Engine Fuctions TRIZ Cases

Interconnected dual gear systems enable seamless horizontal and vertical mode transitions, optimizing torque distribution and reducing component weight.

An insert in a turbo machine blade root provides cooling pathways while maintaining structural integrity.

A geared gas turbine engine reduces fan noise by decoupling rotational speeds through a gearbox, shifting turbine frequencies beyond human perception.

Adjustable spacers in the shroud assembly maintain optimal clearance between segments and rotor blades to reduce gas leakage.

Three gates distribute circumferentially to deploy under vertical tails, resolving space constraints that block conventional two-gate designs.

A support member positions a gas turbine link away from an articulation joint, reducing lever tension and wear on moveable bleed doors.

A static sealing tip on the shroud aligns vortex rotation with the main flow, reducing high-loss mixing caused by counter-rotating vortices in axial turbines.

Virtual network models replicate high voltage distribution to eliminate safety risks and facility costs during control system validation.

Actuator ring rotates to move ring segments, adjusting turbine blade tip clearance dynamically to balance efficiency and blade protection.

Continuous thickness variation in the serration portion suppresses tonal sounds and broadband noise while maintaining lift-drag ratio.

A multicellular centrifugal pump converts fluid kinetic energy into pressurized flow to drive a remote alternator via hydraulic coupling.

Integrating actuators with thrust reverser beams enables axial centerbody adjustment without increasing nozzle wall thickness.

A two-piece clamped shroud hanger assembly transfers nozzle loads through a ceramic matrix composite structure.

Anti-ice static structure uses oil and bleed air to warm inlet components, preserving engine thrust capability.

Annular undercut and fillet in blisk rim redistribute compressive loads, preventing airfoil root separation while maintaining assembly integrity.

A compressor drive device uses a low speed pickup sensor to detect rotation speed of the low pressure side shaft during turning operations.

Nested cascade members expand radially to reverse thrust without increasing nacelle length or engine weight.

Controller manipulates turbine guide vanes using a deadband signal derived from actuator and angular positions, compensating for linkage hysteresis.

Nested ducts maintain consistent cooling air temperature across the circumference, preventing overheating in specific zones.

A turbine lubrication pump driven by differential shaft rotation actuates oil flow without external power sources.

Integrates air particle separators within turbine vanes to filter contamination from bleed gas, protecting the bearing compartment.

Pivoting thrust reverser half-assemblies lock via a six o'clock connecting beam tenon and groove mechanism.

A coking box heats oil-laden air to pyrolyze hydrocarbons into solid residues.

A controller models fuel compressibility to adjust valve positioning for precise flow targeting.

Positioning bearings on opposite sides of the gearbox increases bearing span without extending engine length, reducing load transmission to the housing.

A planetary gearbox assembly directly couples a fan-turbine rotor to an axial compressor via a sun gear and planet carrier.

A circular can-shape foundation uses cast-in-place concrete to transfer heavy loads deep into the ground.

Micro boundary layer energizers on the pressure side delay flow separation to reduce aerodynamic noise from wind turbine blades.

A compliant shaft with a flexible body connects turbine engine components to reduce assembly weight.

A variable power generator adjusts rotor-stator overlap to convert mechanical energy into electrical output.

Asymmetric interlocking structures constrain relative movement between shroud segments, reducing wear without requiring expensive rigid materials.

Metallic spars anchor ceramic matrix composite vanes, transferring aerodynamic loads while minimizing leakage and chemical interaction.

Nested inserts in a turbine blade reuse cooling air for dual-side impingement, reducing consumption by 10% and preventing low-temperature discharge.

Integrated trailer housing combines diffuser, baffles, and insulation to reduce exhaust noise while maintaining full electrical power generation capability.

Segmented fan casing rear parts retract independently while outer flaps tilt to orient airflow, increasing retraction distance despite larger engine dimensions.

A power split transmission coupling diverts hydraulic fluid to store excess energy from wind turbine rotors.

A damper control valve directs working fluid to bearing dampers via a movable plunger.

Dynamic support elements accommodate thermal expansion of the turbine casing, preserving optimal air gaps for effective impingement cooling.

A magnetorheological clutch selectively couples a bypass fan to a low pressure turbine shaft in an aircraft engine.

A lubricant tower uses a dynamic valve spool to increase flow at low speeds and reduce it at high speeds, preventing waste while ensuring reliability.

An airflow control baffle modulates cooling air through a gas turbine engine oil cooler based on temperature thresholds.

Shaped edges on cooling passage walls create varying widths to resolve insufficient heat transfer in gas turbine components.

Segmented cavity and radial channels prevent air recirculation, ensuring uniform temperature distribution in deep stator regions.

Redirection devices divert fluids from drainage holes away from ventilation apertures, preventing hazardous reentry into the engine.

Segmented pantograph hinges separate fan cowls to prevent collision and reduce weight.

A unitary turbine shroud integrates internal cooling passages and impingement openings to manage heat distribution.

A monitoring system tracks pressure transients in the starter air duct to detect degradation in the air turbine starter and valve components.

Segmented cooling paths with a pre-swirl nozzle lower fir tree temperatures and extend component lifetime without adding external coolers.

A ceramic matrix composite airfoil integrates a porous foam cooling network to distribute fluid through the blade structure.

Cutouts in the first plate reduce rigidity to minimize circumferential shaft deflections, maintaining proper gear engagement under torque loads.