| 摘要 |
A combustor arrangement for a gas-turbine engine has a longitudinal axis 'y'. The combustor includes a burner head (50 fig 3), a downstream combustion chamber (52 fig 3), at least one swirler (58 fig 3) for creating swirling air in the combustion chamber, and at least one fuel nozzle (60, 62, fig 3) disposed in the burner head for supplying fuel to the combustion chamber. The fuel nozzle is disposed in the burner head such as to give rise to a first angle ' a ' of exit of the fuel from a downstream face of the burner head of > Ò0{ with respect to a longitudinal axis of the combustor, this first angle lying in a first plane passing through the longitudinal axis, and termed 'tilt'. The fuel also exits at a second angle '…' from the downstream face of > Ò0{ with respect to the first plane, the second angle lying in a second plane orthogonal to the first plane, and termed 'swash'. Together, the first and second angles combine to provide a single fuel exit with a compound angle of fuel delivery. |
