Additive manufactured fuel nozzle core for a gas turbine engine
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United States of America Patent
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May 22, 2018
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N/A
app pub date -
Oct 1, 2014
filing date -
Oct 4, 2013
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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.
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