Turbines TRIZ Cases

A non-uniform electric field deflects a waterjet-guided laser to machine complex 3D and non-line-of-sight CMC features with less repositioning.

Additive manufacturing forms a monolithic shaft, rotor, and channeled support structure to improve thermal stress distribution and durability.

Vibratory finishing with alumina and copper media smooths rough laser powder bed turbine parts, including complex geometries.

Pressure and electrical current fuse cast blade zones to preserve alloy bond integrity while improving turbine thermal performance.

A Cr-Ni-C ferrochrome composition resolves the hardness-corrosion tradeoff, delivering HV400+ hardness with strong chromium-oxide protection.

A counter-flow cooling passage and heat-transfer matrix boost aircraft engine oil cooling while reducing separate heat-exchanger weight and bulk.

Cutting heat preheats the deposition region before metal addition, preventing cracking and reducing system complexity and processing time.

A capacitive detector uses a strainer to pass harmless fuzz and retain larger metallic chips, cutting false alarms in engine fluid monitoring.

Selective laser melting tailors microstructure and porosity to rebuild turbine blade crowns in crack-prone nickel superalloys.

A porous AM repair coupon with an interlocking anchor improves braze infiltration, joint strength, oxidation resistance, and material use.

Varying coupon porosity guides braze infiltration to strengthen repaired joints, cut metal use, and improve post-repair performance.

Tailored coupon porosity drives braze infiltration to strengthen repair joints, lower metal use, and tune thermal and mechanical properties.

A porous AM metal coupon with an anchor improves turbomachine component repairs by boosting braze infiltration, bond strength, and oxidation resistance.

Controlled porosity in an AM repair coupon directs braze infiltration to strengthen joints, improve stress resistance, and reduce metal use.

An AM porous region with braze infiltration joins dense repair sections, cutting joint stress while improving bond strength and oxidation resistance.

Selective inspection and cleaning of deposited internal passages preserves rough walls for heat transfer while avoiding pressure loss in cooling flow.

Current and load fuse separately cast blade zones, enabling multi-alloy turbine airfoils with high bond strength and thermal resistance.

A tapered nozzle and curved deflector separate air from engine oil without moving parts, cutting foaming and reservoir volume demand.

A brazed coating combines hardfacing, aluminum particles, and thermal oxidation to protect gas turbine contact surfaces from wear and high-temperature attack.

An acidic spray and filtration chamber removes laser-drilling recast layers from aviation engine blade cooling holes while reusing liquid.

A convex ablative vane region erodes during acceptance testing to form the aerodynamic surface and preserve turbine nozzle design life.

A startup gas source keeps oil mist flowing to turbine bearings before compressor pressure rises, removing manual grease filling.

Adjustable focal-plane optics keep turbine component regions in focus for accurate in-situ inspection and repair with less downtime.

A movable control box shifts away from the transmission component to create maintenance space while preserving compact equipment layout.

Surface probing and compensation vectors let a CNC laser adjust stand-off and orientation to drill accurate holes on deformed components.

Measured surface deviation guides laser stand-off and orientation compensation to drill accurate holes in deformed propulsion components.

A low-density lattice inside the pinion web cuts turbine gear mass while limiting rim deformation, vibration, and mixing losses.

A centrifugal load ring varies the labyrinth seal gap with compressor speed to cut radial leakage and improve shrouded compressor efficiency.

Sacrificial terminal portions localize thermal stress in additive manufacturing, enabling large hollow turbomachine parts with tighter shape tolerance.

Air pressure, flow, and temperature changes stop laser drilling at breakthrough, protecting underlying turbine component features.

Air pressure, flow, and temperature sensing detects laser cooling-hole breakthrough and stops drilling before underlying features are damaged.

A tailed laser beam weld fixes spacer posts with lower cracking and porosity, preserving vane clearance and reducing turbocharger vane binding.

A vacuum-brazed coating hardens micromixer tube surfaces to limit vibration wear in plate apertures, extending turbine combustor life.

Sinker EDM uses one component as the electrode to form matching surfaces, enabling narrow braze gaps with lower porosity in complex joints.

A monolithic additively manufactured shaft-rotor support uses circumferential channels and baffles to improve strength and thermal stress control.

A helical passage and partitioned settling section remove air from turbine oil mixtures, improving lubrication efficiency in bearings and gearboxes.

Computed tomography maps substrate defects so braze powder can be deposited, sintered, and diffusion bonded with less waste and fewer secondary defects.

Synchronized camera imaging tracks the laser-workpiece interaction in real time to control cooling aperture geometry and reduce post-machining inspection.

By venting air from oil mist inside the rotating shaft, this scoop design delivers more oil-rich lubricant to gas turbine bearings at high speed.

A de-aerator-fed pump loop removes air from returning lubricant while reducing tank dwell time, oil volume, and air-ingestion risk.

Internal annular cavities and a radial web fluid channel tune seal rotor coning and cooling in high-speed, high-temperature operation.

Build orientation and directed energy deposition align casing roughness with flow to cut pressure drop and improve gas turbine efficiency.

A cable-guided cutter head removes excess material from additively manufactured internal channels to smooth rough down-facing surfaces and improve flow.

Combining continuous and pulsed beam paths controls heat input in additive layers, improving surface finish and accuracy in thin walls and overhangs.

Laser cladding rebuilds damaged labyrinth seal teeth with the base material, improving bond strength and lowering repair cost.

Positive exhaust-manifold pressure and piston rings stop lubricating oil from leaking back into the turbocharger compressor.

Short and long laser pulses split perimeter and center ablation to limit heat-affected zones and keep acoustic panel holes uniform.

Machining, arc welding an intermediate layer, and direct energy deposition rebuild cast nickel-alloy walls while preventing HAZ liquation cracking.

An electrically controlled valve shifts oil flow to bypass a leaking turbine engine heat exchanger, preserving supply stability and flame-out resistance.

A fluid-filled deformable holding portion expands during heating to grip AM part blanks with less mechanical stress and easier powder removal.