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.

Varying vane angles in cascade boxes redirect bypass airflow to minimize reingestion, enabling lower cutoff speeds and reducing landing gear braking loads.

A transonic rotor blade shapes its airfoil meanline to control relative curvature parameters across the chord.

A variable area fan nozzle integrates with a thrust reverser using a common actuation system to control bypass flow.

Segmented circumferential exit holes discharge heated gas to prevent ice formation while disrupting D-duct resonance patterns that generate noise.

A supersonic air intake plenum uses a porous side wall to bleed air into a coolant mixing zone, reducing thermal load without active control mechanisms.

A multi-nozzle flow diverter valve directs third stream air through primary or secondary nozzles in variable cycle jet engines.

External electric generator mounting between inlet and bypass ducts resolves heat dissipation and maintenance access challenges.

Fusible rods break under blade rupture loads while secondary rods maintain force transmission, reducing connection weight.

Dynamic inlet lip geometry adjusts contraction ratios to reduce drag, flow separation, and weight during cruise flight conditions.

Bleed port diverts excess low-pressure compressor flow to a secondary engine, preventing high-pressure stall.

Shoulder features on ceramic matrix composite vanes secure platforms while sealing gaps to prevent leakage.

A ceramic matrix composite pin connector manages thermal expansion between turbine frame components.

An elastomeric clamp ring accommodates axial tolerances and thermal expansion, ensuring precise radial tip spacing without damaging flexible airfoil structures.

Integrated electrical connector lies flush with turbine engine casing fastening flange to resolve mounting complexity and ensure reliable connections.

A crimped heat shield design secures fluid tubes through plastic deformation of interlocking flanges.

A vanadium resistant coating system uses a bond coat and rare earth stabilized ceramic layer to protect superalloy substrates.

Composite ice panel segments bond to fan cases, reducing manufacturing complexity and labor costs.

Segmented pivotable doors redirect engine efflux downwardly to create a nose-down pitching moment, improving aircraft controllability on wet runways.

A unitary ceramic matrix composite flow path assembly positions an inner band via nozzle airfoils extending from a single outer wall structure.

Modifying thrust demand via growth time constants prevents tip rub during transients while maintaining engine efficiency.

A nickel aluminide coating forms through thermal diffusion of an aluminum foil onto a nickel deposit layer.

Electrical starter machine exchanges energy with storage member to assist gas generator rotation, reducing fuel consumption during standby.

Woven sleeve extension adjusts fan bypass area to optimize airflow, preventing choking during takeoff and reducing fuel burn in cruise.

Offset lower and upper doors redirect airflow upward, resolving crosswind instability by pressurizing the vertical tail.

A nacelle air inlet uses localized hot air injection through a manifold with passage holes to circulate heat around the duct circumference.

Aircraft fuel filter monitoring system detects clogging events using differential pressure and temperature thresholds to identify specific contamination types.