| 摘要 |
<p>A fuel nozzle support stem for a gas turbine engine the stem having: a longitudinal axis (9); an elongated substantially cylindrical body (4) symmetric about the axis and having an outer diameter D0 and Length L; an inlet end (11) with primary (12) and secondary (13) fuel inlet ports; and an outlet end (14) with primary (15) and secondary (16) fuel outlet ports, the support stem having a concentric longitudinal secondary fuel bore (17) having an inner diameter DI and communicating between the secondary inlet port and the secondary outlet port, and a concentric primary fuel tube (20) 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 Do is greater than 2DI, and L is less than 10 (Do - DI).</p> |
