilling.

A gas turbine support strut assembly uses a ball pivot element and elastomeric damping to maintain stable casing support.

Optimizing the turbine outlet to inlet area ratio between 2.5 and 3.5 enables power extraction exceeding 38,000 horsepower.

A wind turbine coupling configuration transmits torque while absorbing bending moments using conical bearings.

Internal flow modifiers in a gas turbine coolant channel adjust local pressure at apertures to balance cooling effect against engine efficiency.

A thrust-vectorable rocket nozzle uses mechanical locking and flexible shear plies to retain insulation.

Annular finger seal uses cooling holes and a fillet to direct airflow onto the flow path platform.

Decreasing the plenum outer wall radius increases airflow rotational speed, separating particles via centrifugal force while minimizing pressure loss.

Segmented cooling passages with low friction regions and chevron turbulators reduce supply pressure requirements while enhancing heat transfer.