Blade Accessories TRIZ Cases

Axially aligned dovetail slots in a fixture system guide turbine blades onto rotor wheels, overcoming interlocking shroud impediments during assembly.

Varying the maximum thickness to chord ratio along the blade height reduces bending-torsion coupling and increases the flutter margin.

Bulge on central cavity inner core provides increased anchoring depth for connecting rods, preventing cracks during lost-wax casting of turbomachine blades.

Passive guide bearings constrain a grinding wheel to restore airfoil edge tolerances, resolving precision trade-offs while eliminating removal costs.

A bi-material cooling plug melts at a predetermined temperature to expose an inner material and release supplemental cooling air through the pathway.

Segmented shear keys and a threaded locker puck retain turbine rotor rim seals axially, resolving limited dovetail access while maintaining reliability.

Controlling the blade thickness ratio to the back wall thickness within 25% variation reduces casting irregularity and rotational unbalance.

Segmenting the blade root into pre-formed composite plates eliminates thermal shear stresses and machining degradation while simplifying manufacturing.

Aligning voids in ceramic matrix composite plies forms internal cavities, eliminating leaching residues and reducing thermal gradients.

Segmented offset corner surfaces minimize thermal stresses and enhance high-temperature resilience while maintaining precise gas path gaps.

Eutectic gamma prime particles pin grain boundaries in a nickel alloy matrix, balancing tensile strength and workability without complex manufacturing.

Notches in cantilever stator vanes receive dampers to reduce resonance amplitudes, preventing damage from gas turbine engine vibrations.

Pre-filling ceramic core pores with liquid prevents acid retention and material loss, preserving turbine blade dimensions and longevity.

Asymmetric snaps and differential materials manage centrifugal loads and gas leakage between rotating and static components in gas turbine engines.

Optimized bore curvature ratios distribute centrifugal loads to reduce stress concentrations by 25% and prevent plastic deformation in overhung radial turbines.

A shuttle carrier moves axially along a tie shaft while the piston ring seal remains stationary relative to the rotor, reducing wear from relative motion.

A single high-power laser pulse creates visible surface marks on turbine blades without material deformation.

A gas turbine rotor blade root section combines composite and metallic materials to create a secure metal-to-metal coupling for internal cables.

Radial expansion of the enlarged diameter portion acts as a thermal barrier, suppressing heat transfer to the seal groove during welding.

EDM machining creates a tight interface for brazed pucks that restore radial thickness on cracked turbine platforms, reducing downtime and replacement costs.

Varying strut airfoil incidence angles prevent flow separation and blockages, enhancing pressure recovery in gas turbine exhaust diffusers.

Portable insertion tool uses swivel joints to align heavy turbine blades, reducing operator exhaustion and preventing damage during ground-level installation.

Segmented lamellar elements with additive manufactured nozzles eliminate boundary vortices and friction losses during energy conversion.

A radially diffused tip flag airfoil reduces thermal mass through hybrid skin core cavities.

Masking control region manages shot peen force to form tapering compressive stress transitions in gas turbine components.