Engine Fuctions TRIZ Cases

A mounting system with a deflection limiter absorbs bending moments in planetary gear trains, preventing misalignment during high gravity turns.

A bolt thread run-out fillet radius between two and six times the thread root radius reduces peak stress concentrations.

Passageways between pressure and suction sides energize low momentum airflow to mitigate flutter in aircraft propulsion devices.

Outer guide vanes pivot to minimize drag during engine-out conditions, maintaining range and fuel efficiency in twin-engine aircraft.

A thermal transport bus transfers heat using a working fluid to manage engine thermodynamics.

A rocket engine system pressurizes and heats coolant to a supercritical state for augmented heat transfer.

A translating sleeve moves turning doors to redirect bypass gas for reverse thrust.

A valve controller determines actual minimum impulse bits from current and voltage profiles to adjust fluid flow timing.

Routes turbine exhaust and intercooler waste heat into a distillation feed heater, converting discharged thermal energy into process utility.

Helical groove and tooth configuration guide shaft rotation for precise radial tip clearance control.

Segmented firewall assemblies isolate electric motor and heat engine fire zones, preventing fire propagation between power lanes in hybrid aircraft nacelles.

Shaped bonding material interlocks airfoil tip and body portions to resolve alignment complexity and reduce assembly time.

Segmented rotor blades with progressive twist maintain power output efficiency by maximizing torque and reducing drag during operation.

Brazed sealing plate with axial tangs retains turbine blades while directing cooling airflow, reducing secondary leakage and mechanical stress at high speeds.

A transpirational flow acoustic liner draws airflow through segmented chambers to retain laminar flow over the guide vane surface.

Integrated piston bore couples hydraulic pressure to a track lock blade, eliminating separate sensors and enabling visual leakage detection.

A turbine shroud assembly uses a springless biasing apparatus to load the inner shroud against the outer shroud.

A Coanda effect fluidic device directs clearance control fluid to manage turbine tip gaps without mechanical valves.