Engine Control TRIZ Cases

Central pressure sensing and adjustable outlet ports let one pump control multiple vehicle cleaning lines without separate flow sensors.

Independent sub-turbine controllers regulate power, pressure, and thermal stress to keep steam turbine operation flexible under changing conditions.

A linear motor or solenoid lock member blocks thrust reverser motion, replacing heavy hydraulic locks with a lighter, stronger load path.

Flow stabilizers in a thrust reverser cascade block vane-to-vane gas flow to suppress acoustic feedback and reduce reverse-thrust noise.

Dewpoint-based steam measurement lets compressor surge control adapt within seconds to gas composition changes without slow gas chromatography.

A sonic choke passively fixes gaseous propellant flow in a rocket motor feed line, reducing pump complexity while keeping combustion ratio stable.

Fluid-pressure inflatable diaphragms and hinged panels vary jet nozzle area at cruise while cutting actuator weight and mechanical complexity.

Capacitive dome sensing with adjustable thresholds helps vacuum-primed pumps avoid false prime detection when debris coats the chamber.

Variable extraction and inlet injection recirculate outlet flow to prevent compressor stall and hold outlet pressure during deep turndown.

Fluid-pressure diaphragms adjust jet nozzle area without heavy actuators, cutting engine weight and mechanical complexity.

Inflatable diaphragms and hinged panels adjust jet nozzle area with fluid pressure, cutting actuator weight, complexity, and cost.

Inflatable diaphragms replace bulky nozzle actuators, cutting gas turbine engine weight and complexity while controlling effective area.

Separate fuel and oxidizer gels enable self-igniting underwater propulsion with thrust control, safer storage, and compact high-speed operation.

Electrical drive signals estimate dynamic-compressor surge margin and detect precursors without mass-flow meters or vibro-acoustic sensors.

Changing water vapor can destabilize compressors; dew point mirror sensing rapidly shifts the surge control line without full gas chromatography.

One controller manages the VFD and engine, automatically shifting pump drive on communication failure for seamless operation.

Temperature-fan and current-fan speed tables tailor each fan’s rotational speed to sensed area temperature, limiting energy waste and resonance from mismatched fans.

This case replaces heavy hydraulic thrust reverser locks with a compact linear motor or solenoid mechanism.

This case uses separate neural networks and selected historical features to detect fan failure while limiting memory and compute overhead.

This case infers compressor operating point and surge margin from motor current, voltage, power, torque, and speed.

A turbine control device calculates actual load capacity using analog signals from governor valve position sensors.

A pump controller switches between parameter-based and continuous modes to maintain consistent liquid pressure.

A fan method calculates volumetric flow using motor internal variables and an algorithm.

Constant rotary shaft speed decouples responsiveness from moment of inertia, boosting frequency from 0.2 Hz to 6 Hz for vertical landing.

A segmented anti-surge system coordinates a single backflow valve across multiple compression stages to maintain stable gas flow.

Relative position sensing determines instantaneous cowl location, maintaining system availability after power interruptions.

A control system reduces closing force on a valve actuator to minimize dead time and enable rapid anti-surge response.

Segmented parallel valves reduce actuation forces and flow losses by switching between rotary slide and control valve modes.

A safety apparatus for extraction steam turbines detects casing pressures and throttles main steam flow to reduce rotor thrust force.

Frequency converter estimates fan rotational speed and torque to identify stall conditions without external sensors.

Autogenous pressurization using a thermoelectric generator eliminates heavy inert gas tanks, reducing rocket engine weight and complexity.

A hybrid liquid-propellant engine uses a gas turbine and generator to power electric pumps for fuel and oxidizer delivery.

A multi-lobed bullnose ramp uses a profile discontinuity to induce bypass flow separation and reattachment.

A compressor instability indicator uses skew analysis of upstream pressure fluctuations to detect surge limits before damage occurs.

An axial flow control mechanism in a three-stream turbofan engine adjusts bypass area to resolve the trade-off between fuel efficiency and thrust production.

A variable geometry nozzle control method detects individual flap states to adjust functional actuators beyond nominal positions.

A moveable combustion control member regulates solid fuel exposure to fluid oxidizers in hybrid rocket motors for precise thrust management.

A variable area bypass mixer adjusts the bypass ratio via a translatable sled, resolving fixed geometry limitations in gas turbine engines.

A magnetostrictive sensor measures torsional vibration and torque on a turbomachine shaft without external power or direct mounting.

An integrated electromagnetic valve reduces switching time and actuation force in mechanically controllable coolant pumps.

A computer-implemented method classifies compressor stall precursors by comparing data sets and removing mean values to determine correlation factors.

A rocket engine control device adjusts thrust setpoints based on electrical power availability to optimize energy usage.

Dynamic nozzle adjustment creates backpressure to limit turbine speed, reducing engine weight and cost while maintaining thrust.

Voltage threshold detection replaces complex ARINC 429 decoding, reducing local control module complexity and cost.

A high-pressure bypass control system adjusts valve opening degrees dynamically to manage steam flow and pressure in 660MW supercritical units.

A variable speed pumping system detects blockages and performance changes through real-time sensor monitoring.

Segment-based control of dual feed valves compensates for pump variations to maintain stable mixing ratios across operating points.

A flow control device adjusts the fan nozzle exit area to actively manage axial thrust loads on a geared turbofan engine bearing.

Bang-bang control commands drive slow rocket engine actuators using threshold-based inhibition logic.

A turbopump system sheds secondary propellant flow upstream of the turbine to regulate rotational speed and maintain power balance.