A variable displacement pump driven by an accessory gearbox adjusts oil flow to match epicyclic gear speed.
Bonding segmented arched pieces with thermal growth constraints eliminates leakage and reduces weight in turbine rotors.
Removing surrounding metal creates a support surface for an inserted structure, preventing material deposition into internal channels during fusion.
Temporary protuberances stiffen asymmetrical gas turbine blades during injection molding to control dimensions and reduce material loss.
A vascular engineered lattice structure circulates cooling air through a gas turbine platform to manage thermal loads.
Welding tool prevents splatter contamination during aerofoil-to-stub fusion, resolving load transmission and weight trade-offs.
Shielded axial mid-section with insulator reduces heat transfer from lubricating fluid to core airflow, improving thermal efficiency.