| 摘要 |
A combustor (30) for a gas turbine engine comprises an annular combustion chamber (31) having radially outer and inner rows of fuel injectors (19 1 , 20 1 ) disposed concentrically in the combustor head wall (32). Injectors in one of the rows are in angular registration with spaces between injectors in the other row. Each fuel injector comprises a means for producing a fuel/air mixture having a swirling motion, and a mixing duct located downstream of the means for producing the fuel/air mixture. Each mixing duct opens into the combustion chamber (31) through the combustor head wall (32) and has a length sufficient to allow at least partial mixing of the fuel/air mixture before entry to the combustion chamber as a divergent swirling stream (38, 40). Mixing ducts in the first and second rows of injectors have longitudinal centre-lines (L1 1 , L2 1 ) oriented to coincide with generating rays of respective first and second imaginary conical surfaces. These conical surfaces intersect at an included angle (2D) (Fig.3A) within a primary combustion zone in the combustion chamber, whereby injectors (19 1 , 20 1 ) located in different rows are angled towards each other in the downstream direction and the divergent swirling streams of fuel/air mixture (38, 40) coming from different rows cross in the combustion chamber in an interdigitating manner. This creates a strong mixing interaction between the streams from different rows and enhances uniformity and rapidity of combustion in the primary combustion zone. |
