| 摘要 |
A combustor for a gas-turbine engine includes a burner head, a combustion chamber disposed downstream of the burner head, a swirler means for creating a swirling flow of air in the combustion chamber, and a fuel nozzle (60) 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 of exit of the fuel from a downstream face of the burner head of > ±0° with respect to a longitudinal axis (74) of the combustor, this first angle lying in a first plane passing through the longitudinal axis. The fuel also exits at a second angle from the downstream face of > ±0° with respect to the first plane, the second angle lying in a second plane orthogonal to the first plane. |
