초록 ▼

A combustor for a gas turbine engine includes inner and outer liners with a row 112, 114 of dilution air holes penetrating through each liner. The row 114 of holes in the outer liner comprise at least a set of large size, major outer holes 116 and may also include a set of smaller size minor outer h

A combustor for a gas turbine engine includes inner and outer liners with a row 112, 114 of dilution air holes penetrating through each liner. The row 114 of holes in the outer liner comprise at least a set of large size, major outer holes 116 and may also include a set of smaller size minor outer holes 118 circumferentially intermediate neighboring pairs of the major outer holes. The row 112 of holes in the inner liner include dilution air holes circumferentially offset from the major outer holes and may also include a set of minor holes 122 circumferentially intermediate major inner holes 120 . The major and minor holes admit respective major and minor jets of dilution air into the combustor. The unique distribution of major and minor holes and the corresponding major and minor dilution air jets helps to minimize NOx emissions and regulates the spatial temperature profile of the exhaust gases discharged from the combustor.

대표청구항 ▼

1. A combustor for a turbine engine, comprising:an outer liner having a row of circumferentially distributed outer combustion air holes penetrating therethrough, the outer holes comprising larger size major outer holes and smaller size minor outer holes circumferentially intermediate neighboring pai

1. A combustor for a turbine engine, comprising:an outer liner having a row of circumferentially distributed outer combustion air holes penetrating therethrough, the outer holes comprising larger size major outer holes and smaller size minor outer holes circumferentially intermediate neighboring pairs of major outer holes; andan inner liner circumscribed by the outer liner and having a row of circumferentially distributed inner combustion air holes penetrating therethrough, the inner row of holes being substantially axially aligned with the outer row of holes, the holes of the inner row being circumferentially offset from the major outer holes. 2. A combustor for a turbine engine, comprising:an outer liner having exactly one row of circumferentially distributed outer combustion air holes penetrating therethrough, the outer holes comprising larger size major outer holes and smaller size minor outer holes circumferentially intermediate neighboring pairs of major outer holes;an inner liner circumscribed by the outer liner and having exactly one row of circumferentially distributed inner combustion air holes penetrating therethrough, the inner row of holes being substantially axially aligned with the outer row of holes, the inner holes comprising larger size major inner holes, circumferentially offset from the major outer holes, and smaller size minor inner holes circumferentially intermediate neighboring pairs of major inner holes; andan array of fuel injectors, each injector being substantially circumferentially aligned with a major outer combustion air hole. 3. The combustor of claim 1 wherein the row of outer combustion air holes comprises circumferentially alternating larger size major holes and smaller size minor holes. 4. The combustor of claim 2 wherein the row of outer combustion air holes comprises circumferentially alternating major and minor holes, and the row of inner combustion air holes also comprises circumferentially alternating major and minor holes. 5. The combustor of claim 1 or 2 wherein the liners have an axial length and the inner and outer rows of combustion air holes penetrate the liners no further aft than about midway along their axial length. 6. The combustor of claim 5 wherein the inner and outer rows of combustion air holes penetrate the liners at about midway along their axial length. 7. The combustor of claim 1 or 2 wherein each liner comprises a support shell, a forward heatshield secured to a forward portion of the support shell and an aft heatshield secured to an aft portion of the support shell. 8. The combustor of claim 7 wherein a plurality of impingement cooling holes penetrates each support shell and a plurality of film cooling holes penetrates each heatshield. 9. A combustor for a turbine engine, comprising:an outer liner having exactly one row of circumferentially distributed outer dilution air holes penetrating therethrough, the outer dilution air holes comprising larger size major outer holes and smaller size minor outer holes circumferentially intermediate neighboring pairs of major outer holes;an inner liner circumscribed by the outer liner and cooperating therewith to define an annular combustion chamber, the inner liner having exactly one row of circumferentially distributed inner dilution air holes penetrating therethrough, the inner row of holes being substantially axially aligned with the outer row of holes, and the holes of the inner row being circumferentially offset from the major outer holes; anda combustor front end assembly serving as the exclusive vehicle for introducing primary combustion air into the combustion chamber. 10. A combustor for a turbine engine, comprising:an outer liner having exactly one row of circumferentially distributed outer dilution air holes penetrating therethrough, the outer dilution air holes comprising larger size major outer holes and smaller size minor outer holes circumferentially intermediate neighboring pairs of major outer holes;an inner li ner circumscribed by the outer liner and cooperating therewith to define an annular combustion chamber, the inner liner having exactly one row of circumferentially distributed inner dilution air holes penetrating therethrough, the inner row of holes being substantially axially aligned with the outer row of holes, the inner dilution holes comprising larger size major inner holes, circumferentially offset from the major outer holes, and smaller size minor inner holes intermediate pairs of the major inner holes; anda combustor front end assembly serving as the exclusive vehicle for introducing primary combustion air into the combustion chamber. 11. The combustor of claim 9 wherein the dilution holes of the outer row comprise circumferentially alternating larger and smaller holes. 12. The combustor of claim 10 wherein the holes of the outer row comprise circumferentially alternating major and minor holes and the holes of the inner row comprise circumferentially alternating major and minor holes. 13. The combustor of claim 9 or 10 wherein the liners have an axial length and the inner and outer rows of dilution holes penetrate the liner no further aft than about midway along their axial length. 14. The combustor of claim 13 wherein the inner and outer rows of dilution holes penetrate the liners at about midway along their axial length. 15. The combustor of claim 9 or 10 wherein each liner comprises a support shell, a forward heatshield secured to a forward portion of the support shell and an aft heatshield secured to an aft portion the support shell. 16. The combustor of claim 15 wherein a plurality of impingement cooling holes penetrates each shell and a plurality of film cooling holes penetrates each heatshield. 17. The combustor of claim 9 or 10, wherein the combustor front end assembly comprises:a hood extending radially between forward ends of the inner and outer liners;a guide assembly also extending radially between the forward ends of the liners; anda fuel injector projecting through the hood and the guide assembly, the hood, guide assembly and fuel injector having passageways for delivering primary combustion air to the combustion chamber. 18. A combustor for a turbine engine, comprising:an outer liner having exactly one row of circumferentially distributed outer combustion air holes penetrating therethrough, the outer holes comprising larger size major outer holes and smaller size minor outer holes circumferentially intermediate neighboring pairs of major outer holes;an inner liner circumscribed by the outer liner and having exactly one row of circumferentially distributed inner combustion air holes penetrating therethrough, the inner row of holes being substantially axially aligned with the outer row of holes, the inner holes comprising larger size major inner holes, circumferentially offset from the major outer holes, and smaller size minor inner holes circumferentially intermediate neighboring pairs of major inner holes;wherein the liners have an axial length and the inner and outer rows of combustion air holes penetrate the liners at about midway along their axial length.