FUEL NOZZLE FOR A COMBUSTOR OF A GAS TURBINE ENGINE

摘要

A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages.

主权项

1. A fuel nozzle for a gas turbine, comprising:
a. a main body, the main body having an upstream end axially separated from a downstream end, the main body at least partially defining a fuel supply passage that extends through the upstream end and at least partially through the main body; b. a fuel distribution manifold disposed at the downstream end of the main body, the fuel distribution manifold having a plurality of axially extending passages that extend through the fuel distribution manifold; and c. a plurality of fuel injection ports, each fuel injection port defining a flow path between the fuel supply passage and a respective one of the plurality of axially extending passages.