Power Installations TRIZ Cases

An integrated drive generator monitoring system tracks operating hours and guides pilot engine selection.

Segmented RAT mounting frames shift resonance frequencies away from operating ranges, reducing damage risk while maintaining lightweight structural integrity.

A rear fence on an aircraft door blocks airflow through the storage gap, reducing aerodynamic drag on the closure panel.

Electrically driven pump system eliminates manual stroking burden and reduces installation time for Ram Air Turbine stowing operations.

A fuel cell exhaust system directs pressurized gas to aircraft skin outlets to accelerate airflow and manage boundary layer conditions.

An integrated flywheel power and cooling system couples a flywheel, compressor, starter generator, and power turbine to a common shaft.

Dual spool generators feed a distribution bus to resolve weight and reliability trade-offs in centralized aircraft power architectures.

Modular mobile energy supply unit reduces on-board network load and ensures immediate availability of emergency power.

A cabin pressure control system routes pressurized air from the cabin to an auxiliary power unit core compressor inlet via a dedicated control valve.

Segmenting propulsion from power generation using solid oxide and proton exchange membrane fuel cells reduces emissions while maintaining electrical redundancy.

A cross rod features a flanged midsection for secure clevis attachment.

A controller coordinates dry motoring across multiple gas turbine engines using starter air valves to manage rotor speed.

Variable voltage operation reduces torque pulses on engine gearboxes, minimizing wear and fuel consumption during anti-icing cycles.

Honeycomb core structures reduce centrifugal forces in 3D printed ram air turbine blades, improving critical speed margins.

Hydrocarbon fuel reforming supplies hydrogen to a fuel cell, replacing heavy engine-driven generators and reducing aircraft weight.

An angled barrier divides a single seal into segregated chambers, preventing fume mixing while minimizing compressive load.

Autonomous primary controllers implement droop power curves to regulate bus voltage, reducing capacitor size and system weight in aerospace applications.

Tapered drainage mast geometry evacuates liquid from aircraft compartments, resolving negative pressure priming issues without active control devices.

An aircraft auxiliary power unit uses an electric motor to drive the compressor independently of the turbine.

A ten-phase step-up transformer paired with diode pairs rectifies AC input to form a stable DC bus voltage.

A rotorcraft uses two main turboshaft engines and a smaller secondary engine to drive the rotary wing.

Equidistant longitudinal grooves on the driveshaft reduce torsional stiffness, lowering torque ripple and peak loads on the drivetrain.