초록 ▼

A low emissions combustor can 18 for an aircraft gas turbine engine includes a louvered combustor liner 24 with three arrays of dilution holes 52, 54, 56. The first hole array comprises twelve equally sized, equiangularly distributed holes that penetrates the liner about midway along its axial lengt

A low emissions combustor can 18 for an aircraft gas turbine engine includes a louvered combustor liner 24 with three arrays of dilution holes 52, 54, 56. The first hole array comprises twelve equally sized, equiangularly distributed holes that penetrates the liner about midway along its axial length. The second hole array comprises twelve equally sized holes, smaller than the holes of the first array, that penetrate the liner a predetermined distance aft of the first hole array. The holes of the second array are equiangularly distributed and each second hole is circumferentially aligned with a first hole. A third hole array penetrates the liner a predefined distance aft of the first array. The third holes are nonuniformly sized and nonequiangularly distributed to regulate the spatial temperature profile of combustion gases exiting the combustor can. The quantity, size, distribution and location of the holes mitigates undesirable exhaust emissions without affecting the performance or durability of the engine. Accordingly, the combustor can may be used to replace an existing combustor can in an older generation gas turbine engine.

대표청구항 ▼

[ We claim:] [1.] A combustor can for a turbine engine, comprising:a liner comprising a set of eleven axially adjacent louvers, the liner having a centerline, a forward end with a fuel injector port extending therethrough and an aft end terminating at a trailing edge, the liner circumscribing a comb

[ We claim:] [1.] A combustor can for a turbine engine, comprising:a liner comprising a set of eleven axially adjacent louvers, the liner having a centerline, a forward end with a fuel injector port extending therethrough and an aft end terminating at a trailing edge, the liner circumscribing a combustion zone and having an effective axial length;a first array of dilution holes penetrating the liner about midway along the effective axial length of the liner and penetrating through the sixth of the eleven louvers;a second array of dilution holes penetrating the liner a predetermined distance aft of the first array and penetrating through the seventh of the eleven louvers, each hole of the second hole array being substantially circumferentially aligned with a hole of the first hole array; anda third array of dilution holes penetrating the liner aft of the second array and a predefined distance aft of the first array and penetrating through the tenth of the eleven louvers, the holes of the third array being nonequiangularly circumferentially distributed and irregularly sized.