Turbines TRIZ Cases

A stepped transient liquid phase joining process bonds metallic substrate segments using multi-stage thermal treatments.

Coated lattice supports erode via combustion flow, preventing debris risks and fluid obstruction in additively manufactured gas turbine engines.

A precipitation hardening stainless steel alloy uses nickel-titanium-vanadium-molybdenum composition to achieve high strength and toughness.

A two-layer molded repair part with a nickel-solder base and hard alloy mixture protects turbomachine openings from severe wear.

Retaining a multi-material canister as an integral component surface after isostatic pressing consolidates powder without sacrificial removal.

Zirconium dioxide prevents atomic interdiffusion between titanium-aluminum and steel alloys during thermal treatment, blocking brittle phase formation.

Gravity shaping transforms injection molded bodies into sintered combustor panels, preventing warpage and cracking during high temperature manufacturing.

Mold inserts form elongated cooling passages during powder injection molding, eliminating costly electric discharge machining.

A graded coefficient of thermal expansion composite structure joins dissimilar materials through layered fabrication.

Sintered preform hybrid hardface mixture brazed to turbine blade shrouds eliminates welding defects and porosity while enhancing shear strength.

Diffusion joints bond distinct structural airfoil segments, resolving the trade-off between single-material simplicity and multi-zone thermal resistance.

Segmented support members with recesses allow a pivoting tool to remove temporary structures without deforming the vane geometry during laser fusion.

A cold spray process deposits metallic powder onto a precipitate-strengthened alloy substrate without melting the particulates.

Forging and additive manufacturing create complex relief elements on a fan disk, reducing material waste from large blanks.

A dummy blade with integrated measurement devices aligns linear friction welding tooling in situ for precise rotor blade joining.

Vertical cooling structures retract from the build plate to cool components through unfused powder.

Consolidating powder in a mold cavity resolves manufacturing precision issues while maintaining structural integrity.

Stamping metal sheets around a shaped core enables precise diffusion bonding for turbine engine blade reinforcement inserts.

A single-crystalline substrate guides epitaxial growth of powder layers during additive manufacturing to establish consistent crystal orientation.

Induction heating creates a thermal gradient to promote directional solidification of brazing alloys on turbine blades.