Engine Fuctions TRIZ Cases

Interlaced trip strip arrays enhance convective heat transfer in gas turbine internal cavities.

Ceramic matrix composite blade track segments attach to metallic units via interference fit and diffusion welds.

Tongue and groove brackets enable flexible movement in turbine wall assemblies, reducing internal stresses from thermal expansion.

Graded thermal conductivity in ceramic matrix composite regions manages temperature gradients, minimizing thermal stresses and extending component life.

Oxygen filtration and high-pressure water injection reduce nitrogen oxide emissions and compressor load consumption.

Segmented blocker doors pivot via rigid linkages to hide components in the stowed position, reducing flow disturbances within the bypass duct.

Flexible connectors reduce hoop stresses in modular tower sections, enabling taller towers while easing transportation logistics.

Parallel venting valves prevent oil leakage during seal failure by maintaining positive pressure differentials across gas turbine engine bearings.

Integrated radial lugs with ventilation orifices guide cooling air to contract the housing, eliminating spacer gaps that cause leakage.

Motorized pulleys collapse the tower structure, reducing visual impact by 80% and lowering transport costs.

A drive assembly uses a flexible lever arm to transfer wave energy captured by a buoyant member to an energy converter.

A wind turbine calibration system updates its reference power curve using real-time performance data to maintain accurate operational baselines.

Circumferential tab on fan platform resists twisting forces to maintain cylindrical shape.

Thermographic imaging calculates airflow performance scores for turbine blades, identifying blocked holes that cause excessive heat exposure.

Anti-ice air flows through an inlet guide vane cavity and exits overboard.

A stator vane ring uses a pressing unit to apply radial pressure against shroud segments, securing the vane group in place.

An actuating handle moves a connecting rod along a slotted groove to accommodate varying nacelle circumferences without custom parts.

Monitoring rotor speed acceleration and tower vibration identifies asymmetric icing without adding sensors, reducing installation costs.

A recirculation system uses a fan to direct fuel-free exhaust gases into a mixing chamber, reducing unburnt fuel concentration in the engine exhaust stream.

Flexible elastomeric fairings cover joint gaps and absorb wind-induced warping, reducing noise and weight while ensuring lightning protection.

Chaotic double pendulum arms drive a generator to produce electric power from sea waves while overcoming cogging torque and reducing maintenance needs.

Petal-shaped nozzles enhance turbulent mixing of hot bleed air with circulating air in the D-duct, reducing total pressure losses and eliminating hot spots.

Mechanical keying secures ceramic matrix composite airfoils, enhancing load capacity and resisting thermal degradation.

A turbomachine actuator monitoring system detects deviations between dual cylinder position feedback measurements to identify mechanical wear.

A waste heat recovery system converts exhaust thermal energy into mechanical work using a supercritical carbon dioxide cycle, reducing thermodynamic loss.

Press fit centers inner housing radially to improve seal-bearing structure roundness and reduce leakage.

Heat pipes transfer thermal energy from a source to nacelle acoustic panels, extending heating distance to prevent ice blockages in short air intakes.

A mount assembly uses a laterally movable pin body and spring to attach a heat exchanger.

A pump flow rate estimation method uses two downstream pressure sensors to calculate output without external meters.

Radar sensing elements transmit radio waves to detect component characteristics and identify mechanical failures in aircraft gas turbine engines.

Idle rotation expands hot combustion products to drive the spool, removing residual heat and preventing component degradation caused by thermal soak-back.

A wind turbine cooling system calculates ambient liquid water content using operational efficiency data from existing heat exchangers.

Machining internal channels into partially densified ceramic matrix composite preforms enables integral cooling circuits that survive full densification.

Auxiliary lubrication system supplies rotating components via a bi-directional pump during windmilling or primary failure.

Segmented slotted apertures in a movable turbine blade damper improve cooling uniformity while reducing the total quantity of coolant required.

Lubricant injection into a collection cavity evacuates energy dissipated at spline contacts, accommodating thermal expansion.

Embedded anchoring openings transmit axial loads between steel and concrete tower segments, eliminating geometric stress concentrations in thin-walled designs.

Adjustable inlet guide vanes regulate airflow to maintain optimal rotor speed during cool-down motoring, preventing bowed rotor conditions.

A ring segment cooling system with elongated passages directs cooling air along the inner circumferential surface to prevent thermal damage.

A gearbox flapper valve seals the manual rotation access passage to prevent lubricant escape from the outer housing.

Variable inlet guide vane portions adjust bypass airflow to enable power transfer between shaft and fan loads in gas turbine engines.

Thin-wall sectors and quadrilateral arms absorb shearing forces to resolve load maldistribution in single-piece epicyclic gearing.

A geared gas turbine compressor uses a specific vane-to-blade ratio to alter fluid dynamic interactions and reduce acoustic emissions.

A wave-direction-adaptive convertor uses multiple water channels to focus incident waves and double particle movement amplitude for enhanced energy capture.

A ramped flow conditioner aligns leakage and coolant streams with the main gas path to reduce aerodynamic losses.

A planetary gear speed change mechanism transfers torque between fan and turbine sections using integrated bearing support.

Tapered part-span shrouds reduce structural stress and aerodynamic drag by minimizing weight and contact surface areas via localized parameter changes.

Multiple stiffeners reinforce the variable area fan nozzle cowl, increasing flutter margin against tonal and broadband aerodynamic loads.

Segmented dovetail platforms and pins distribute centrifugal loads on ceramic blades, resolving thermal expansion stress.