Turbines TRIZ Cases

Pressurized fluid inside hollow airfoils attenuates laser energy during drilling, preventing back strikes and avoiding wax or epoxy filling.

A slotted shell guides brazing paste onto impeller blade tips to prevent overflow, simplify joining, and improve shroud bond consistency.

An additively manufactured coupon stores braze internally and releases it by heating to improve infiltration, bond strength, and repair durability.

Segmented additive manufacture of a gas turbine bearing housing integrates fluid conduits and cuts build time and cost without sacrificing integrity.

A phase-change material in the aircraft engine lubricant conduit absorbs shutdown heat to prevent coking, blockages, and lubricant breakdown.

Segmented cooling cavities in an additively built gas turbine squealer tip cut cooling fluid use while improving tip cooling and stress control.

A hybrid PIM and additive process enables customized sintered parts with high surface accuracy, including hollow structures and small-run production.

Rounded stub contours sized to at least twice the welding eccentric improve material mixing and thermal homogeneity in turbomachine blade welds.

A guided rotating cutter smooths rough down-facing surfaces in additively manufactured internal channels to improve flow before final finishing.

Additive braze powder deposition, low-temperature sintering, and structured light scanning cut repair waste and substrate defects.

Linear friction welding joins homogeneous blade material to a disk, reducing waste while preserving cold-dwell fatigue life.

Shifting the laser focal position across Z-levels drills multiple curved-surface holes efficiently while limiting heat buildup and material damage.

Extracted lubricant is filtered, conditioned, and recirculated to wind turbine bearings to limit contamination, reduce wear, and improve power transfer.

A tuned Co-Cr-Ni-W-Al-Ta-C alloy improves DLD repair of turbine parts by balancing laserability, ductility, oxidation resistance, and porosity.

A partial AM aft frame and tapered transition replacement removes weld-limited structures, cuts corrosion, and extends gas turbine combustor life.

Recirculating extracted lubricant through filtration and feedback control keeps wind turbine bearings clean, well-lubricated, and less prone to wear.

A one-piece additive flame tube forms double-wall cooling channels that cut end-wall thermal stress, machining, and assembly time.

A de-aerator-fed lubrication loop separates air before pump recirculation, cutting tank oil volume and limiting air ingestion in flight.

A two-stage low- then high-energy deposition builds bosses on thin alloy parts while limiting thermal damage and deformation.

Alternate lubrication ports feed fresh grease between bearing rows so downwind rollers avoid degraded lubricant and premature wear.

An open bearing interior with overflow and equalizing channels drains oil without pressure, reducing leakage and maintenance in wind turbines.

Adjusting neighboring laser scan spacing to melt-pool width reduces microstructure anisotropy and improves strength uniformity in additively built parts.

Two separated sensors monitor upper and lower oil zones in a curved turbomachine tank, easing installation, maintenance, and leak control.

A bounded gutter-to-gearbox volume ratio improves lubricant scavenging while limiting windage loss, weight, and space in turbine gearboxes.

A guided drilling and extension system removes internal blade bulkheads to open tip access for wind turbine ice protection installation.

A movable outer race in a cageless rear bearing absorbs thermal expansion differences to prevent seizure and axial positioning errors.

Thermal cycling moves a mesh sleeve inside hydrocarbon conduits to break up coke deposits, maintain flow, and cut turbine maintenance.

Oversized attachment margins and electrode-guided joining improve cropped airfoil alignment, repair yield, and net-shape restoration.

Bulk laser ablation followed by mechanical finishing machines blind openings in CMCs faster while preserving surface integrity and accuracy.

A low-resistance bypass routes lubricant to the reduction gear at low speed, maintaining pressure, cooling, and gear protection.

Controlled cooling and holding in a vacuum furnace create segregated crystallization that raises brazed joint liquidus temperature.

By removing the worn tip and additively rebuilding it, this repair restores airfoil tip cooling passages without weld cracking or back-wall damage.

A convex ablative region on the vane concave sidewall erodes during testing to form the aerodynamic surface and preserve engine life.

Fluid pressure balancing across a thrust disc stabilizes pump shafts, reducing axial oscillation, friction losses, and bearing wear.

A deflected waterjet guided laser enables precise machining of complex 3D and non-line-of-sight features in hard, brittle CMCs.

Laser-induced plasma and cavitation finish complex internal surfaces faster, with lower contamination and preserved dimensional integrity.

Symmetrical vane halves are brazed to form flow passages, improving dimensional control and reducing casting-related metallurgical shortfalls.

Fiber laser treatment removes weak oxide and contaminants, then forms a porous titanium oxide layer for more consistent adhesive bonding.

Alternating dense and porous layers during additive manufacture reduces intrinsic stress and cracking in nickel- or cobalt-based superalloys.

A constraining member contains braze during heat treatment, enabling denser near-net-shape turbomachine repairs with fewer process steps.

Directed energy deposition rebuilds damaged stator vane edges with lower heat input, reducing distortion and repair time versus manual TIG welding.

A pressure-biased bypass valve isolates a leaking turbine engine heat exchanger while maintaining oil flow and adaptive cooling control.

Burning debris with a single current pulse and measuring energy lets engine chip detectors separate harmless fuzz from real chips and estimate size.

Cooling air flows through sintered channels between hot and cold turbine walls to limit heat damage and maintain engine performance.

Direct metal laser sintering integrates injector and thrust chamber features to cut assembly cost while improving cooling and pressure drop.

Hot compression of deposited metal beads before full cooling reduces residual stress, oxidation, porosity, and anisotropy while improving layer bonding.

Removing the worn tip rail, 3D printing an extension, and machining it back restores cooling passages while avoiding weld cracking.

Utility-guided insertion and reinsertion heuristics improve network path sequencing when brute-force optimization is too slow for large constrained jobs.

A retention-member blade tip attachment enables replaceable cooling passages, improving heat transfer while reducing cooling air use.