Engine Manufacture TRIZ Cases

A connection passage links separate cooling inlets to a single airflow source within gas turbine stator vanes.

A gas turbine air intake channels ambient airflow through a scroll portion and strutted section to guide the flow toward the engine inlet.

Replacing heavy rigid reversing doors with a tensioned flexible membrane reduces engine mass while maintaining thrust reversal efficiency.

Offset impingement holes toward the concave side of a turbine blade trailing edge to reduce conduction resistance and improve heat transfer.

Rigid radial-axial guide pins restrain the unison ring against excessive movement, resolving the contradiction between free rotation and reliable attachment.

Interconnected modular housings form a triangular polyhedron shape that reduces axial length and improves power density in gas turbine engines.

A turbine shroud assembly manages blade tip clearance through a movable blade track coupled to a metallic carrier.

Rounded suction side blade tip edges act as diffusers to slow down leakage flow, reducing energy loss while maintaining safe operational clearance.

Recesses between receiving openings lower flexural rigidity to mitigate cording effects and seal wear in gas turbine guide vane assemblies.

Weld thermoplastic surface features to rotor blades using heat and pressure, reducing catastrophic bond line failures common with thermoset resins.

A gas turbine transition duct uses a curved geometric profile to reduce stress concentrations.

Relocating the lubricant reservoir into the core zone frees fan area space, enabling increased fan diameter while simplifying lubrication piping.

Variable thickness and 3D shaping shift natural frequency away from engine excitations, preventing resonance and fatigue in gas turbine components.

Curved rotor grooves bridge radial expansion gaps using extension bolts, reducing thermal stress concentrations in high-mass-flow gas turbines.

Precise hole coordinates and diameters manage thermal stress while minimizing energy loss.

Helically corrugated metal tubes and venting collars accommodate thermal expansion while preventing liquid ingress in high temperature gas turbine engines.

An inclined leading edge on the diffuser strut reduces Mach number and minimizes shock losses while maintaining structural rigidity.

Rotor blade sling with rigid bars and support straps positions blades for maintenance, eliminating large crane costs.

A rotor blade carrier integrates stiffening elements to reduce weight and simplify assembly.

A multi-part wedge fastening unit simplifies prestressed concrete tower assembly by converting linear pull force into radial clamping action.

Segmented laser and electroerosion steps form the channel, reducing electrode complexity while preventing cracks at the rounded bottom.

Segmented ply groups with varying orientations and spacing in a laminated composite fan blade airfoil disperse matrix concentrations to reduce delamination.

A vane mount ring couples turbine vanes to the case using a bird mouth connection.

Wedge-shaped obstruction diverts air flow to increase pressure rise and improve mixing, reducing shock interactions that cause inlet unstart.

Segmented floating support structures enable offshore wind turbine installation in shallow waters, reducing costs and avoiding deep-water constraints.

A turbine blade airfoil profile uses scaled Cartesian coordinates to define an external surface geometry.

Cavities in the flywheel surface hold permanent magnets, eliminating separate retention rings and reducing rotor assembly complexity.

Spiral cooling channels and impingement holes distribute coolant across stator heat shield surfaces.

Segmented load-distribution arms manage thermal expansion stress in ceramic matrix composite turbine shrouds by providing compliant spring loading points.

Raised areas on turbine blade roots modify static pressure fields to minimize secondary flows and reduce energy losses in annular space ducts.

A 3D woven composite fan platform integrates a metal reinforcement tab within the fiber structure to secure the assembly.

A suspended lattice supply frame stabilizes tower internals using tensile forces from its own weight and payload loads.

A bulkhead unit with a frame structure provides support for additional components in wind turbine blades.

Segmented rotor disks linked by integral axial mounts resolve heat treating challenges while minimizing fluid leakage across the assembly.

A turbomachine blade damper uses a convexly curved contact surface to promote friction-laden sliding movements between adjacent blades.

Wear-resistant contact blocks on the VTG lever reduce assembly complexity and improve durability.

Chevron-shaped trip strips enhance heat transfer in gas turbine airfoil cooling passageways while minimizing pressure drop and thermal strains.

An axial sliding connection between the inner and outer casings directs all thrust loads to the external structure, reducing internal diffuser mass.

Radially offset rims and hooks distribute external stresses across segmented contact zones, preventing premature wear at ceramic matrix composite interfaces.

Offset pivot tilts wind turbine tower segments to balance weight distribution and reduce trailer tire wear.

Additive manufactured synchronization ring reduces actuator loads while maintaining interface rigidity for optimized thrust and fuel efficiency.

Area-ruled cross sections in a modular exhaust system resolve trade-offs between aerodynamic efficiency and structural adaptability.

Non-uniform fan blade camber distribution enhances operability by reducing susceptibility to flutter and stall while maintaining high efficiency.

A turbine vane airfoil trailing edge configuration minimizes flow detachment through specific axial and circumferential angle constraints.

Segmented grooves channel hot air for de-icing while perforated zones absorb sound, expanding treatment areas without damaging acoustic panels.

A nacelle bleed passage draws turbulent airflow from the pressure side to the suction side using curved and linear sections.

A modular turbojet accessory driveshaft uses a nested bevel gear mechanism to transmit power through an intermediate casing radial arm.

Poles coupling aft plates reduce hoop stress in gas turbine diffusers.

Segmented flanges with relief orifices hold ceramic matrix composite ring sectors, reducing mechanical stress from metal attachment part expansion.

Segmented engine housing with pivoting doors groups fuel and oil components to resolve maintenance accessibility contradictions.