Turbines TRIZ Cases

Precise multi-element alloying balances creep strength and dwell fatigue crack growth, resolving thermal stability trade-offs in gas turbine components.

Variable lattice density in a cabin air compressor rotor reduces weight while managing stress and deflection.

Segmenting large components into sections with position features allows machining back failures to recover material, preventing total build loss.

Radial ribs distribute centrifugal stress to reduce mass and enable higher rotational speeds.

Grain selectors grow large single crystals in superalloy castings to eliminate grain boundaries and prevent heat affected zone cracking.

A method additively manufacturing a sacrificial crucible to directionally solidify metal materials into complex components.

Segmented double-walled fairings with auxetic seals direct cooling air radially inward, resolving material selection limits at high operating temperatures.

Low-melt alloy preforms repair turbine blade tips without cracking the base material.

Integral additive manufactured spring assemblies eliminate twisting and stress concentrations in gas turbine bypass valves.

Inclined dividing walls support additive layer manufacturing of dual wall components with internal cooling passages.

A tip member with an airfoil cross-section and a directional opening receives a blade post for metallurgical bonding.

Optical detection records surface brightness values to calculate additive manufacturing scan speed, resolving measurement precision versus device complexity.

Fusion welding connects turbine blades to disks through an additive connecting body, resolving strength and apparatus complexity trade-offs.

Segmented core geometry with inclined channels resolves trapped powder issues in additive layer manufacturing, ensuring reliable dual wall component production.

Integrating a cambered ring airfoil with the rotor hub generates additional thrust while reducing overall system weight and drag.

Imaging-guided tenon formation aligns airfoil tip and body portions, resolving laborious manual alignment issues during turbine blade repair.

Segmented trailing edge cooling channels use partial pressure drop members to reduce excess airflow and minimize aerodynamic losses.

A turbine nozzle repair method salvages the inner band by severing it from damaged vanes and casting a replacement assembly.

Amorphous melt-spun solder foil with nanometer surface coating prevents recrystallization during repair of single-crystal turbine blades.

Segmented rings with oxide braze joints reduce gas leakage while simplifying thermal barrier coating application.

Segmented fine and coarse filters with a bypass valve maintain lubricant flow when pressure builds, allowing selective maintenance.

Copper-nickel alloy powder deposition creates complex turbomachine blades with high thermal conductivity.

Selective laser sintering creates enclosed unfused powder pockets within a metallic gas turbine casing body to form an abradable liner.

Sintering assembled metallic greenbodies creates strong bonds that overcome casting size limits and improve heat dissipation.

Corrugated blade surfaces generate discrete vortices to accelerate wake mixing.

Gaseous nitrogen incorporation resolves the contradiction between oxidation resistance and mechanical strength in refractory metal composites.

Constant stress springs maintain uniform pressure on alloy pads, preventing component distortion and extending tooling life.

Teeth on a self-breaking inner band fracture under thermal stress to relieve distortion during additive manufacturing of complex turbomachine geometries.

Automated optical detection replaces subjective manual inspection with objective parameter comparison, eliminating post-weld testing costs.

A method tailors grain size in additive manufactured components by applying distinct process parameters to different volumes.

Curved mold extensions prevent backing formation during de-casting, enabling taller part production.

Outwardly extending portion with side face creates a gap for weld flash material to pass through during oscillatory motion.

Flash sintering forms complex turbine blades with homogeneous microstructures by applying simultaneous pressure and current.

External detection device captures spatially resolved thermal radiation from additive manufacturing layers to generate composite three-dimensional images.

Direct metal laser sintering forms monolithic particle separators to prevent compressor erosion while eliminating complex assembly maintenance.

Inserts a weld member into turbine core openings to seal internal passages without fully liquefying the filler material.

Welding separately manufactured housing elements to a blank eliminates large machining allowances, cutting time and cost.

Nickel-based weld filler additive prevents liquation cracking in high gamma prime Rene 108 alloys while maintaining mechanical strength.

Segmented bonding areas and peripheral gaps reduce thermal stress, preventing delamination in gas turbine components.

Laser projection constructs rim flanges on turbine blades, replacing foundry processes to improve sealing and abrasion resistance.

Additive manufactured microchannels create a closed cooling film, resolving insufficient thermal protection in high-temperature turbine blades.

Precipitated carbides enhance creep rupture time, overcoming the mechanical property gap between cobalt and nickel alloys.

A spring-less check valve with a buoyant plug manages oil levels in gas turbine engines.

A porous brazing material support holds molten filler within its pores during heating to bond repair areas on complex geometries.

Directed energy deposition eliminates ceramic core removal complexity by building dual wall gas turbine components with integrated cooling channels.

Segmented tubular members form flow passages within a gas turbine support structure, reducing manufacturing complexity while maintaining structural strength.

Controlled braze cycles bond filler to seal teeth while solutioning the base metal, eliminating costly manual welding and re-machining steps.

Segmenting the protection chamber into a fixed base and movable extension resolves oxidation protection versus curved surface adaptability.

Mechanically drilling cooling apertures through combustion chamber heads from the downstream side using a rotating tool.