Engine Manufacture TRIZ Cases

Optimized stator vane airfoil reduces aerodynamic losses while balancing mechanical loading.

Consolidating multiple roller pins into one unified component reduces manufacturing complexity while maintaining precise nozzle vane positioning.

An array of open-ended hexagonal cells reduces swirl angles in convoluted inlet ducts, mitigating engine surges and enhancing gas turbine efficiency.

Rotating hub assembly device positions wind turbine components outside platform periphery for efficient offshore installation.

Serpentine cooling circuits pull heat from bearings using fuel discharged into the combustor, eliminating recirculating oil costs.

A honeycomb panel assembly uses edge-applied adhesive to bond a mesh layer, maintaining open cells for sound absorption.

Rectangular film cooling holes with tilted centers and rounded corners diffuse cooling air to prevent separation on the front edge of turbine vanes.

Gravity-driven alignment members join wind turbine blade segments, resolving assembly complexity while maintaining precision.

Assembling a hydraulic turbine to a hybrid vehicle transaxle rotary shaft reduces manufacturing costs by reusing end-of-life components.

Merges lift beam with yaw platform to resolve space constraints and ease maintenance access.

Segmented auxiliary units enable redundant operation and lower transportation costs by allowing component replacement without system disruption.

A thermal insulation bushing lines a through-hole in a ceramic flange to reduce thermal gradients and mitigate distress in gas turbine airfoils.

Stripping the cable and attaching a connector creates an insulated pathway that diverts strikes away from vulnerable sections.

Vortex generators create controlled vortices that energize the boundary layer, preventing flow separation and reducing backpressure in turboshaft exhaust ducts.

A turbine shroud assembly uses a metallic carrier and C-shaped clamps to secure ceramic matrix composite blade track segments.

Nesting multiple internal combustion tubes inside one outer actuator increases operating frequency and magnitude without expanding the external footprint.

A nacelle support structure uses movable rollers to guide heavy medium-voltage lines, reducing installation time and effort.

Azimuthal nacelle length variation minimizes aerodynamic interactions between the engine and fuselage, reducing fuel consumption.

Concave trailing edges minimize wake effects and maintain stable boundary layers to reduce turbine blade stress.

Separate fan paths provide adjustable airflow volume and speed to accessory systems despite gear reduction limiting primary fan output.

A frustoconical disc spring seal member prevents fluid leakage through annular gaps in turbochargers.

Segmented De Laval nozzles minimize fluid dynamic losses by orienting jets within the blade cascade entrance plane.

Slotted brackets and swiveling bails accommodate varying hole spacings, eliminating cumbersome adjustments during heavy object lifting operations.

External motor positioning avoids overheating in gas turbine engines, maintaining accurate position feedback.

Aerodynamically shaped screen cross-members protect aircraft engine intakes from foreign object debris while maintaining low air resistance.

Elliptical curve gussets maintain seal orientation during relative movement, preventing cooling air leakage and high-energy gas loss.

Radial air cooler uses front wedge to increase inlet pressure and rear ramp to guide exhaust flow, reducing bypass stream resistance.

A turbine rotor blade tip shroud incorporates a seal rail with an integrated cutter tooth and leakage gap to manage thermal loads.

A canted multinozzle grid plate directs exhaust gases rearward while maintaining a flush cylindrical profile.

A spacing device with pins creates precise perforations in deicing acoustic skins during baking.

Hard particle coatings on intermediate connection bodies increase friction to resolve reliability issues under harsh assembly conditions.

A high pressure turbine vane airfoil uses a specific Cartesian coordinate profile to optimize radial swirl and total pressure gradients.

A rotor design secures a locking sheet to a blade root using an internal fixing portion for stable assembly.

Conical contact surfaces center the guide vane ring via disc spring preload, preventing self-locking during thermal expansion.

Orientation marks on the vortex generator platform enable accurate mounting angles, resolving unstable vortex generation caused by misalignment.

Segmented exterior trenches with single passages distribute cooling media, resolving uneven thermal wear on turbine airfoils.

Anti-icing exhaust system directs heated fluid radially through a structural gap, eliminating external tubes to reduce complexity and cost.

A turbine blade airfoil to platform fillet contours specific coordinates to create a smooth geometric transition between surfaces.

Offset radial channels reduce pressure losses and improve efficiency, addressing size and sensitivity bottlenecks in conventional axial designs.

Automated scanning identifies turbine rotor screw weights and angular positions for engine monitoring unit reinitialization.

An eccentric sleeve aligns a bearing concentrically with a shaft, resolving tight space constraints in small turbine engines without complex tie rods.

Honeycomb inserts in the hollow spar reduce blade mass without compromising mechanical strength against bird ingestion shocks.

A jet engine variable-geometry exhaust nozzle uses pivotally connected flaps with continuous sliding surfaces to prevent leakage and reduce noise.

A system deposits energy along conductive paths to modify shock waves and control supersonic fluid flow.

A turbine blade airfoil profile with a decreasing passage width ratio prevents flow separation from the ventral surface.

Post-tensioned radial and anchor bolts in a cementitious collar extend wind turbine foundation life by resisting dynamic fatigue failure.

Modular handling equipment accommodates tapered tower profiles by adjusting support base positions and column heights to distribute acceleration loads.

Segmented scalloped platforms and trailing edge ridges reduce horseshoe vortex strength to lower pressure losses in turbine stages.

Three independent masts with winches lift turbine modules via a pulley triangle, eliminating auxiliary columns that cause residual stresses.

Segmented external shims adjust thrust bearing position to optimize mesh precision while avoiding repeated assembly cycles that risk part damage.