Engine Fuctions TRIZ Cases

Machining the oil manifold into the bearing housing simplifies assembly and repair while enabling flexible oil jet placement and less rotor interference.

Varying fiber orientation and density across shaft regions improves torque transfer, axial stiffness, and vibration behavior with less weight.

Separating long-term deterioration from short-term tuning in gas path analysis improves gas turbine parameter estimates without adding sensors.

Axial protrusions on planet gear faces redirect bearing oil away from recesses, cutting oil buildup, imbalance forces, and power losses.

Higher static pressure lets a gravity rundown tank bridge main-to-standby pump switchover and replace separate accumulators.

An output-side clutch lets the transmission handle constant-torque aircraft accessory loads with less size and weight than input-side layouts.

A curved auxiliary oil tank uses gravity-fed oil recovery to keep the aircraft engine reducer lubricated during windmilling.

A spring-biased tine finger delays lock sleeve relocking until the lock shaft returns, preventing false locked signals in actuator systems.

A bleed-line jet pump shifts a spool to vent header tank vapor, prevent fuel pump cavitation, and avoid a separate bypass line.

A sacrificial mechanical fuse in the auxiliary mounting bracket absorbs fan blade out shock loads and keeps the component attached to the engine case.

Predicted wind farm operating states are compared with user-driven conditions to flag unauthorized access and enable faster response.

Groove and slot feed paths redistribute lubricant around the journal bearing-rotor interface to maintain film consistency and limit cavitation.

By tuning midshaft rating, shaft structure, and gearbox mode spacing, this case raises critical speed and limits whirl instability.

Integrated axial bores and recessed sprinklers improve aircraft turbomachine gearbox lubrication while reducing leakage risk and assembly complexity.

Modular oil distribution modules feed lubricant into a rotating planet carrier, improving reducer lubrication reliability while simplifying assembly.

A lightweight ML forecast lets wave energy converters tune resistance ahead of changing seas, boosting output and reducing wear.

An internal squealer tip cooling channel cuts blade tip thermal loading while using less cooling fluid and preserving gas turbine aerodynamics.

A flexible airflow manipulator mounted on a tower segment redirects wind flow to reduce vortex shedding, resonance, and erection-phase vibration.

Axial high- and low-pressure grooves transfer oil through plain bearings to lubricate planet carriers while limiting leaks at high pressure.

Gear-directed lubricant passageways cool and protect air turbine starter bearings, reducing heat and wear to extend operating life.

A sleeve-controlled traveling finger lock cuts thrust reverser lock weight and complexity while preventing accidental deployment and fatigue.

Hard-particle friction layers plus sealing block seawater washout, keeping rotor shaft and hub joints backlash-free under torque.

Circumferential lobes reinforce the shaft-flange joint, spreading loads to cut stress concentration, bending moments, and vibration.

Adaptive BOAS positioning and climb thrust control balance efficiency, fuel use, noise, and engine life across operating modes.

A compound epicyclic gearbox cuts angular misalignment loads in turbofan fan drives while preserving the required speed reduction.

Lubricant is routed to the most heavily loaded slidable tooth elements in an eccentric-cam transmission to reduce friction, parasitic loss, and gearbox mass.

Separate annular scoops split oil flow between seal-track cooling and bearing lubrication, reducing leakage risk and improving compact turbine-engine sealing.

A gearbox links offset thrust reverser actuators to transfer torque, fit tight packaging, and prevent disproportional movement.

A guided cut-and-plug repair restores honeycomb panel strength and acoustic performance without foam blocking cells or forcing part replacement.

Selective check and dump valves route intercooled compressor air to turbine components only when needed, preventing surge at low power.

Large bladed rotor point clouds are reduced to relevant section data, speeding transfer, damage analysis, and repair blend decisions.

Correction factors align onboard and aero-thermal models to improve synthesized gas turbine engine parameter accuracy across operating conditions.

Mounting accessory equipment on the planet carrier lets planet gears drive rotors, saving nacelle space while increasing onboard power.

A gutter windage blocker builds upstream pressure and a downstream vortex to recirculate wept oil into the drain hole.

Integrated oil-pipe passages in a one-piece satellite carrier simplify reducer assembly while cutting weight, cost, and lubrication complexity.

Axial oil injection feeds an annular impeller cavity to improve planet bearing lubrication while reducing shaft interference and oil use.

Integrated oil ports and liner grooves improve thrust bearing lubrication while cutting part count, power losses, and bonding demands.

A hybrid sandwich and SPF/DB structure forms tight-radius, reduced-width titanium panels without core crushing, wrinkling, or pan-down deformation.

Variable-depth sinusoidal cooling channels mix stratified propellant, improve wall heat transfer, and reduce turbopump pressure demand.

Acoustic striking and noise analysis automate wind turbine flange fastener inspection, cutting manual effort, errors, and maintenance time.

Two independent hydrodynamic bearings guide each planet gear to cut axial size, oil flow, and power loss while preserving load capacity.

Integrated blade stages in one flow pipe raise small hydropower output while cutting installation time, weight, and maintenance effort.

A segmented baffle redirects secondary air-oil flow around turbine gears to limit oil impingement, cut windage heating, and improve scavenging.

PWM air switching smooths standby-to-active engine transitions, enabling asymmetric cruise operation with lower fuel use.

Hydrodynamic added mass is separated by spring or damper elements to cut low-frequency vibration in submerged structures without foundations.

A dual attachment pin assembly secures gas turbine shroud segments to hanger assemblies using interference fit and nested sealing elements.

A dual-walled gas turbine component structure uses chemical etching to form support structures and cooling channels between a hot section part and a cold section part.

Variable-thickness slot wedges modulate radial channel resistance to distribute cooling air evenly, preventing local overheating in wind turbine motors.

Segmented radial guide portions draw cooling gas into the exhaust swirl, improving mixing efficiency without increasing structural complexity.

A mechanically assisted starting system uses an overrunning clutch to transmit motive power from the aircraft transmission to the compressor drive shaft.

Scoop channels transform turbulent flow into laminar orientation upstream of blades, reducing tip vortices and flutter in gas turbine engines.

Spring-biased dual spools maintain stable oil pressure during negative-g events, preventing unnecessary bypass opening and reducing recovery time.

Homogeneous Inconel construction with integrated rim-to-blade cooling channels reduces differential expansion risks while maintaining high thermal resistance.

A closed-loop anti-icing system circulates a phase-change fluid to transfer heat from bleed air to engine surfaces.

Bottoming cycle uses cryogenic fuel as heat sink to recover exhaust thermal energy, overcoming limited working fluid heat acceptance.

Integrated wedge plies prevent delamination at narrow neck fillets by distributing interlaminar stresses through radial and transverse fiber orientations.

Segmented thermal protection sheet engages anti-rotation pins via alternating tabs to prevent disengagement and housing wear.

Ejector mixes core motive flow with low-pressure heat exchanger exhaust to match bypassed stream pressure, resolving thrust loss from thermal recovery.

Porous nacelle walls dissipate acoustic energy as heat, eliminating bulky honeycomb panels and complex active noise control systems.

Oscillating planar sails on a vertical shaft capture low-speed wind energy while minimizing acoustic disturbance and enabling self-starting operation.

Differential oil injection compensates for centrifugal pressure gradients in turbojet bearings, reducing wear and improving energy transfer efficiency.

Locking plates and seal rings secure service tubes in gas turbine platforms, preventing airflow leakage and thermal transfer.

A turbine blade tip cavity ejects high-velocity cooling medium through a trailing edge hole to enhance convection.

A diaphragm mixing chamber directs purge flow through inclined exit passages to induce parallel velocity components.

Replacing gas generators with an electric motor reduces launch weight and energy loss, while propellant circulation prevents overheating.

Soft sensors estimate turbine inlet temperature while anomaly detection prevents erroneous manipulated variable settings during operational transitions.

Varying heat exchanger length along the height direction reduces drag penalties while maintaining heat exchange capacity in propulsion systems.

Segmented axial bores in a cooled rotor disk reduce hoop stresses from centrifugal loads while supplying cooling air to the last turbine blade rows.

Interlocking elements on the shaft and bore restrain angular movement to eliminate fretting corrosion and premature wear in wind turbine generators.

A solid bore turbine disc design eliminates outboard fasteners to reduce weight and part count in geared turbofan engines.

Varying orifice density in a gas duct noise attenuation panel optimizes acoustic resistance, solving broadband noise issues without heavy components.

Segmented air and fuel lubricant heat exchangers manage gearbox heat, reducing fuel thermal degradation while improving specific fuel consumption.

A method interpolates compressor performance data using lines of constant exit corrected mass flow.

An autonomous robot inspects hollow wind turbine blades by modifying internal fluid pressure, enabling rapid defect detection without prolonged shutdowns.

A bifurcated fan shaft assembly couples inner and outer shafts via a contact mechanism to restore load paths.