Efficient Propulsion Technologies TRIZ Cases

Movable battery holders adjust the center of gravity to reduce power consumption during flight transitions.

Segmenting the stator and rotor areas allows independent cooling near the stator, eliminating complex hollow shaft circuits.

A mechanical brake assembly limits blade pitch rotation via a stop wheel and traveler engagement.

Feedback control adjusts fuel injectors based on electric machine torque to maintain engine core acceleration within compressor limits.

A variable area fan nozzle pivots outwardly to expand the duct throat area.

A turbine shroud cooling system directs pressurized air through hollow pins and impingement plates to manage thermal loads.

Geared architecture drives fan blades at distinct speeds to reduce aerodynamic flutter and rotating mass, maintaining thrust without variable area nozzles.

Movable rectifier vanes straighten twisted reverse airflow to eliminate low-pressure depressions and improve braking distance.

Segmented turbine nozzle vanes pivot via dual actuating systems to modulate throat area, reducing actuation torque and bending loads on the vane structure.

Consolidating control functions into a single FADEC unit reduces wiring complexity and system mass.

Replacing bulky intercoolers with a refrigeration cycle reduces aircraft mass while increasing turbine power delivery.

Merges auxiliary pump with main unit to reduce mounting locations and weight while ensuring reliable lubrication for epicyclical gear assemblies.

A single actuator translates the reverser cowl to uncover cascades and vary the nozzle section, reducing nacelle mass and drag.

Casing cavity and abradable coating manage thermal expansion differences to prevent rotor blade contact during intermediate cooling.

An inclined connection region follows the airfoil camber line to reduce circumferential displacement and improve structural strength.

Polygonal reinforcement ribs distribute radial loads in a gas turbine outer ring, reducing weight while maintaining internal pressure resistance.

A fan track liner uses a gas-washed layer to retain detached blade material within the engine casing.

A flexible baffle unfolds and folds with the thrust reverser door to manage gas flow orientation.

A dual-stiffness support system secures a turbine electric machine while accommodating thermal expansion.

A flexible nacelle cowl section changes shape via a nanoelectromechanical system to control the effective boundary layer thickness.

A rotor armature winding connects to resistors embedded in compressor blades to generate heat through electromagnetic induction.

Corner brackets replace problematic composite corners in duct panels, resolving manufacturing precision issues while maintaining structural strength.

Replacing toxic chromate seals with zinc-nickel alloy flash plating eliminates hazardous wet sealants while maintaining coating integrity.