Efficient Propulsion Technologies TRIZ Cases

Segmented W and brush seals with radial support reduce leakage airflow between stator vanes and blade outer air seals under high pressure.

Segmented fan case liners decouple dimensional tolerance from repair time by allowing independent segment replacement after blade-off events.

A fixed area exhaust nozzle integrates an augmentation duct for secondary combustion to increase thrust in mixed flow turbofan engines.

Aircraft nacelle thrust reverser uses an axially translating movable part to deflect flow and reduce noise.

A flexible ceramic matrix composite seal uses embedded fiber fabrics to adapt its shape within varying groove tolerances.

A hollow ceramic matrix composite blade outer air seal segment reduces thermal gradient stresses through a nested structural design.

A resilient coupler eliminates complex synchronization devices to reduce wear from uncoupling jerks.

Integrating a connection box inside the pivot bore protects power cables from mechanical stress caused by pitch change system interactions.

Cu-Ni insert materials enable diffusion bonding of TiAl intermetallic compounds without active pressure application.

Segmenting the cascade into fixed and translating portions reduces nacelle volume, creating clearance for improved airflow and maintenance access.

Slidable center body mounting assembly accommodates thermal expansion loads between dissimilar materials to maintain mechanical continuity.

Nested radial arm Stirling engine recovers waste heat to generate power, preserving turbomachine performance.

Torque control system offsets engine fluctuations by adjusting generator resistance, eliminating flywheels and reducing weight.

Direct 3D fibre placement on a convex mould core eliminates planar draping distortions while forming flange-ready holes with optimal load-bearing orientation.

Modifying sol-gel chemistry enables ambient curing, resolving the trade-off between corrosion resistance and aircraft substrate temperature constraints.

Segmenting the fan into two stages with counter-rotation reduces centrifugal loads and eliminates FLADE complexity for supersonic aircraft.

A personal air vehicle uses a central ducted fan for vertical lift alongside wing-mounted tilting rotors to resolve stability and complexity trade-offs.

Thickened suction side endwall transfers aerodynamic loads to the vane support, relieving tensile stresses in the ceramic matrix composite heat shield.

An eccentric gearbox input shaft allows sequential motor integration, reducing diameter and drag.

A perforated liner sheet connects to a cored panel containing bulk absorber and thermal conductor materials.

Inverting the spool layout shortens the low pressure shaft, reducing diameter and core size for better fuel efficiency.

Reinforcement structure radially divides the nacelle inlet cavity into sub-cavities, mitigating foreign object damage and ice ingestion risks.

Tilting rotor axes generates side forces for yaw torque, avoiding high drag and stalling risks from excessive pitch angles.

Segmented cowl doors provide selective maintenance access while directing airflow to increase thrust and reduce noise.