Engine Fuctions TRIZ Cases

Fixing ferrule isolates movable ring from bolted connection to prevent flange opening caused by high thermal gradients.

Segmented series-parallel stages compress fluid from low amplitude waves into high pressure, eliminating minimum wave thresholds and reducing thermal expansion.

A combined air-oil and fuel-oil heat exchanger merges cooling functions into a single unit using shared structural components.

Eliminates separate acoustic liner assembly by merging noise attenuation functions directly into the monolithic propulsion flow path duct structure.

Integral securing ribs on the guide vane segment trailing face enable peripheral locking without additional components, reducing assembly complexity.

Flexible couplings accommodate axis deviations in planetary gear trains, ensuring consistent lubrication across misaligned parts.

Segmented seal system reduces leakage by allowing independent segment movement to accommodate thermal expansion while managing stress via cooling flows.

Ceramic matrix composite turbine blades use through-thickness tows to enhance structural integrity.

Radial pivot deployment of segmented blocker doors eliminates cascade sets, reducing excrescence drag and weight while maintaining thrust reversal reliability.

Blind cavity ducts with tapered cross-sections distribute coolant uniformly on hot gas surfaces, preserving structural integrity.

A hydrogen fuel system manages fluid flow using a liquid delivery assembly and a gaseous storage tank to supply an aircraft engine.

Leakage flow guide vane assembly induces swirl velocity in fixed blade passages to align working fluid with primary flow path.

Segmented cooling passageways route air directly to turbine blade tips, reducing thermal fatigue from overheated coolant.

Reorienting leakage gas circumferentially reduces aerodynamic disturbances and efficiency losses in the primary jet.

Segmented coverplates with asymmetric bayonet tabs transmit torque while maintaining cooling paths, reducing disk rim temperature by over 37.8°C.

Axial projections on seal plates engage rotor blade roots to prevent relative rotation and eliminate coolant leakage risks.

An auxiliary wheel couples to a turbine disc to provide a dedicated surface for magnetic speed sensing probes.

A T-bushing conduit connects the inner diameter shroud to the bearing support, allowing radial motion while restricting axial and circumferential movement.

Segmented internal flow displacement elements tune modal frequencies without altering external aerodynamic surfaces or cooling channels.

A variable position valve adjusts fluid pressure and flow rates to prevent suboptimal oil flow in gas turbine engine bearings.

Double impingement rib directs cooling air along external walls to create high momentum jets, eliminating interior cold walls that increase weight.

Segmenting aerodynamic loads through a stop structure distributes pressure away from the actuation system, reducing its required strength and size.

Segmented CMC heat shields resist radial loads and thermal stress, resolving the trade-off between temperature resistance and mechanical strength.

Variable area nozzles control pressure ratios to minimize irreversible propulsive losses in gas turbine engines.

Controller-driven idle rotation extracts thermal energy via self-service expansion, preventing component degradation from thermal soak-back.

A power converting apparatus accumulates wave energy in a storage device to maintain continuous output shaft rotation.

Segmented compressor support stabilizes components, reducing rotor tip clearance variations while simplifying plumbing access.

A conductor routes igniter events from the combustion chamber to a remote sensor, eliminating costly igniter removal during troubleshooting.

Predictive matrices adjust variable-pitch stator vanes to eliminate transient overshoots, extending component life and reducing maintenance needs.

Computing device calculates inlet total air pressure using iterative mass flow and Mach number analysis.

Soyos environment clean engine converts air sand and water into mechanical energy using gravity and atmospheric pressure.

Axial operation of the seal plate restraint part resolves visual recognition challenges during maintenance by enabling phase switching from the opposite side.

Independent control of fuel-to-oxidant and exhaust gas-to-oxidant ratios stabilizes combustion while reducing NOx emissions.

Asymmetric propulsion system recovers thermal energy from exhaust gases using a dedicated heat exchanger, limiting power transients to protect the component.

Streamlined strut cross-sections suppress vortex shedding in a gas turbine bleed valve, reducing noise without the weight penalty of bulky mufflers.

Segmented porous inserts increase heat transfer and clear blockages via melting, resolving manufacturing complexity and reliability trade-offs.

A blade assembly with a loose-joint coupling secures pivot door thrust reversers.

Segmented reinforcing plates with spacing gaps disperse thermal expansion strain, preventing collision between adjacent plates while maintaining rigidity.

A gas turbine cogeneration system manages duct burner valves to enable seamless operation mode changes without shutting down the turbine.

Real-time model feedback compensates for component degradation to stabilize power output during gas turbine fuel circuit purging.

A turbine engine flange uses a V-groove and anti-rotation pin to secure mating halves without fasteners.

Replacing wax with a ceramic slurry casting core reduces baffle landing tolerances and placement variability in gas turbine engine airfoils.

Internal bosses on hollow arms support service tubes to prevent resonance and fatigue without requiring compression during assembly.

Threadless head engagement eliminates stress concentration points from threaded fasteners, preventing fatigue breakages in steam turbine control valve shutters.

Segmented ribs in gas turbine airfoil cooling passages enhance internal airflow distribution while maintaining structural integrity at high-stress root regions.

A portable switch box generates current to open valves in integrated fuel pumps without external power.

An uninterruptible power supply actuates a brake to hold the regulating valve when the controller fails, preventing downtime.

An annular casing element integrates an elastic coil damper that exerts pressure against its outer surface to dissipate vibrational energy through friction.

A gas turbine blade platform cooling system directs air through a vertical channel to seal the internal pocket.