Engine Fuctions TRIZ Cases

Coolant-fuel heat exchangers transfer waste heat to fuel, storing capacity in the tank to offset high demand periods.

Replacing fan duct air with cryogenic fuel reduces precooler size by three times and eliminates engine drag penalties.

Curved embossments protect seal slots from breakage during cooling insert insertion, preventing air leakage and extending component lifetime.

Monolithic additive manufacturing merges separate components into a single structure, eliminating brazed joints that cause fluid leaks and high assembly costs.

Integrating balancing mass within the turbine cover plate eliminates external flanges, reducing assembly time and manufacturing cost.

An epicyclical gear assembly drives the fan at optimal speeds, resolving the trade-off between propulsive efficiency and device complexity.

Frequency converter drives generator as starter motor to rotate steam turbine independently, reducing start-up time and improving grid responsiveness.

Merges supercritical CO2 and Rankine cycles using shared heat exchangers to reduce device complexity while maintaining high energy efficiency.

Thermal transport bus pumps normalize power and rotor diameter against fluid properties to match working fluid pressure demands with fuel flow rates.

A gas turbine vane adjusts its leading edge thickness to match upstream wake profiles.

A bleed flow power generation system extracts compressed fluid from a gas turbine core to drive a dedicated turbine rotor for electric energy production.

Segmented cooling circuits maintain thermal stability at varying stagnation points, preventing hot gas ingestion.

Segmented annular sealing portions counterbalance centrifugal loads to limit gas circulation through inter-blade cavities.

An offset flange on the planet shaft accepts a lock member to secure axial retention, preventing rotation under high force.

Friction-based braking elements dampen kinetic energy during cowl overtravel, eliminating oversized axial stops and reducing thrust reverser mass.

A jet engine combustor igniter disappears after activation to form a dedicated flame-holding space within the combustion chamber.

Rifling features inside turbine cooling holes generate nonlinear air movement to reduce flow separation and improve film cooling coverage.

Integrating a heat exchanger into the intermediate support casing reduces device complexity and production cost while maintaining oil temperature control.

Closing the bleed valve and opening the fan air valve directs cooling air into the core, reducing peak temperatures at shutdown.

Piezoelectric actuators displace a deformable nozzle portion to vary the engine outlet section area, replacing heavy hydraulic systems.

Angled and perpendicular passageways in the inlet case circulate anti-ice fluid to guide vanes, preventing ice formation without increasing engine axial length.

Varying unguided turning angles along the span suppresses hub and tip vortex growth, reducing energy losses without adding shroud weight.

Raised features on spar walls create flow pathways between coversheets, ensuring uniform coolant distribution to cavities even when inlets are blocked.

A plenum chamber directs cooling air through impingement openings to strike the inner liner surface.

Tapered feeders maintain consistent pressure across the spiral wafer core, reducing weight and power output losses in aircraft gas turbine engines.

Segmented spokes secured by a central bolt transfer bearing loads while reducing manufacturing tolerance sensitivity.

Curved shield slots mitigate stress concentrations by preventing accidental lock insertion into load slots.

Segmented locking members fix semi-floating bearings without press fit control, improving operation efficiency.

An epicyclic gear train drives a boost compressor in contra-rotation, eliminating extra support frames and reducing engine weight.

An intermediate pneumatic valve controls chamber pressure to ensure reliable closure of a gas turbine bleed valve during solenoid failure.

A fuel heater system divides fuel flow to drive a separate combustion turbine for auxiliary power generation.

Position-specific serration geometry adapts to the trailing edge contour to resolve the trade-off between noise reduction and design complexity.

Rotating the nacelle dome cover downward reduces overall height for compliant transport while maintaining structural integrity without separate covers.

A two channel transmission uses a speed variator to control rotation speeds and torques across diverse applications.

An elastic member biases a press member into an engaging recess to prevent gear slipping and jumping during angle adjustment.

An intermediate ring supports a sealing flange against disk teeth and vane roots, eliminating axial play that causes hot gas leakage.

An eductor ventilation system synchronizes motive fluid flow with engine operating modes to match cavity demand.

Dynamic filter screens deploy only where needed to prevent component erosion while preserving airflow efficiency.

Optimized variable bleed valve assemblies reduce axial length while maintaining aerodynamic efficiency by balancing bleed cavity area with exit flow angles.

A spring biased retention system maintains load spreader contact with the shroud surface to inhibit radial movement.

A hybrid resistive skin shell combines perforated metal bands with composite solid bands to form an acoustic panel for aircraft air intakes.

A split rotor blade joins inner and outer sections via a structural thickening ridge that distributes forces through double-row threaded rods.

An asymmetric keyway and tab washer constrain tie rod orientation in a gas turbine mid-turbine frame, preventing loosening without complex machining.

A flexible sleeve with airflow modifying elements wraps wind turbine blades to alter flow patterns and reduce vibrations.

Segmented threaded engagement prevents tie shaft unwinding by distributing pre-load across multiple friction interfaces, maintaining torque transmission.

Heat pipes embedded in pockets reduce thermal gradients and stress in CMC airfoil trailing edges.

Pedestal segmentation divides internal cooling passages to limit Mach number while maintaining heat transfer capacity with reduced compressor bleed air.

A cored airfoil platform uses segmented cooling passages and manifold regions to feed outlet slots at various faces for precise thermal management.

Elongated legs of an annular member traverse the epicyclic reduction gear to fix the stator, resolving space constraints in thin nacelles.