Turbines TRIZ Cases

A pre-sintered superalloy preform is electron beam brazed onto turbine shroud notches to resist wear, vibration damage, and thermal cycling.

A retaining ring and anti-rotation insert let this oil nozzle snap on and off for flow testing without major engine disassembly.

A multi-wall airfoil uses additive-made cooling chambers and internal TBC layers to limit spall damage, reduce thermal gradients, and extend life.

A low-gamma-prime shell with superalloy powder core cuts LMD material loss and contamination while matching the repaired base alloy composition.

Additive manufacturing encloses flowable-medium dampers inside internal cavities, improving vibration control while avoiding complex fill steps.

Image-guided casting matches the airfoil tip to the body for accurate cooling passage alignment, faster assembly, and easier repair.

Thin-walled hypotubes are brazed to additively made manifolds to improve strength, surface finish, and heat transfer in gas turbine engines.

Direct metal laser melting forms small, complex turbine cooling holes with precise aperture profiles while cutting scrap and machining cost.

A nanosecond pre-hole, millisecond deep drilling, and nanosecond shaping improve cooling-hole accuracy while protecting the TBC interface.

An electromagnet draws a magnetic mold onto the substrate to improve heat transfer, cool thin turbomachinery builds, and limit distortion.

Chamfering-cutter machining forms one-piece studs inside an outlet guide vane cooling passage, cutting cost and time while improving lubricant heat exchange.

A metallic microlayer seals surface-connected porosity in 3D-printed microfeatures, enabling HIP densification without degrading alloy properties.

Laser ablation forms near-net cooling holes quickly, then EDM removes recast in meter and diffuser sections to cut machining time and cost.

Hard, high-melting deposits on turbine bucket squealer tips cut into abradable shrouds to maintain sealing and reduce wear during thermal transients.

Electrospark deposition reshapes turbine cooling holes in place for precise flow control without stripping and recoating thermal barrier coatings.

Vacuum-sealed HIP forms a metal-ceramic abrasive blade tip that resists long-term wear while preserving turbine clearance performance.

A layered nickel-based repair assembly fills larger turbine superalloy defects while avoiding brittle interfaces and sintering shrinkage.

A flow restrictor and gravity-fed reservoir keep turbine oil tubes full after shutdown, limiting heat-soak coking and bearing oil starvation.

Waisted tank sections guide de-aerated oil in shorter drops to limit splash, re-aeration, and false oil level readings in gas turbines.

By varying beam size, scan speed, and preheating, this case controls crystallization in powder-bed additive builds for tailored microstructure.

A homogeneous additively made build platform prevents substrate impurities and phase variation from disrupting superalloy deposition reproducibility.

Piezoelectric transducers vibrate additive-manufactured parts to dislodge trapped unfused powder from narrow, winding, and dead-end passages.

A staged heat treatment with post-weld stress relief cuts residual stress in solid-state welded nickel alloys without over-aging nearby base metal.

A movable suction nozzle tracks solidifying positions to remove heavy particles, protect the powder bed, and improve 3D build quality.

A zinc diffusion layer is formed and removed to seal surface-connected defects in AM aluminum alloys, enabling HIP and smoother surfaces.

Low-melting interlayers enable strong, thermally stable bonding between metal parts and metal-plated polymer or composite surfaces without heat damage.

A one-piece metallic clevis uses a deformable honeycomb annulus to replace elastomer damping bearings in hot, liquid-exposed turbomachines.

A zinc diffusion layer is formed and removed to smooth AM aluminum surfaces, reduce cracks and porosity, and enable HIP processing.

Complex cast aperture indentations paired with drilled passages improve film attachment and laminar cooling flow in gas turbine walls.

Guiding pads and an external bar support keep a slim boring bar rigid inside stepped shaft bores, improving finish and dimensional accuracy.

Near-surface 3D-printed cooling channels improve turbine thermal management while reducing the complexity of casting and machining.

Laser-drilled vent holes in airfoil ribs replace slower forming-heavy blade production, cutting time and cost while preserving stiffness and strength.

Varying laser irradiation angles during metal additive manufacturing creates region-specific grain alignment that boosts blade strength and fatigue life.

Local peening reshapes a flared welded component in place, restoring spacing without disassembly while adding compressive residual stress.

Additive repair rebuilds damaged cooling-hole sections with tuned roughness and diameter to improve cooling efficiency and cut downtime.

A curved laser-clad shield boundary helps turbine blades keep erosion resistance, hardness, and secure attachment without welding defects.

Controlled heat and actuator pressure diffusion bond a cavity-back airfoil periphery, preserving titanium blade ductility and fatigue strength.

An accessible fill port linked through the accessory gearbox lets a remotely placed aircraft engine oil tank be filled cleanly and safely.

Work-hardening austenitic steel cladding protects nodular cast iron steam turbine inner casings from last-stage water droplet erosion.

A layered blade profile with concave upper and convex lower sections balances airflow, boosting static pressure while reducing noise.