Turbines TRIZ Cases

A nickel-based alloy powder with precise compositional control enables additive manufacturing of components.

Wire feed laser welding eliminates powder demixing to produce homogeneous TiAl structural elements.

A multi-cast turbine airfoil joins distinct alloy sections using friction welding to preserve local material properties.

A turbine joint uses carbides and nitrides to block carbon and nitrogen diffusion between steel and TiAl alloy members.

Segmented scoops and O-ring seals prevent fluid loss while ensuring reliable lubrication in gas turbines.

Preheating the mold reduces adhesion to facilitate demolding, while compacting the powder mixture at high pressure improves mechanical strength.

A bridge portion connects an overhanging component to its support structure via a void of unconsolidated powder.

Directed energy fuses metal powder to create complex film cooling holes, overcoming conventional machining shape limits.

A boron-modified repair material bonds to parent metal via a sacrificial preform, restoring sealing interface integrity while preserving temperature resistance.

A dual-metal rotor design uses layered materials with an intermediate gradient to increase stiffness and manage thermal expansion forces.

Three-dimensional weaving of metal yarns followed by hot isostatic pressing creates solid reinforcing structures.

Combining a ceramic base with an additive metal portion creates intricate cooling circuits that conventional casting cannot produce.

Angled clip surfaces and notched relief areas distribute centripetal loads to prevent weld joint cracking in multistage gas turbines.

Laser drilling creates effusion cooling holes with excess material that deforms to reduce the effective exit diameter.

Segmenting ceramic cores and nesting mandrels prevents cracking during casting of complex internal passages.

A short-pulse laser ablates a protection layer on metal to enable high-precision processing.

Additive manufacturing deposits compositional gradients between material sections in hybrid compressor blades, eliminating crevice corrosion at interfaces.

Forming a near-net shape shield with a nickel intermediate layer reduces machining time and prevents carbon dilution cracking in turbine blades.

Integrating a helical pump into the shaft reduces system complexity and maintenance costs while ensuring reliable lubrication.

Embedding a metallic core via metal injection molding creates a composite shroud that resists crack propagation and hot gas ingestion.

Non-circular lattice branches inside turbine walls enhance convective cooling, resolving thermal management and structural integrity trade-offs.

Additive manufacturing builds an integral combustor liner and turbine nozzle, reducing device complexity while maintaining structural integrity.

Segmenting the coating resolves insufficient bonding between oxide dispersion strengthened alloys and superalloy substrates.

A superalloy brazing fixture uses tab and tab lock couplings to assemble modular members without welding.

A combined heat and power system uses an exhaust bypass channel to route gas around the recuperator.

Microstructural elements on connecting surfaces ensure precise braze joint gaps during thermal processing.

Acoustic cavitation drives abrasive particles against additive manufactured components, resolving internal channel finishing bottlenecks.

Direct powder pressing into a rotor sleeve creates a secure magnetic core fit without separate assembly steps.

Dissolving sacrificial cores within the hub creates stress distribution tunnels, reducing low cycle fatigue and extending operational lifespan.

Hot pressing consolidates low-density metal powder into hollow fan blades, avoiding complex machining and shape prediction issues.

A plunger-based lubrication applicator immerses bolts in anti-seize compound to coat threaded sections and thrust faces.

Binder jet printing creates complex green bodies from refractory powders for subsequent chemical vapor infiltration densification.

Layer-by-layer additive manufacturing merges turbine, compressor, and shaft portions to eliminate subsurface defects from traditional casting processes.

Crack resistant features reduce thermal stress cracking in additive manufactured gas turbine components.

Partition wall with oblique portion reduces flow-passage cross-sectional area to increase cooling medium velocity.

Upstream strainer and magnetic detection module filter ferromagnetic debris to prevent clogging and improve measurement precision.

Internal pedestals in a gas turbine casing boss receive bolt threads, reducing weight by minimizing boss height and material usage.

A flexible impingement insert uses a spring element to bias side walls into an expanded position for hot gas path cooling.

Windage-suppressor shroud channels high-pressure gases away from oil reservoirs, preventing lubricant entrainment and minimizing oil loss.

Dynamic parameter adjustment prevents beam breakthrough and insufficient solidification, ensuring consistent quality in additive manufacturing.

Additively manufactured inner tubes integrally join to outer tubes, eliminating brazed joints that cause fluid leaks and fires.

Additive deposition of a transition ring joins the outer blade ring to the hub disk, eliminating complex machining and leakage paths.

Braided fabric embedded in aluminum-lithium alloy forms a lightweight metal matrix composite airfoil.

Coiled passages reduce effective mass density in gas turbine rotor discs, lowering weight and material costs while maintaining structural integrity.

Diffusion bonding with a nanoparticle foil joins superalloy turbine components without inducing cracks or degrading creep resistance.

Additive materials lower the repair melting temperature, enabling diffusion into shaped cavities to restore sealing interface integrity and prevent air leakage.

Additive manufacturing forms a gas turbine support housing with complex internal flow paths, overcoming the high cost of conventional machining.

Segmented metal blocks accommodate long composite inserts during hot isostatic compacting, eliminating lengthy compression cycles and costly welding steps.

A laser ablation system uses laser-induced breakdown spectroscopy to monitor coating composition during removal.

Segmented radial retention eliminates large fasteners, allowing independent nozzle insert removal for flow testing while protecting expensive engine modules.