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.

Embed ceramic particles within superalloy mother particles using melt-and-spin casting to create uniform composite powder mixtures.

A weld configuration joins a cover to a guide stand-up using a perpendicular joint that creates an adjacent cavity.

Laser shock impacts create raised surface peaks on turbomachine blades to disrupt boundary layers and control turbulence intensity.

Shield blocks windage effects to guide oil onto the impeller, preventing starvation in non-standard orientations.

A Yb fiber pulsed laser system drills aerospace effusion holes with uniform peak power and flat-top pulses.

Stationary rotor orbital welding simplifies equipment complexity while maintaining precise temperature control during blade attachment.

Known geometry fixtures enable precise energy beam alignment, eliminating complex coordinate system measurements during simultaneous part repair.

Laser melting eliminates coating bonding defects without chemical dissolution, reducing manufacturing cycle time and environmental hazards.

A nickel-based solder alloy matches base material properties to enable reliable gas turbine component repair.

Sealing apertures enable compressed air flow that extracts residual powder from inaccessible additive manufacturing cavities.

Welded elongate sheets form a base structure for airfoil leading edges, covered by additive metal deposits to enhance strength and wear resistance.

Optimized gamma prime nickel-base superalloy composition resolves high-temperature creep and hold time fatigue crack growth trade-offs.

Controlled heating rates during solution treatment prevent microcracking in nickel superalloys, eliminating re-welding requirements.

Lattice structures between impingement and effusion plates enhance cooling efficiency in gas turbine vanes.

A nickel-based alloy composition balances weldability with high-temperature strength through precise elemental control.

A cobalt alloy weld filler deposit joins turbine components with high joint strength.

Additive manufacturing builds a tapered channel section on an existing burner part, resolving alignment inaccuracies at the interface.

A composite heat shield combines a metallic lattice with a ceramic matrix to reinforce the structure against mechanical loads.

A braze paste process repairs thin-wall components using a composite alloy mixture.

Friction welding dissimilar titanium aluminide alloys creates a composite blade with optimized root strength and airfoil temperature resistance.

Eliminating boron and silicon from the braze material prevents solidification cracking while maintaining 70% of base metal yield strength.

Additive turbine blade root integrates lattice support within hollow interior to deliver uniform impingement cooling across curved inner surfaces.

Segmented replacement rings repair turbine rotor dovetails using partial-penetration welds applied only within end grooves.

Opposing lasers heat thin workpieces to stabilize structure, preventing deformation from thermal stress.

Segmented laser pulses improve production speed while maintaining cut surface quality and preventing cracks.

An additively manufactured inseparable seal and damper assembly integrates frictional vibration absorption directly into the turbine blade platform structure.

Titanium-based braze alloys repair superalloy substrates by eliminating boron and silicon to prevent ductility loss from deleterious phases.

A turbomachine shroud repair method measures blade clearance to determine material addition requirements for the shroud surface.