Engine Fuctions TRIZ Cases

Coordinate-defined rib arcs relieve stress at turbine blade cooling channel turns while supporting blade lifespan and cooling efficiency.

This geared turbofan case combines fan reduction and accessory drive through one sun gear, with flexible coupling for alignment changes.

A separate damper element uses composite friction at the rotor platform to dissipate energy and reduce resonance risks.

This case uses spaced bearing supports and defined stiffness ratios to mount a high-power epicyclic gearbox fan shaft while limiting weight.

A bypass-circuit separator uses centrifugal and inertial forces to reduce cooling-air particles before they reach turbine blades.

This case uses heated fuel as a hydraulic medium to drive multiple gas turbine actuators while managing thermal degradation risk.

This turbine stator assembly uses radial sliding sectors and deflectors to reduce hot-gas heating while stabilizing rotor/stator clearance.

This case uses radial and circumferential fins plus bleed-air impingement jets to improve heat transfer without excessive airflow loss.

An insert key secures the retainer plate in a turbine blade seal assembly, reducing protrusions, windage loss, and stress concentration.

A reduced-order model combines blade displacement and operating conditions to predict damage and guide maintenance timing.

This case shows how single-sided platforms interlock CMC vane segments, easing fabrication while supporting load transfer and sealing.

Trailing-edge bump airfoils alter lift and reduce aerodynamic loads, limiting edgewise vibration and fatigue in longer blades.

Revolving blades align with fluid flow, combining rotation and revolution to improve torque generation without external control power.

Balance compact heat exchangers with effective power gearbox heat-duty processing.

A turbine uses inner and outer annular orifices with flow control to cool discs while limiting thermal expansion and vane tip clearance.

Different coating types or thicknesses across rotor sectors mistune bending modes and reduce vibratory response.

Navigation probes improve blade deformation and orientation analysis in varied conditions.

This case replaces heat exchangers and motors with compressed-air ejector cooling for gas turbine oil separation.

This case shows how a textured coating on blade-connecting tension members shares loads while reducing rotor drag and noise.

A gas turbine seal arc segment bridges vane gaps, while brush seals and cooling features support CMC airfoil sealing and thermal shielding.

An integrated heat exchanger delivers different oil temperatures to the generator and engine gearbox, reducing weight and complexity.

Interlocking sheet partitions form variable cells that adapt aircraft panel cores to complex geometries and broad-spectrum noise absorption.

A metal spar and variable-area cooling path concentrate airflow at hot spots while supporting ceramic matrix stator vanes.

This case uses compressed air and an ejector to recover oil while reducing system footprint and power demand in gas turbine recovery.

Separate cooling paths and a stator heat exchanger cool turbine components while managing pressure and limiting reverse flow.

A fuel-oil heat exchanger and modulator valve regulate return flow to manage tank temperature while maintaining combustor fuel heat.

A pylon-mounted burner and heat exchanger pre-heats cryogenic fuel, limiting icing while using engine heat and rearward exhaust.

Sensorized rolling elements update bearing life estimates from actual load conditions.

This combined-cycle configuration uses a non-condensing turbine to deliver steady steam and improve carbon capture efficiency.

A rotor-stage damper uses composite friction at the platform interface to dissipate vibration and reduce blisk resonance and flutter.

Perforated disks divide a gas turbine center plug into DDOF Helmholtz cavities for compact attenuation of 200–1,000 Hz exhaust noise.

A flexible coupling lets the ACM diffuser move axially and radially, reducing vibration transfer while heated flow prevents icing.

This case shows how a removable spoiler adds edgewise aerodynamic resistance during idling, standstill, transport, or servicing.

A melting thermal valve deploys a visible plunger when leaked hot air exceeds a threshold, helping crews find anti-ice duct leaks.

This case uses injected compressed air and an exhaust-curve bias to maintain firing temperature and reduce underfire conditions.

Fluid channels and pressurizers add co-flow jets to wind turbine blades, improving lift, reducing drag, cut-in speed, and rotor control.

This case uses a retainer and carrier to transfer centrifugal loads during aircraft rotor testing while protecting existing fasteners.

This case uses primary and secondary oil-fuel heat exchangers to cool bearing oil while heating fuel without deposit formation.

Hybrid fuel-electric control accelerates turbofan thrust response and reduces speed overshoot.

A removable blade device forms an air channel that diverts airflow and limits vortex- and stall-induced vibrations during standstill.

A multi-bend scavenge manifold uses centrifugal separation to raise oil concentration and route air away from the pump.

A ceramic coating combines HfSiO4, Yb2Si2O7, and BMAS to limit thermal cracking and CMAS-related delamination.

A coolant loop and evaporator use liquid hydrogen’s cold phase change to reject heat without large ambient-air exchangers.

A controller adjusts paravane depth and PTO impedance to protect the converter while capturing both heave-up and heave-down forces.

Flexible coupling isolates air cycle machine vibration while preserving a sealed fluid connection.

Segmented cell rows and oblique panels form resonant cavities that improve acoustic energy dissipation in aircraft propulsion panels.

This case uses transient and steady-state flight data to build a prediction model for more accurate turbomachine health margins.

A nested locking spacer and fastener fill the final disk slot, improving rotating-blade alignment and vibration stability.

This case shows how 0.5°–3° inclined rotor-segment contacts spread axial forces and reduce stress peaks in gas turbines.

A density-tuned magnetic float sinks in contaminated oil, while pressure sensing confirms fuel leaks for real-time diagnosis.