| 摘要 |
In order to avoid plugging the air passageways (70) of fuel injectors (42) with carbon particles in a gas turbine engine (10), the gas turbine engine (10) includes an annular combustor (18) having radial dilution air injection. The gas turbine engine (10) also includes a rotor (12) having turbine blades (14) and a nozzle (16) adjacent the turbine blades (14) which is adapted to direct hot gases at the turbine blades (14) to cause rotation of the rotor (12). The annular combustor (18) is disposed about the rotor (12) and has an outlet (20) to the nozzle (16), spaced inner and outer walls (22 and 24), and a generally radially extending wall (26) connecting the inner and outer walls (22 and 24). The gas turbine engine (10) further includes a housing (28) substantially surrounding the annular combustor (18) in spaced relation to the inner, outer, and radially extending walls (22, 24 and 26) to define a dilution air flow path (30). The annular combustor (18) further includes a combustion annulus (36) defined by the inner, outer, and radially extending walls (22, 24 and 26, respectively), and a plurality of radially disposed air blast fuel injectors (42). The gas turbine engine (10) also includes dilution air holes (48, 52 and 56) for bleeding air into the combustion annulus (36) to produce a localized cooling air film on the inwardly facing surfaces of the inner, outer and radially extending walls (22, 24 and 25, respectively). With this arrangement, the gas turbine engine includes screens or mesh for preventing matter potentially obstructive to the fuel injector air passageway from passing from a dilution air hole into a fuel injector air passageway.
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