Turbines TRIZ Cases

A beveled fin portion creates a predetermined space for stable filler metal feeding, preventing defective welds caused by dimensional tolerances.

Threaded mechanical joints absorb main loads to prevent hot cracks in gamma-TiAl alloys.

Boron-free Ni-Ti-Cr filler alloy repairs turbine blade cracks at 1175°C, eliminating brittle boron compounds and preserving mechanical properties.

Segmenting the closing function with an accumulator eliminates spring force requirements, reducing servo motor capacity and power consumption.

Robotic welding deposits metal feedstock to form a secure external jacket, replacing vacuum processes that limit component size and reliability.

A mechanical auger feeds filler material through an aperture array to ensure uniform deposition during laser cladding.

A drilling tool uses a cam clamp fixture to secure turbine blade assemblies during fabrication.

Laser overlay welding creates precise flow passages between beads, avoiding costly panel replacement and reducing repair time.

Composite grit and braze alloy coatings reduce air leakage while maintaining dimensional stability.

A turbine blade squealer tip features a densified oxide dispersion strengthened layer extending from the tip cap to act as a sacrificial cutting edge.

Laser-based additive manufacturing replaces mechanical alloying to eliminate contamination and reduce cycle time while achieving high-temperature strength.

A turbocharger case integrates a three-dimensional lattice structure to reduce thermal conduction between turbine and bearing sections.

Selective mechanical deformation followed by heat treatment creates localized coarse grains in nickel super alloys to enhance creep resistance.

High temperature heat treatment of additively manufactured superalloys overcomes casting limitations to tailor creep strength and fatigue behavior.

A niobium silicide composite microstructure with dispersed precipitates improves high-temperature strength and room temperature toughness.

Extruding aluminum alloy blanks under temperature-limited forming conditions reduces component weight while maintaining high-temperature fatigue strength.

Sintered metal nanoparticles encapsulate planar carbon fiber structures to form high strength-to-weight turbine rotors.

A segmented aerofoil casting method joins two body portions to form internal cooling passages without complex core support structures.

Axially extending cage-like rotor blades increase pumping speed threefold while reducing pump size and weight for compact mass spectrometers.

Selective laser melting creates raised features in diffusion cooling holes, enabling complex geometries that traditional drilling cannot achieve.

A vascular engineered lattice structure circulates coolant through nodes and branches to cool gas turbine engine walls.

A nested torch design merges optical and infrared sensors to monitor weld quality, eliminating undercuts in thick metal components without manual intervention.

An integrated apparatus simultaneously cuts and laser peens workpieces to induce compressive residual stresses.

A processing method for additive layer manufactured superalloys uses hot isostatic pressing below the gamma prime solvus temperature to close internal voids.

Real-time machine vision detects weld defects during production, eliminating costly post-weld testing delays.

Precise silicon, boron, and zirconium control reduces solidification cracking in gas turbine parts.

Differential thermal expansion in composite airfoil regions passively adjusts geometry, maintaining aerodynamic efficiency across varying gas flow conditions.

Monolithic additive manufacturing merges inner and outer rings with spiral fins to contain debris while reducing weight.

Heat sinters a powder coupon onto a turbine component, preserving the original microstructure while creating a strong bond.

Additive manufacturing insert creates sequential impingement cooling circuit for small gas turbine stator vane airfoil.

Laser peening treats turbine rotor pin holes with optical energy to prevent stress-corrosion cracking without degrading coupling precision.

A frustoconical nozzle positions a liquid-jet guided laser beam at steep angles to cut precise passages in airfoils.

Upward angled scavenger pipe evacuates oil from narrow bearing compartments during nose-down attitudes.

Directed energy deposition material addition restores damaged dual-walled metallic coversheets by fusing new material to exposed pedestals.

Dynamic compaction bonds dissimilar powder metallurgy materials using instantaneous high pressure to preserve microstructure and avoid chemical reactions.

Fused filament fabrication deposits a sacrificial binder mixed with shape memory alloy powder to form complex components.

Polygonal inlet openings eliminate airflow separation and increase the discharge coefficient in gas turbine cooling passages.

Modifying build strategy parameters within specific object regions to customize additive manufacturing operations.

Nitrogen treatment during sintering prevents doping element precipitation, enabling reduced binder content and improved hardness-to-toughness ratios.

A temporary mandrel supports a capping panel during diffusion bonding, preventing thermal distortion and reducing material wastage in hollow aerofoils.

A co-grown helical wire cutter extracts partially sintered powder from internal passages in electron beam additive manufactured components.

Direct metal laser melting forms overhangs into hollow spaces to increase surface area while reducing material waste from subtractive machining.

A nickel-based alloy powder with precise compositional control enables additive manufacturing of components.

Corrugated internal ribs enhance wake mixing and cooling efficiency within the radially extending chamber of a turbine airfoil.

A martensitic steel alloy composition retards z phase precipitation to enhance hot strength.

Additive manufacturing forms neck structures in turbine seal slots to restrict leakage pathways, resolving spline insertion and retention trade-offs.

Segmenting airfoil clusters allows laser drilling of non-line-of-sight cooling holes, then fusing segments restores original geometry.

Flux-protected laser deposition repairs superalloys by preventing oxidation and cracking during layered material addition.

Automated robotic welding restores gas turbine end cover openings with precise insert placement, reducing manual repair time and human error.

Metal matrix composites reinforced with carbon nanotubes enhance tensile strength and thermal conductivity in turbomachine components.