| 摘要 |
A gas turbine engine combustor fuel-air mixer (28) includes a body (38) having a substantially annular venturi (40) and a longitudinal axis (42) therethrough, an upstream end (44), a downstream end (46), and an inner surface (48). A primary radial jet swirler (50) upstream of the venturi (40) includes a plurality of radially extending primary air jets (56) circumferentially and downstream angled with respect to the longitudinal axis (42). A plurality of axial jets (71) axially extend through the primary swirler air and are circumferentially disposed around the longitudinal axis (42). An exemplary embodiment of the fuel-air mixer (28) further includes the axial jets (71) and the inner surface (48) of a throat (73) of the venturi (40) being radially located at a radius (R) from the longitudinal axis (42). The axial jets (71) are located in an insert (80) mounted to an upstream portion (52) of the primary radial jet swirler (50) and axially forward of the plurality of radially extending primary air jets (56). At least some of the axial jets have jet centerlines that intersect primary swirler centerlines of corresponding ones of the primary air jets (56) downstream of outlets of the primary air jets (56). |
