초록 ▼

The invention relates to a simple low cost fuel nozzle support stem that can be manufactured to meet extremely close tolerances with enhanced structural rigidity through use of a cylindrical stem body machined from solid bar stock. Superior thermal control to regulate thermal displacement of the ste

The invention relates to a simple low cost fuel nozzle support stem that can be manufactured to meet extremely close tolerances with enhanced structural rigidity through use of a cylindrical stem body machined from solid bar stock. Superior thermal control to regulate thermal displacement of the stem body and to prevent fuel coking is provided by a concentric secondary fuel bore and a primary fuel tube disposed within the bore. The low pressure secondary fuel flow encircles the high pressure primary flow tube and serves to cool the fuel tube and cylindrical stem body in a uniform symmetric manner. An outer cylindrical insulating sleeve mounted on shoulders extending from the cylindrical body of the stem defines an elongate annular insulating air gap between the sleeve and cylindrical stem body. The support stem includes a dual fuel spray nozzle and a fuel adapter/mounting flange that are mounted to the stem body with simple cylindrical sockets. Therefore, the support stem has a modular construction based on a simple cylindrical easily machined stem body with concentric primary and secondary fuel channels, a fuel adapter/mounting flange with cylindrical socket brazed to an outer end of the stem body, and a replaceable nozzle with cylindrical socket brazed to an inner end of the stem body.

대표청구항 ▼

[ We claim:] [1.]1. A fuel nozzle support stem for delivering a primary liquid fuel and a secondary liquid fuel to be mixed with compressed air in the combustor of a gas turbine engine, the stem having: a longitudinal axis; an elongate substantially cylindrical body symmetric about the axis and havi

[ We claim:] [1.]1. A fuel nozzle support stem for delivering a primary liquid fuel and a secondary liquid fuel to be mixed with compressed air in the combustor of a gas turbine engine, the stem having: a longitudinal axis; an elongate substantially cylindrical body symmetric about the axis and having an outer diameter D.sub.0 and length L; an inlet end with primary and secondary liquid fuel inlet ports; and an outlet end with primary and secondary liquid fuel outlet ports, the support stem having a concentric longitudinal secondary liquid fuel bore having an inner diameter D.sub.I and communicating between the secondary inlet port and the secondary outlet port, and a concentric primary liquid fuel tube disposed within the bore, sealed to the inlet and outlet ends of the support stem and communicating between the primary inlet port and the primary outlet port; wherein D.sub.0 is greater than 2D.sub.I, and L is less than 10(D.sub.0 -D.sub.I').