Turbines TRIZ Cases

See how additively manufactured turbomachinery components use inner lattice structures with con

See how fluid-flow coupons and flow-rate measurement replace time-consuming physical artifact i

See how sequential welding and machining of turbine rail concave surfaces prevents springback e

See how single-step machining after TIG welding repairs turbine rail wear while avoiding stress

See how segmented metal sheets are pressed and bonded to form centrifugal fan blades with compl

See how single-action machining after TIG welding restores turbine upstream rails without sprin

Heating fluid near the component surface creates convection that removes salt byproducts during finishing and supports 1 to 5 micro-inch roughness.

A fuel cell stack placed in the combustor diffuser passage uses pressure-driven flow and cooling to improve turbine efficiency while limiting thermal transients.

Multiple print chambers and an airlock raise additive manufacturing throughput while maintaining low oxygen for large metal parts.

An energy-converting phosphor enables ambient-temperature adhesive curing inside hidden joints, avoiding line-of-sight limits and thermal stress.

Printed sprues, lips, and notches give robots reliable grasp points to reorient complex AM parts and raise manufacturing throughput.

Swappable lens assemblies change beam size and magnification during powder bed fusion, avoiding optical shutdown and re-alignment.

Rejected polarized light is reshaped and fed back into the beam path to raise print intensity, throughput, and energy efficiency.

Two-dimensional energy patterning and beam reuse raise powder bed fusion throughput while preserving resolution and avoiding higher laser cost.

Multiple build chambers with side part removal and separate powder feeds cut powder-change downtime while keeping powder bed fusion running.

Stencil-deposited and sintered rotor layers enable sub-100 µm laminations with less material waste, lower eddy losses, and added insulation.

Rounded wedge corners and insulated Fe-based magnetic particles enable smoother stator slot insertion while reducing damage, contamination, and eddy current loss.

Multiple build chambers enable concurrent powder bed printing, faster material changes, and lower downtime with controlled temperature and energy reuse.

Multiple patterned laser or electron beams with energy reuse increase powder bed fusion throughput, enable larger parts, and lower energy cost.

Printed temporary walls confine powder to needed zones in powder bed fusion, cutting material use, weight, and handling cost.

Two-dimensional energy patterning splits and recycles beams to raise powder bed fusion throughput without the cost and resolution loss of higher laser power.

A zoned powder bed process advances parts continuously to build long, high-resolution structures with higher throughput and lower laser burden.

A hermetic drain intake with onboard sensors enables immediate aircraft engine fluid analysis while reducing pollution and avoiding circulation interference.

Additive manufacturing builds a motor rotor onto an impeller shroud to eliminate the shaft, cutting weight, housing needs, and assembly complexity.

Temporary printed walls confine powder only where needed in powder bed fusion, cutting material use, weight, and recycling burden.

Rejected patterned light is repolarized, redirected, and recombined to raise additive manufacturing throughput without extra laser power.

Multiple polarized semiconductor laser beams are combined into one high-intensity beam to improve powder bonding with minimal optical loss.

Tilting and inverting the build platform automates powder recovery in an inert atmosphere, cutting manual handling and contamination risk.

Alternating current melts metal powder between adjacent components to create stronger, more stable joints with shorter thermal cycles.

Rejected polarized light is recaptured, homogenized, and fed back into additive manufacturing optics to raise build-platform intensity with less wasted energy.

Pressure differences drive airflow through an integrated fuel cell stack in the combustion section, boosting efficiency while extending hardware life.

Tilting and inverting the build platform automates powder removal and hopper reuse in powder bed fusion while limiting oxidation and contamination.

Separate coolant loops for the heat engine and electric motor improve lubrication, cooling, and fuel-efficient hybrid aircraft operation.

In-process powder sampling and characterization helps detect material changes, adjust print settings, and preserve audit samples in powder bed fusion.

Onboard generator sets and hydraulic networks power fracturing auxiliaries from a dual-fuel gas turbine, cutting unit count, congestion, and cost.

Higher Sm content in the main phase raises resistivity in rare earth sintered magnets, cutting eddy current heat while reducing Dy use.

Integrated cooling channels, shielding, and reinforcement protect aircraft power electronics from heat, EMI, and shock while reducing weight.

A conveyor moves parts through fusion and powder-removal zones, enabling long high-resolution structures with higher throughput and lower cost.

Interchangeable lens assemblies let powder bed fusion systems change magnification and image distance without shutdowns, preserving resolution and throughput.

Periodic powder sampling and characterization in powder bed fusion enables parameter adjustment, material verification, and defect prevention.

A split-compartment oil reservoir keeps turbomachine oil flowing during zero or negative G flight by using conduit position to prevent air ingress.

A segmented mold forms twisted blades, hub, and shroud in one molding step, enabling stronger high-efficiency plastic impellers with easier demolding.

Wave-shaped screen mask openings let green parts expand and compress during forming, reducing cracks in curved powder-metallurgical components.

A variably porous AM repair coupon directs braze flow by capillary action, improving bond strength while reducing material cost.

Controlled die heating and staged cooling form hollow gas turbine airfoils with accurate shape, lower weight, and preserved structural integrity.

Directed energy deposition rebuilds defective stator vane edges with less heat distortion and faster, more standardized repair than manual TIG welding.

Two symmetrical vane halves are brazed along a low-stress centerline to meet engine geometry and material requirements beyond core casting limits.

A cavity-patterned support layer stabilizes metal injection molded turbomachine blades during debinding and sintering to limit cracks and distortion.

Centrifugal separation and a dedicated air exit keep oil mist from bow shock, delivering more oil-rich lubricant to turbine bearings.

Internal partitioned channels feed multiple tip cooling holes from one duct, improving uniform air distribution and blade thermal resistance.

A fixed and moving die mold forms 3D twisted blades with hub and shroud in one piece, cutting waste, demolding complexity, and seams.

A staged friction and constant higher forging force improves blade-to-stub weld precision, stress uniformity, and defect resistance.

A sacrificial build platform enables additive repair of damaged gas turbine blades while blocking laser strikes and powder contact to cut waste and cost.

A sacrificial build platform supports additive repair of damaged gas turbine blades while blocking laser strikes and powder contact on the disc.

A hinged fixture clamps a CMC airfoil preform for partial densification and accurate trailing-edge cooling-hole drilling before full densification.

Damaged turbine sections are replaced by additive manufacturing with tuned cooling-hole roughness and diameter to improve cooling and cut downtime.

Layer-by-layer blade and base-body buildup cuts impeller machining time and material waste while maintaining strong load-bearing connections.

Multiple laser emitters vary power by target area to heat turbine blades with controlled gradients, reducing stress during manufacture or repair.

A lever-actuated plug vents the depressurized adapter cavity, reducing cap opening force and easing oil refilling after flight.

Integrated additive cooling manifolds solve powder entrapment and rotor integrity limits, enabling higher turbine inlet temperatures.

A shaped laser energy profile forms teardrop cooling holes in turbine parts, cutting EDM cost while preserving precise hole geometry.

Spatially varied porosity in an AM repair coupon controls braze flow, strengthening joints while preserving structural performance and cost.

A slotted mounting tool with fasteners and sacrificial support bases stabilizes thin compressor blades during hybrid repair to limit vibration and scrap.

A pressure reducer, piston extruder, and switching control keep bearing oil flow stable despite compressor air pressure fluctuations.

Preloaded braze reservoirs in AM metal coupons enable thermal-triggered internal infiltration, improving bond strength and repair performance.

Variable cold-spray velocities build airfoil leading-edge covers that match complex shapes while balancing mandrel release and strong layer adhesion.

A porous repair coupon with a sealed cavity directs braze infiltration by capillary action to strengthen joints and cut material use.

Inert gas cooling keeps the feed nozzle stable during LMD, preventing deformation, preserving deposit quality, and avoiding oxidation.

Additively formed mask strips and securing inserts cover turbine cooling holes during spray coating to prevent bridging and rework.

Electrochemical machining with bipolar pulsed voltage smooths lattice workpieces without thermal or mechanical stress.

Polygonal shaft couplings replace hard-to-machine splines in lubrication pumps, easing production and tolerating shaft misalignment.

An electrode and fixed camera enter clogged internal passages, using controlled arcing to remove debris and recover parts that would otherwise be scrapped.

A fishbone braze foil and spring-like locking insert repair mis-machined gas turbine slots, cutting part waste, downtime, and replacement cost.

A forged base plus additive build-up cuts waste and cost in complex component manufacturing while enabling repair of damaged parts.

Stagewise additive build and machining keep internal flow surfaces accessible while forming an integral shrouded rotor with less assembly complexity.

An oversized repair section and resistance welding restore cropped airfoils with accurate alignment, lower repair time, and less adjacent-part damage.

Vehicle air stream pressure drives lubricant to bearings through a pitot tube dispenser, cutting pump, reservoir, and plumbing weight.

Integral lubricant traps in the bearing housing release temperature-responsive oil onto bearings, cutting pump, plumbing, weight, and cost.

Independent lubrication circuits let power and auxiliary gearboxes use tailored oils, cutting maintenance and improving space use.

Layer-by-layer DED parameter control tailors repair microstructure in worn aerospace parts to meet structural needs and extend service life.

A removable backing surface lets DED rebuild thin or through-hole aerospace regions while controlling repair-layer stress and microstructure.

Preloaded compressive residual stress in a cast repair zone enables directed energy deposition without HAZ microcracking or interface failure.

Linear laser-drilled holes are bent into curved cooling passages, avoiding shallow-angle beam damage and preserving hole integrity.

Pre-measuring the held workpiece and holder reference position enables accurate beam path generation and avoids in-process positioning errors.

Variable-thickness turbine engine ducts use additive manufacturing and bellows joints to cut weight while handling tight bends and thermal loading.

A matched-expansion nickel braze filler improves weldability and oxidation resistance for crack-free superalloy joints in gas turbines.

An extended plug with an annular seal and wire bristle pack improves conduit sealing while scraping deposits for easier maintenance.

Circumferential angled channels in an additively built turbine rotor support structure spread thermal stress while preserving shaft and bladed rotor integrity.

Cooling passages and textured surfaces are machined or molded into the green shroud segment before sintering to cut coolant demand and thrust loss.

Alternating reactive powder layers use beam-triggered exothermic heat to cut melting energy, reduce passes, and speed part fabrication.

Overflow sensing in a gravity-fed oil collector confirms when a wind turbine main bearing cavity is sufficiently filled without pressure-based gauges.

A cover slot guides the high-energy welding beam to join thin blades to a thicker diffuser cover with less deformation and stable weld quality.

Electron beam brazing repairs gas turbine airfoil damage in inaccessible areas by sintering deposited braze material before furnace diffusion.

Controlled fixturing and actuators enable lower-temperature diffusion bonding of hollow titanium fan blades while preserving ductility and reducing distortion.

Multiple chip capture zones with different gaps distinguish harmless fuzz from larger metallic chips, reducing nuisance engine alerts.

Defective stator stage sections are removed and replaced with powder bed fusion segments to cut heat input, distortion, and repair labor.

A porous repair coupon with an internal conduit guides braze infiltration to strengthen repaired joints while reducing metal use and improving heat flow.

A porous stress-relief section in an AM metal coupon lowers residual stress and cracking risk, improving brazed repair of superalloy components.

A porous AM metal coupon directs braze infiltration to strengthen repaired joints, improve oxidation resistance, and reduce post-braze machining.

Machining opens pores in silicon-containing turbine ceramics; laser-induced oxide sealing restores a closed surface and improves durability.

Variable-porosity AM coupons with slanted walls improve turbomachine airfoil braze joints while reducing material cost and boosting strength.

A brazed AM porous region between dense component sections cuts joint stress while improving strength, oxidation resistance, and thermal conductivity.

Varying porosity in an AM metal coupon guides braze infiltration to strengthen repaired joints, cut material use, and improve durability.

Controlled porosity in an additively manufactured metal coupon directs braze infiltration to strengthen repaired joints, cut material use, and avoid post-braze machining.

Capillary braze infiltration through a porous AM coupon with a sealed cavity cuts mass while improving repair joint strength and integrity.

Different-porosity porous regions let braze infiltrate an AM repair coupon, improving turbomachine joint strength, fatigue, and oxidation resistance.

A porous AM metal coupon uses braze infiltration and internal pins or fins to improve heat rejection, joint strength, and oxidation resistance.

A porous repair coupon uses a hollow conduit and controlled braze infiltration to strengthen repaired joints while maintaining thermal conductivity.

Blending high-melt and low-melt nickel superalloy powders cuts microcracking and porosity in additive builds without hot isostatic pressing.

A pressure-balanced piston across calibrated ports detects heat-exchanger leaks in aircraft oil circuits early and alerts before fuel contamination spreads.

By wrapping the oil tank around the external case, this engine layout cuts radial projection, reduces frontal area, and improves aerodynamics.

A partitioned reservoir with a channel inside the outlet conduit keeps turbine engine oil flow air-free during zero and negative-G flight.

Additive-built fluid conduits are shifted inside a heat shield to preserve the insulation gap and avoid thermal bridging during support and attachment.

A sealed inlet, outlet, and collection container keep pitch bearing lubricant circulating by gravity and centrifugal force without leakage.

Additional material at the wheel-shaft joint replaces screws or inserts, improving turbocharger connection strength across temperature changes.

Depositing and machining cladded material on tube stock forms injector features with less waste, shorter machining time, and strong braze joints.

Cold spray builds a niobium airfoil leading edge on a mandrel, enabling complex shapes with low waste, low stress, and strong erosion resistance.

Zone-specific laser path planning clears coated gas turbine cooling holes faster while limiting thermal damage and part handling.

A single-piece additive flame tube uses a double-wall end wall and cooling air channel to cut thermal stress, machining, and assembly.

A two-step beam exposure builds thin walls, then remelts defect-prone regions without new powder to improve stability and sealing.

Cold spray deposition on a mandrel forms lightweight airfoil leading-edge protection with complex geometry, erosion resistance, and low stress.

A controlled spherical lens creates a teardrop laser profile to drill shaped turbine cooling holes at lower cost than EDM.

A pressure vessel mixes and sinters powders into wire for laser deposition, cutting superalloy repair material loss and contamination.

A titanium root and aluminium composite blade cut vane mass while preserving strength, erosion resistance, and anti-icing performance.

A single-piece oil distribution ring and seal track cools the dynamic seal by conduction, cutting leakage risk, size, and part count.

Integrated oil channels and nozzles target predicted hot spots in a gas turbine bearing compartment without complex tube routing.

Pre-cooling and laser metal refill restore damaged fan blade leading-edge shields without removal, preserving profile accuracy and adhesive integrity.

Linear-force hyper-feed machining forms complex mini turbine surfaces, enabling battery-free direct electric propulsion for small vehicles.

Structured light scan data guides braze powder deposition and diffusion bonding to cut waste, distortion, and post-processing in component repair.

Structured light scan data guides machining after additive braze sintering and diffusion bonding, reducing waste, defects, and rework.

Structured light scan data drives local braze powder cladding and diffusion bonding to repair defects with less waste, distortion, and secondary damage.

Braze powder is sintered, diffusion bonded, then CT-compared to drive machining, reducing waste, secondary defects, and thermal distortion.

An elastic insert expands under centrifugal force during rotation to feed lubricant to centerline and distant splines with one-shot simplicity.

Friction-welded lugs of different materials let a turbine disc rotor handle high temperature stress while simplifying repair and manufacturing.

A wobbling energy beam forms thin AM walls thicker than its diameter in one pass, improving wall uniformity while reducing hatching.

A variable-section jet pump meters oil between engine and gearbox circuits to improve lubrication precision, cut cavitation risk, and lower power use.

Pressure sensors, actuators, and grease delivery automate frac leg valve control to equalize pressure and reduce hazardous manual intervention.

An annular oil tank around the external case cuts radial accessory projection, reducing engine diameter, drag, and added containment weight.

Directed local heating melts braze at fuel injector and manifold joints while keeping remote areas cooler to speed assembly and preserve material integrity.

Directly rebuilding the honeycomb core and panel on turbine engine parts restores strength without added weight, fasteners, or complex inserts.

Flexible metallic mesh is laser-deposited and welded in situ to cut repair waste and form durable patches on damaged machine surfaces.

3D metal-printed lattice cooling passages raise surface area for heat exchange while limiting thermal stress in high-temperature gas components.

A rotating prism and moveable mirror scan a pulsed laser across confined target areas, improving beam control, coverage, and head robustness.

High-velocity mixed superalloy powders rebuild damaged areas before heating, enabling precise repair on curved or vertical surfaces.

A reversible gearbox lets the pump run at different speeds so a smaller motor can handle cold, viscous lubricant without starvation.

An overhanging AM mask supported by ligaments shields surface openings during coating, reducing clogging, removal time, and crack risk.

A perforated baffle placed ahead of the bearing chamber outlet uses pressure difference to separate oil mist and improve lubricant drainage.

Cross-cowling links to the pylon stabilize air-oil exchanger positioning despite thermal expansion and allow a maintenance access position.

Ceramic reinforcement in a superalloy filler preserves weldability while delivering high-temperature joint strength for turbine-class weld deposits.

A two-layer weld repair uses a nickel butter layer and steel fill layer to limit deformation and cracking in nodular cast iron turbine casings.

Positioning the ceramic target above the jet head lets back-splash drain away, improving deep-hole machining with abrasive or laser liquid streams.

Selective irradiation builds low-rigidity support inside holes to resist thermal distortion and improve additive manufacturing accuracy.

Cooling freezes flow test fluid in selected embedded passages, isolating injectors for faster, lower-cost inspection of attritable engines.

Laser cladding adds a wear-resistant alloy only to the turbocharger vane shaft, cutting material cost while protecting high-temperature contact zones.

An accessible inlet port and fill line let a remotely mounted gas turbine oil tank be filled cleanly, with level sensing to reduce spills.

Partial machining opens precise inner channels in rotary machine blanks, then build-up closes complex sections without casting or weld seams.

Temporary AM supports are removed, then the conduit is shifted and secured with elongated apertures to preserve insulation and absorb thermal expansion.

Recesses near TEC strut leading edges relieve shroud-interface stress while preserving exhaust flow, cutting weight and improving fatigue life.

A partial vacuum pulls softened braze tape into honeycomb cells for more consistent gas turbine seal repair with less manual strain.

Laser shock peening applied directly to corrosion pits restores compressive stress and helps turbine blades resist crack initiation and fatigue.

Concurrent friction welding joins multiple preform rotor blades to a rotor disk, cutting integrally bladed rotor manufacturing and repair time.

Added metal beads across a weld line arrest crack growth in HCF regions, extending inspection intervals without over-thickening the structure.

A buoyancy-actuated valve drains excess oil from an APU gearbox sump while preserving airtightness and avoiding complex maintenance.

Heating above the powder bed and cooling through the seed control thermal gradients to build directionally solidified or single-crystal parts.

A ceramic core with witness features supports additive rebuilding of turbine blade tips, cutting repair time, cost, and material waste.

A slip-joint sleeve and cone-seal coupling let gas turbine fluid transfer tubes be serviced without core disassembly while preventing leaks.

A weld rebuild and hardface nugget repair extends shrouded turbine blade notch crack recovery from 0.03 to 0.1 inches, reducing blade replacement.

Internal braze chambers and feed channels deliver filler into narrow superalloy gaps, limiting distortion and micro-cracking while holding tight tolerances.

A mechanically retained replaceable blade tip enables advanced cooling passages beyond casting limits, cutting cooling air use and extending life.

A formed metal foam core with a sprayed shell and tuned openings cuts weight, machining waste, and noise while maintaining rigidity.

Tangential oil flow and a widening annular passage spin out debris before filtration, extending filter life and reducing turbine engine maintenance.

Preformed blade shield sheets gain additively built reinforcement before core compression, cutting machining waste and tool wear.

A lattice cell with a gyrating mass absorbs turbine vibration energy for damping, energy storage, and non-destructive shutdown.

A sintered metal-powder coating with soluble ceramic particles creates turbine porosity that improves heat transfer, durability, and coating adhesion.