Turbine/Propulsion Fuel Control TRIZ Cases

Blending Wf/P3 ratio and N-dot fuel commands stabilizes gas turbine startup and thrust increases while avoiding hanging acceleration.

A blended Wf/P3 ratio and N-dot fuel command prevents hanging accelerations while preserving safety limits and repeatable gas turbine response.

A two-step IGV and fuel-rate strategy keeps exhaust flow uniform to protect SCR operation and maintain emissions compliance at low gas turbine loads.

Automatic misaligned power control shifts load after one rotorcraft engine fails, holding rotor speed and limiting emergency power use.

A relative fuel ratio limit uses pre-surge values and bias control to stabilize gas turbine surge recovery despite sensor error.

A relative fuel ratio limit uses pre-surge RU and a bias value to cut fuel flow during compressor surge and stabilize gas turbine recovery.

Distributed strain sensors along the isolator duct track shock train position in real time to prevent ramjet unstart and reduce stress.

An automated optimization algorithm uses operating, environmental, and historical data to keep gas turbines within stability and emission limits.

This case combines variable displacement pump control with one valve for high-pressure relief and windmill bypass operation.

A gas turbine control method adjusts variable compressor inlet guide vane positions and inlet temperatures to optimize electricity production costs.

Regulating compressor discharge pressure prevents outlet instabilities and maintains constant turbine power during load changes.

Controller detects combustion instability frequency, coherence, phase, and amplitude to adjust fuel flow parameters.

Dynamic variable inlet guide vane scheduling adjusts propulsion system operation based on real-time fuel characteristics.

Real-time feedback adjusts torque distribution to synchronize engine performance margins, reducing combiner transmission stress and uneven degradation.

Accelerated fuel flow recovery schedules reduce engine deceleration and prevent surge recurrence after detection.

A gas turbine control method adjusts stator vanes and opens anti-surge valves to manage fuel flow during load changes.

Dynamic compensation synchronizes fuel, air, and water mass flow changes at the combustor inlet, preventing flame instability during rapid transient operations.

A control device regulates compressor discharge pressure using feedforward and feedback mechanisms to stabilize fuel gas supply systems.

Discrete fuel pulses vary rotor speed to generate mechanical shocks that dislodge ice from compressor blades.

Segmented fuel injection across convex sections, cavities, and downstream zones ensures complete combustion to generate sufficient propulsion force.

A digital system compares controlled and reference pressure signals to estimate time to compressor surge.

A gas turbine control device adjusts fuel and airflow rates using load sensitivity coefficients to maintain ideal operating conditions.

A control system calculates pressure drops across can combustors to adjust fuel flow rates and maintain consistent combustion conditions.

A computing device issues input signals to a combustion system and adjusts fuel ratios using dynamic step changes based on real-time sensor data.

Feedback control aligns gas turbine output with nominal power targets while reducing firing temperature variation caused by measurement uncertainty.

A nonlinear predictor compensates for fuel flow rate changes to track acceleration limits, reducing safety margins and improving engine capability.

Dynamic inlet guide vane limit correction reduces exhaust gas temperatures during output increases, improving power generation efficiency.

A control system maintains a supplemental engine in a reduced power state until total drive system demand requires additional output.

A fuel flow determination device sets a lower limit for fuel supply during reverse power operation.

A gas turbine controller adjusts air and fuel mass flow rates using model-based parameters to manage compressor surge and lean blowout limits.

A gas turbine energy recovery system uses a low-pressure turbocharger to power air blowers that increase compressor inlet pressure.

A steady-state air versus fuel model coordinates combustion supply signals.

An accelerometer coupled to a turbine engine detects axial acceleration indicative of a shaft shear event, triggering immediate fuel system shutdown.