Engine Fuctions TRIZ Cases

Baffles and apertures guide oil in a planetary reduction gearbox to cut windage and churning, improve scavenging, and lower temperature.

Independent fore and aft ring gears cut turboprop gearbox weight and complexity while reducing turbine speed and boosting propeller torque.

A planar linking member mechanically couples aircraft engine accessories to tune resonance, damp vibrations, and reduce load on the gearbox cover.

Detachable edge coupons add complex coolant passages to turbine airfoils, improving leading and trailing edge cooling with simpler casting.

A clutch and brake let a planetary aircraft-engine gearbox switch ratios in flight, improving power delivery and reducing propeller noise.

A tuned planet carrier envelope balances torque transfer, carrier stress, and weight in compact high-ratio gearbox assemblies.

Fusing 3D IMU motion data from fewer probes with spectral wave modeling enables faster, accurate real-time wave prediction.

Bearing position data is used to both levitate the rotor and detect rotating-structure damage while cutting lubricant, cooling, and friction losses.

Compressed-air cooling in a hybrid magnetic-foil bearing cuts lubricant demand while maintaining rotor support, damping, and low friction.

Sensor-guided magnetic and foil bearing support cuts lubrication and cooling demand while tracking rotor position and damage.

A deformable collar and expansion-matched spacer spread bolt loads in CMC turbomachine joints while accommodating differential thermal expansion.

Autonomous bolt tensioning cuts technician handling in wind turbines while capturing bolt tension data for safer, lower-cost maintenance.

An axially inserted wedge connector replaces heavy bolted flanges in offshore wind joints, improving preload control, fatigue resistance, and handling.

An integrated conduit and strainer feeds cleaner oil to aircraft reduction gearbox planet bearings while cutting gearbox weight and size.

Dual sliding bearings in a wind turbine nacelle absorb axial loads and tilting torque while reducing the need for extra gearbox support bearings.

Remote repair through engine access ports fills and fuses cracks in internal gas turbine components without disassembly, cutting maintenance time and cost.

A planetary gearbox couples an electric machine to gas turbine drive shafts for power add/extract modes while avoiding shutdown damage.

A second bearing between the sun gear and carrier adds radial centering, limiting misalignment, tooth overloads, and gearbox instability.

A recessed pocket and flange let curved blades fasten perpendicularly to a shaft without weak spots, preserving strength and airflow.

Balances pump energy use and liquid level stability by setting target outflow from inflow and best-efficiency flow conditions.

Pre-assembling the reduction gear, shaft, bearing support, and bearings outside the turbomachine cuts access constraints and damage risk.

External collar bearings form an oil film around planet gears, cutting aircraft reducer size and mass while supporting high loads.

Jet-fed spray bars lubricate sun gear teeth while side windows scavenge and recirculate oil in a geared gas turbine reduction.

Fused sensor, flight tracking, and operating data feed an RNN model to predict aircraft engine deterioration and reduce unscheduled maintenance.

Controlled radial and circumferential clearances let a turbine ring gear deflect under load while limiting vibration and misalignment.

A U-shaped channel fairs ring gear flanges and fasteners to cut vortex flow, reduce mechanical losses, and improve oil recovery.

Independent fore and aft ring gears reduce turbine speed and raise propeller torque with less gearbox weight and complexity.

A compound planetary gear layout filters out carrier rotation, enabling endless shaft transmission with fewer moving parts and lower maintenance.

A vertical three-layer power unit shrinks fracturing equipment for remote transport while adding muffling and fire suppression.

A two-piece ring gear with bolted shaft coupling removes spline wear, radial deflection, and churning losses in geared turbofans.

Angled deflectors redirect trapped lubricant away from transmission feedthroughs, protecting wind turbine generator-side components and easing sealing demands.

Compressor-pressure feedback drives an electromechanical valve to match gas turbine lubricant flow to load without hot-air valve jamming.

Equal torsional stiffness in ring gear mounting sections balances planetary loads, cuts tooth stress, and limits axial deformation.

A sealed plate stack uses dual barriers and hydrogen sensing to limit fluid mixing and avoid heavy double-skinned tubing in aircraft heat exchange.

Variable lubricant passage sizes in journal bearings keep upper epicyclic gear assemblies lubricated even when the gas turbine engine is stopped.

A less noble embedded anode protects steel cord belts from offshore corrosion, extending service life without added friction or costly sheathing.

A shuttle valve and reserve accumulator keep bearing-compartment oil flowing during low-G maneuvers when the main reservoir loses pressure.

Interconnected epicyclic gear sets share torque and use lock and brake control to smooth aircraft propulsion mode transitions and reduce wear.

An integrated oil sump places part of the rotor plain bearing below oil level, enabling hydrodynamic lubrication without pumps or oil lines.

A grooved bolt and inter-flange clip prevent fastener drop in blind gas turbine assembly, avoiding costly disassembly for recovery.

A profiled gutter wall converts radially ejected oil into axial flow, preventing clogging and backflow onto the turbomachine reducer.

A ramped baffle channels lubricant from sun and intermediate gear meshes to the auxiliary system and sump, reducing windage and churning losses.

Integrated oil ports and liner grooves improve thrust pad lubrication while cutting spray bar complexity, power losses, and cost.

Independent fore and aft ring gears with axial movement reduce gearbox weight and complexity while matching turbine and propeller speeds.

Unused hydrostatic pressure is converted through friction channels into steam for plasma water splitting, producing hydrogen and oxygen.

Directional clutches let the fan-driven oil pump maintain lubrication during windmilling in either rotation direction while saving package space.

Specific gear tooth roll angles help an integrated drive generator keep driven gear speed consistent despite changing engine shaft speeds.

A replaceable fitting uses a threaded connector, angled metal seal, and insertion stop to prevent generator housing damage and costly rework.

Waste heat from can curing ovens is routed through a heat exchanger and turbine train to generate electricity while maintaining curing airflow.

Brazing a cover to an open vane body creates precise cooling passages and contoured dual walls where casting falls short on geometry and materials.

Internal radial damper uses movable masses to dissipate vibrations, eliminating tip shroud weight penalties and fatigue risks.

A lockable turnbuckle uses a jam nut and pin to fix extension rod length after adjustment.

An inclined partition wall surface directs lubricating oil away from the thrust bearing to improve drainage efficiency.

A multi-axis joint connects a gas turbine vane arm to a synchronizing ring, enabling pivot movement about two perpendicular axes.

A spacer portion on a tie-spar clamps airfoil platforms using differential thermal expansion, mitigating stresses from low ductility materials.

Segmented cooling insert and bleed device route air to the hub, reducing consumption and leakage.

Counterbalanced resonance cancels reaction forces into building components, reducing structural damage during wind turbine blade fatigue tests.

Magnetic fields orient shot peen media along arcing strands inside structural guide vanes, simplifying the bonding process and resolving assembly difficulties.

A gas turbine expansion joint uses a temperature-dependent gap to enable liquid drainage between ducts.

Composite containment casing with radially inward para-aramid insulation reduces weight without sacrificing temperature resistance.

Segmented track apertures and a universal bolt lock secure a translating nacelle fanlet, enabling safe maintenance access without internal tool insertion.

A gear reduction system shifts work from the high speed spool to the low speed spool in a gas turbine engine.

Additive manufacturing creates an integral turbine casing manifold to distribute heat transfer fluid, reducing weight and improving thermal control.

An autonomous underwater vehicle deploys a cross-flow turbine with adjustable foils to reduce operation costs by eliminating heavy lift assets.

A gas turbine engine control system monitors fan and compressor speeds to prevent standing wave formation.

Adaptor housing protects oxygen sensors from thermal stress in gas turbine engines, extending longevity while enabling stoichiometric combustion control.

A turbine exhaust panel fluid scoop directs bypass cooling flow into airfoil regions with insufficient internal pressure.

A robotic air scribe vibrates a tip member at high frequencies to dislodge debris from internal cooling passages, reducing servicing time and cost.

An elastic cage shifts a rotor's critical speed away from operating ranges, reducing mechanical stress and vibration amplitudes during acceleration.

Hollow cooling channel along the outer platform leading edge directs coolant air to a trailing edge cavity.

Segmented baffles manage thermal gradients in CMC airfoils by concentrating flow at stagnation points while preventing over-cooling elsewhere.

A turbine vane shroud uses an impingement box to jet cooling air directly onto the cooling face for targeted heat removal.

Internal fluid passages in the seal runner dissipate heat via thermal conduction, eliminating external spray cooling needs.

A bleed ejector accelerates main fluid flow using an offset motive jet to increase downstream pressure ratios.

Internal cavity structure ingests and expels hot exhaust gas to maintain a laminar boundary layer along the component surface.

A blade outer air seal retention assembly uses interlocking rings with shiplap flanges to secure ceramic matrix composite components.

Additive manufacturing joins powdered metal layers to create airfoils with non-parallel ribs, avoiding microstructural discontinuities from die casting.

A rotor blade cover plate masks exhaust holes to guide hot-air flow, reducing noise and drag while maintaining de-icing performance.

Programmed inlet guide vanes adjust angles to maximize airflow and windmilling speed, enabling efficient gas turbine engine restarts in flight conditions.

Segmented blade tips with internal cooling ducts protect rubbing edges from oxidation and corrosion while maintaining sealing performance.

An axial seal system with recesses and stress relief regions reduces purge air volume, preventing hot gas ingestion while maintaining engine efficiency.

Non-zero clearance between the pin and gear rim prevents contact stress under torsional loads, improving reliability while reducing aircraft weight.

Assess remaining useful life for wind turbine support structure portions using sensor load data and sacrificial blank testing.

A gas turbine disc hub incorporates a groove to securely hold the retaining ring.

Radial blade cutter positioning near turbine roots separates airfoils from hubs to reduce fragment mass and energy.

A torque converter with a lock-up mechanism synchronizes rotational speeds, reducing starter motor power requirements.

A single-casing steam turbine uses a double-flow exhaust configuration to split steam into parallel paths across low-pressure blade rows.

Support ribs with connecting bosses integrate balancing masses to adjust resonant frequencies, enhancing rotor longevity and reducing construction costs.

Segmented baffles with tapered sidewalls convey coolant to manage extreme heat loads in gas turbine engine airfoils.

Opposing right-hand and left-hand threads linked by a connecting member prevent nut loosening without increasing axial dimension.

A ramjet booster engine oxidizes unconsumed fuel from turbopump exhaust with ambient air to generate additional thrust.

Preheating the rotor disk bore via combustor air reduces thermal gradients and prevents disk failure during rapid take-off acceleration.

Segmented flow sleeves direct cooling air radially into cavities to improve heat transfer coefficients and maintain optimal clearances in gas turbine engines.

A ducting plate coupled to a turbine vane platform forms a cooling chamber that channels air from the leading edge to the trailing edge.

A wear protection strip with recesses reduces junction wear and air leakages at the housing-shell interface.

An actuation ring adjusts circumference to control tip clearance between blade tips and the blade outer air seal.

Segmented axial sealing rings limit leakage gaps between the disk and blades, maintaining rotor integrity under high discharge temperatures.

A wind turbine nacelle cooling system uses a shared duct to transport external air across gearbox and generator heat exchangers.