Turbines TRIZ Cases

Angled cuts and laser cladding restore deep trailing edge damage without removing internal cooling ribs, reducing repair costs.

Disposable tools enable complex internal cavities in spark plasma sintering without permanent tool constraints.

Dynamic compaction bonds titanium and nickel alloy preforms via high-pressure shock loading, eliminating oxidation defects from prolonged thermal processing.

Segmented laser ablation forms a physical gap that blocks heat transfer, preventing heat affected zone formation and preserving base metal strength.

Modular cooling inserts slide into turbine slots to boost heat transfer, resolving manufacturing cost and geometry complexity trade-offs.

Dispersed ultrafine particles in equiaxed high entropy alloy grains increase tensile strength while maintaining corrosion resistance.

Diffusion bonding layers with inner depressions to transfer features outward for structural integrity.

An automated welding controller uses imaging data to identify and mask standard features before generating tool control instructions.

Cavities at shiplap interface corners hold braze beads that flow outward, preventing capillary interruption and ensuring complete joint wetting.

A turbine rotor blade airfoil shape defined by specific Cartesian coordinate values to optimize aerodynamic efficiency.

Laser cladding device positions powder and beam to form erosion shields, suppressing incomplete fusion defects.

Angled shroud projections maintain constant radial clearance during variable vane pivoting, reducing tip losses and improving compressor efficiency.

Acoustic monitoring detects wall breakthrough during hole fabrication, preventing damage by ceasing drilling when gas flow creates a distinct signal.

Feedback control maintains laser cavity temperature within ±3°C to prevent microcracking and extend device usage duration.

Composite filler powder containing brazing agents prevents cracking in superalloys during fusion welding.

Segmented welding with a wobbling laser beam fills grooves in layers, reducing thermal distortions that limit large impeller dimensions.

A porous wall segment circulates cooling air through interconnected pores to manage heat in gas turbine engines.

Unique geometric keys define complementary mating surfaces that prevent unauthorized replication and engine failures in aviation.

Asymmetric convexities on axisymmetric workpieces create controlled heat flow patterns that prevent biased material expulsion and maintain weld integrity.

Segmenting particle flow via a separator enables localized surface finish and density control, eliminating post-process machining.

Varying process parameters during powder deposition optimizes material strength and temperature capability while reducing manufacturing time.