Efficient Propulsion Technologies TRIZ Cases

Integrated overmolding merges frame and vane fabrication into one cycle, reducing manufacturing complexity while maintaining aerodynamic performance.

An internal light source reflects off the sensor window to distinguish contamination from a genuine flame-out condition.

A single rotor dual stator electric machine reduces weight while maintaining reliability by eliminating single-point failures in redundant power systems.

Flexible load spreaders intercept pin forces and distribute them over the shroud, preventing stress concentrations caused by differential thermal growth.

Drain assembly accommodates radial and axial displacement to prevent fuel pooling and maintain structural integrity.

Counter-rotating assemblies generate air friction to produce heat, eliminating complex bleed air systems and preventing ice damage.

Sandwich plates secure damaged exhaust sleeve edges with spaced rivets, avoiding honeycomb damage and maintaining structural integrity.

Adjustable radial shims constrain flange positioning accuracy to prevent thickness defects while allowing continuous mandrel rotation.

A fairing mount and link assembly with a pivot axis accommodates radial movement of the outer platform.

Perpendicular motor axes reduce wing thickness and drag while maintaining power output through integrated bevel gear transmission.

Replacing traditional gearboxes with electromagnetic coupling, the FASSTER design boosts thrust-to-weight ratios and aerodynamic efficiency.

A wing tip stub spar extends into the main section to react moment loads across its length.

A thrust reverser assembly merges the actuator directly onto the door structure, eliminating separate mounting hardware.

A combined sump structure unifies oil supply and drain lines across multiple bearing assemblies in a turbine engine.

Metal centering elements bridge gaps between ceramic fiber composite segments, securing radial alignment without weakening grooves.

Segmented wave attenuation panels with permeable layers minimize on-board weight while preserving acoustic treatment performance in aircraft nacelles.

A geared turbofan architecture uses an epicyclic gear speed change system to drive the fan at optimal rotational speeds.

Tongue-and-groove interfaces and bonding material join ceramic-matrix composite segments, reducing gas leakage while managing manufacturing complexity.

Replacing gearboxes with a direct-drive motor reduces airframe weight while maintaining torque transmission.

RTM jig manufactures integrated composite aircraft frames, eliminating riveted assembly steps and reducing structural weight.

A dual-spool gas turbine engine controller extracts electrical power from the high-pressure spool to meet demand.

Direct drive electric motors rotate rotor assemblies independently, eliminating complex reduction gearboxes to reduce device complexity and vibration.

Impingement holes direct temperature control fluid against the turbine casing to manage radial expansion and maintain minimal tip clearance.

An electrical switch disconnects the variable nozzle from the aircraft power network during reverse jet operation.

Structural airfoils provide lift to offset drag, resolving the trade-off between hovering efficiency and forward flight performance.

Replacing hydraulic cylinders with a piezoelectric actuator reduces engine mass by five times and eliminates fuel circuit heating.

A geared gas turbine engine uses a gearbox to decouple fan and turbine speeds for high propulsive efficiency.

Low-modulus foam inserts replace heavy carbon fiber in fan platforms, reducing weight while preventing resin infiltration during assembly.

Buffer air pressurizes a flexible seal member between metallic and ceramic composite segments, preventing gas leakage caused by differential thermal expansion.

Shape memory alloy actuators adjust fan nozzle throat area through thermal deformation.

Axial extensions on the anti-ballistic wrap induce hoop tension to resist radial deflection, maintaining structural integrity during blade separation events.

Hydrostatic variators transfer energy from the low pressure shaft to alleviate high pressure shaft load, preventing compressor surging at low rotation speeds.

Electronic engine control system determines output power using differential oil pressure across the reduction gearbox.

Merged calibration and inspection holes allow an eddy current probe to collect data in one pass, eliminating manual recalibration time loss.

Segmented barriers direct resin flow into composite preforms, reducing porosity and void content during manufacturing.

A thermodynamic system integrates a heat pump to recycle waste heat from the condenser back to the evaporator inlet.

Merging actuation into the track beam preserves the aerodynamic profile and flow area while reducing nacelle weight.

Automating stamping replaces labor-intensive hand layup, reducing production time while maintaining structural integrity.

Thickened shroud walls integrate secondary flow channels to evacuate hot air, reducing noise and thermal stress in turbomachines.

Discrete molding of composite thrust reverser cascade segments eliminates flexible mandrel tooling and labor-intensive hand layup processes.

Deflector vane redirects heated gas flow within an annular chamber to mix streams, reducing peak temperatures that damage nacelle surfaces.

Segmented flexible printed circuit boards route critical engine signals through localized fire-proofing layers.

Steam flows past a turboset generator to cool it, reducing equipment complexity and energy consumption.

A pressure-activated seal cap moves between retracted and sealing positions using fluid conduit channels.

Oriented composite fiber layers on thrust reverser blades resolve structural integrity versus manufacturing cost trade-offs while enhancing mechanical strength.

A core turning motor driven by a depowered FADEC rotates the engine core to mitigate thermal gradients.

An internal duct channels air to a tip outlet, disrupting blade vortices to mitigate brownout visibility hazards.

Fusible screws disconnect the low-pressure compressor stator from the intermediate casing to isolate rotor imbalance.

A quadrail ergonomic apparatus uses multiple pathways and carriages to suspend workloads securely above a surface.