| 摘要 |
<p>A gas turbine combustion chamber (28) which has primary, secondary and tertiary combustion zones (36,40,44) in flow series has a secondary mixing duct (70) and a tertiary mixing duct (82). The secondary and tertiary mixing ducts (70,82) reduce in cross-sectional area from their intakes (78,88) to their outlet apertures (80,90) to provide an accelerating flow through the mixing ducts (70,82) to prevent the formation of recirculating zones. Fuel injectors (96,112) have fuel discharge apertures (106,120) downstream of any recirculating zones formed at the intakes (78,88). The fuel injectors (96,112) extend across a major portion of the width of the ducts (70,82) to effectively subdivide the ducts (70,82) over at least part of the streamwise length of the ducts (70,82). The portions (107,117) of the fuel injectors (96,112) within the ducts (70,82) are race track shaped in cross-section and the portions (105,115) outside the ducts are aerofoil shaped in cross-section. The fuel injectors (96,112) reduce in dimension perpendicular to the widthwise direction of the duct (70,82). <IMAGE></p> |
