Additive manufactured fuel nozzle core for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorJinQuan Xu
Life of this patent
Estimating the term…
Abstract
A method of manufacturing a fuel component for a gas turbine engine combustor includes additive manufacturing a sacrificial core and manufacturing a fuel component body at least partially around the sacrificial core. The sacrificial core is at least partially removed to at least partially define an internal geometry of the fuel component. An additively manufactured sacrificial core for a fuel component of a gas turbine engine combustor includes a first structure and a second structure. The first structure at least partially defines a first passage of the fuel component. The second structure at least partially defines a second passage of the fuel component. The second structure at least partially surrounds the first structure.
Claims20
A method of manufacturing a fuel component for a gas turbine engine combustor, the method comprising:
- additive manufacturing a sacrificial core;
- manufacturing a fuel component body at least partially around the sacrificial core;
- and
- at least partially removing the sacrificial core to at least partially define an internal geometry of the fuel component.
An additively manufactured sacrificial core for a fuel component of a gas turbine engine combustor, comprising:
- a first structure that at least partially defines a first passage of the fuel component;
- and
- a second structure that at least partially defines a second passage of the fuel component, the second structure at least partially surrounding the first structure.
Dependencies are inferred from the claim text.