| 摘要 |
A multi-stream fuel injector for a gas turbine engine comprises a plurality of concentric member which define a plurality of flow passages carrying HP compressor air or fuel/air mixture (29,34). One of the members is formed with a wide-angle, frusto-conical flared lip (43,48) to propagate a wide-angle fuel/air mixture cone in the combustion region. The lip is of such a cross-sectional configuration that air flowing over the lip surface remains attached to the surface and flows in a non-turbulent manner, initially in a radially inward direction, and subsequently in a radially outward direction. The lip ensures that undesirable regions of recirculation are avoided around the fuel injector. |
