A fuel nozzle for a gas turbine engine is constructed with two major castings where one is the support and the other is the head, both welded together adjacent the fuel orifice plate. The fuel passage is cast into the support providing a smooth radius from the radial to axial flow path and a smooth transition from the circular to the annular cross section. This configuration allows dimension control over the filming lip and other critical dimensions of the nozzle.
申请公布号
DE3472829(D1)
申请公布日期
1988.08.25
申请号
DE19843472829
申请日期
1984.05.15
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
PANE, FRANCIS CHARLES, JR.;MATTHEWS, JOHN ANTHONY;WRIGHT, RICHARD ROBERT;SARNIK, JOHN MEYERS;FRASCA, THOMAS