Turbines TRIZ Cases

Measured bearing temperature guides oil cooling and mixing control to stabilize shaft dynamics and minimize turbine rotor vibration.

An insulation layer over the braze cap and heat extraction near the recess base guide solidification to limit porosity and hot cracking.

Coaxial LED and reflected-light sensing in a waterjet-guided laser improves ceramic machining precision, depth control, and thermal management.

Separating the shoe, beams, and base cuts wire EDM time and cost while preserving low leakage, thinner beams, and longer seal life.

Independently controlled vacuum lines clear pooled waste grease from pitch bearing outlets and send it to one accessible depository.

A titanium root, fiber-reinforced aluminum blade, and CNT-coated strips cut mass while improving erosion, ice, and fatigue resistance.

A high-melt and low-melt superalloy powder blend cuts microcracking during additive manufacturing and avoids hot isostatic pressing.

A scheduling valve adjusts gas turbine oil flow by torque and operating conditions to avoid low-load oversupply and reduce cooler burden.

An in-machine beam scan locates the blade interface before deposition, preventing misalignment and rework when printing extension segments.

Embedded vascular lattice walls route cooling flow through turbine components to improve convective heat transfer and resist heat-related stress.

Filtered lubricant particles are analyzed by composition to quantify volcanic ash and diagnose engine condition before failures occur.

Presintered support structures form internal cooling channels in turbine airfoils, limiting hot-section melting risk and easing manufacture.

A laser-drilled through-hole lets ultrasonic machining form precise cooling-hole sections in ceramics while maintaining speed and slurry drainage.

Contoured additive heat exchanger geometry varies local surface and flow area to cut pressure drop, weight, cost, and thermal stress in gas turbines.

Laser pre-drilling creates a through-hole that lets ultrasonic machining shape ceramic cooling holes faster while maintaining alignment and geometry.

Simultaneous diffusion bonding and hot forming in one rig cuts hollow aerofoil steps and time while preserving tolerances and material properties.

Electrophoretic ceramic deposition smooths rough additively manufactured turbomachine parts, preserving cooling geometry and thermal protection.

Braze-filled cooling passages are remachined to vary diameter along the blade, improving tip shroud cooling and sealing at high temperature.

A continuous bore cavity around the rotor disk bore cuts weight, eases thermal gradients, and preserves hoop strength at high speed.

A two-stage EDM and secondary machining approach forms aligned meter and diffuser cooling sections without sacrificing coating protection.

Onboard sensing and jointed tool motion automate turbine blade repair, cutting machining time while preserving precision on varied damage.

A welded dummy member lets complex metal parts such as nozzles or blades be fixed securely for accurate reprocessing, then removed afterward.

Dual lubricant flow paths keep an aircraft pump shaft interface primed and lubricated during pressure fluctuations, improving cooling and flow continuity.

Electrical sensing across a gear assembly detects thin or contaminated lubricant films early, enabling warnings or control actions to prevent wear.

A forced weld crack followed by braze infiltration repairs oxidized superalloy defects while limiting heat damage and preserving strength.

Localized heat and actuator pressure diffusion bond fan blade covers without fusion welding, preserving ductility and fatigue strength.

Pulsed laser-induced sound waves densify additively built turbomachine parts, improving strength, grain size, and surface quality.

Modular alignment-mounted tooling enables precise turbomachine machining on complex casings, cutting downtime and fuel leakage risk.

Folded additive-manufactured preforms and metal rings create a lightweight planet carrier that withstands gearbox loads without complex forging equipment.

Aluminum-containing particles form a self-limiting oxide layer that protects brazed hardfacing coatings from high-temperature oxidation and wear.

A pressure-responsive bypass valve and flow restrictor split engine oil flow to match changing aircraft cooling loads with less system complexity.

Pressurized gas drives leakage fluid from a container into an overboard drain tube, enabling reliable aircraft engine drainage without a lower bifurcation.

A cupped contour forms a cooling chamber over endwall channel openings, improving gas turbine blade cooling while stabilizing casting cores.

A dual-end driven machining head uses hydraulic radial expansion to machine slender long-shaft bores with better concentricity and less setup complexity.

Oil inlet-outlet temperature normalization and thermal efficiency tracking reveal gas turbine reducer drift before vibration thresholds show failure.

Fuel-cooled heat exchange and air/oil separation are built into the oil tank to protect lightweight composite structures from engine heat.

EDM forms a precise meter section in a conductive substrate, then secondary machining shapes the coating diffuser for better cooling flow.

An alignment plate and solidified fill material hold multiple blades in one build plane, improving recoating accuracy and reducing powder use.

Secondary oil passages and check valves keep turbine bearing lubrication flowing during negative-G and windmilling conditions.

A nested inner and outer fitting uses mating threads, weld lips, and a flow channel to manage lubricant leakage and simplify gas turbine tube assembly.

Routing the lubricant fill path through a hollow thrust rod improves access to an inter-flow compartment tank in dense turbine engine assemblies.

Pulsed laser treatment forms a porous titanium oxide surface that improves adhesive infiltration, bond consistency, and durability without wet chemistry.

Wire-based additive manufacturing forms a leading-edge air conduit in propeller blades to suppress cavitation, cut noise, and avoid crack-prone welding.

Localized removal and recoating at the damaged blade tip preserves wall thickness and strength while enabling more repair cycles.

A solid retainer inserted through an aperture creates low-temperature mechanical interlocks that preserve microstructure and joint strength.

Laser sintering bonds braze powder only along defined paths on complex surfaces, cutting waste and improving bond placement.

Valve-controlled swap stations and manifolds balance pressure and redirect fracturing fluid between wells to speed multi-well operations.

A plug with an inner braze element seals circular holes in hard-to-weld superalloy parts without the cracking risks of conventional welding.

Localized induction brazing repairs load-bearing gas turbine components without furnace processing, cutting repair time and cost.

Variable magnetic fields and gap-response sensing distinguish harmful ferromagnetic chips from small particles to cut false alarms.