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.