Engine Fuctions TRIZ Cases

A turbine outlet temperature model predicts future values using operational parameters and fan speed to automate maintenance scheduling.

Radial protrusions on shroud bodies stagnate convected fluid, raising pressure at the clearance outlet to limit gas turbine leakage.

Segmented cooling orifices and variable fillet radius reduce fuel consumption while extending blade lifespan under high temperature stress.

Symmetric hydraulic rams maintain effector position through variable area compression, eliminating mechanical springs prone to fatigue.

A validation tab extends radially through the slash face gap to verify platform seal installation orientation.

A vacuum pump system uses a second microcontroller to determine rotor speed from phase currents, enabling reliable overspeed protection without physical sensors.

A dual low-pressure pumping assembly with a supply variator adjusts fluid flow rates to turbine engines.

Offsetting the bolt pattern from the geared architecture eliminates scallop stress concentrations while maintaining structural integrity.

A turbomachine airfoil element with tuned resonance frequencies avoids vibratory stress.

A bleed air supply system selectively routes engine gas through high, intermediate, and low pressure ports to condition airflow for environmental control packs.

Double pilot snap fit interface with resilient seal distributes mechanical loads across segmented flange components.

A stator vane platform cooling circuit uses separated plenums linked by a connecting channel to transfer heat from hot gas path components.

A three-state bypass valve manages aircraft engine airflow through dynamic position changes, reducing pressure loss to optimize stream interactions.

A sleeve mediates drive shaft rotation to enable smooth swash plate inclination, eliminating direct contact that causes severe vibration and noise.

An engine anti-ice system uses sensors and a controller to selectively inhibit heat sources on turbine components.

Replacing spline rings with journal bearings eliminates radial clearance and wear, reducing heat generation in gas turbine engines.

A flow guide structure directs steam over a casing flange to reduce resistance and turbulence.

A secondary air flow path balances pressure differentials across the rotor, reducing axial loads and operating temperatures in air turbine starters.

Bosses on the ceramic core define center plenum location and rib wall thickness, eliminating gaps that cause cooling flow turbulence.

A power electronics cooling assembly uses an ignitable fluid coolant to transfer heat from electronic components within a housing.

Calculating a flameout indicator from shaft acceleration resolves the trade-off between response time and detector reliability in harsh environments.

Redistributing cooler gas through an internal channel reduces housing temperature gradients and flow disruptions in turbomachines.