发明申请
US20120279224A1 GAS TURBINE ENGINE COMBUSTOR 有权
燃气轮机发动机

GAS TURBINE ENGINE COMBUSTOR
摘要:
A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.
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