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A combustor liner for a combustor of a turbine engine includes a single-walled generally cylindrical liner that extends from a head end to an aft end. A venturi is formed on the combustor liner at a location between the head and aft ends. The venturi is formed by first and second straight portions o

A combustor liner for a combustor of a turbine engine includes a single-walled generally cylindrical liner that extends from a head end to an aft end. A venturi is formed on the combustor liner at a location between the head and aft ends. The venturi is formed by first and second straight portions of the combustor liner that angle inward to form a reduced diameter portion. The combustor liner may also include an air deflector to deflect air down onto the exterior of the reduced diameter portion of the single-walled combustor liner. The combustor liner may also include dilution holes, and turbulator rings.

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1. A combustor liner for a combustor of a turbine engine, comprising: a generally cylindrical liner that extends from a head end to an aft end;a venturi formed in an interior of the liner between the head end and the aft end, the venturi being formed by: a first inclined portion of the liner that re

1. A combustor liner for a combustor of a turbine engine, comprising: a generally cylindrical liner that extends from a head end to an aft end;a venturi formed in an interior of the liner between the head end and the aft end, the venturi being formed by: a first inclined portion of the liner that reduces in diameter while progressing in the aft direction; anda second inclined portion of the liner that increases in diameter while progressing in the aft direction, wherein an aft end of the first inclined portion is joined to a head end of the second inclined portion; andan air deflector that is mounted on an exterior of the liner such that it at least partially surrounds at least one of the first and second inclined portions and such that an annular space is formed between an inner side of the air deflector and an outer side of the liner, wherein the air deflector is configured to deflect a portion of a flow of air that is passing along the exterior of the liner from the aft end to the head end onto a circumferential depression formed on an exterior the of the liner by outer sides of the first and second inclined portions, and wherein air passing through the annular space continues to travel along the exterior of the liner toward the head end of the liner where it turns 180° and enters the interior of the combustor liner. 2. The combustor liner of claim 1, wherein the generally cylindrical liner includes an aft cylindrical portion that is joined to the aft end of the second inclined portion, and wherein a plurality of dilution holes are formed in the aft cylindrical portion. 3. The combustor liner of claim 2, wherein the plurality of dilution holes are arranged in a ring that extends around a circumference of the aft cylindrical portion, and wherein the ring of dilution holes are spaced away from the aft end of the second inclined portion in the aft direction. 4. The combustor liner of claim 1, wherein the generally cylindrical liner includes an aft cylindrical portion that is joined to the aft end of the second inclined portion, and wherein at least one turbulator ring is located on the aft cylindrical portion, each at least one turbulator ring projecting from the exterior of the aft cylindrical portion and extending around a circumference of the aft cylindrical portion. 5. The combustor liner of claim 4, wherein the at least one turbulator ring comprises a plurality of turbulator rings that are spaced from one another along the aft cylindrical portion. 6. The combustor liner of claim 1, wherein the air deflector comprises: a first inclined portion that reduces in diameter while progressing in the aft direction, wherein the first inclined portion of the air deflector is aligned with the first inclined portion of the liner; anda second inclined portion that increases in diameter while progressing in the aft direction, wherein an aft end of the first inclined portion of the air deflector is joined to a head end of the second inclined portion of air deflector, and wherein the second inclined portion of the air deflector is aligned with the second inclined portion of the liner. 7. The combustor liner of claim 6, wherein a head end of the first inclined portion of the air deflector extends in the head direction beyond a head end of the first inclined portion of the cylindrical liner. 8. The combustor liner of claim 7, wherein an aft end of the second inclined portion of the air deflector extends in the aft direction beyond an aft end of the second inclined portion of the cylindrical liner. 9. The combustor liner of claim 6, wherein an aft end of the second inclined portion of the air deflector extends in the aft direction beyond an aft end of the second inclined portion of the cylindrical liner. 10. The combustor liner of claim 1, wherein the air deflector comprises an inclined portion that increases in diameter while progressing in the aft direction, wherein the inclined portion of the air deflector is aligned with the second inclined portion of the cylindrical liner. 11. The combustor liner of claim 10, wherein the inclined portion of the air deflector is generally parallel with the second inclined portion of the cylindrical liner. 12. The combustor liner of claim 10, wherein an aft end of the inclined portion of the air deflector extends further aft than an aft end of the second inclined portion of the cylindrical liner. 13. The combustor liner of claim 10, wherein a head end of the inclined portion of the air deflector does not extend as far in the head end direction as the head end of the second inclined portion of the cylindrical liner. 14. The combustor liner of claim 1, wherein the generally cylindrical liner includes an aft cylindrical portion that is joined to the aft end of the second inclined portion, and wherein a plurality of dilution holes are formed in the aft cylindrical portion. 15. The combustor liner of claim 14, wherein the plurality of dilution holes are arranged in a ring that extends around a circumference of the aft cylindrical portion, and wherein the ring of dilution holes are spaced away from the aft end of the second inclined portion in the aft direction. 16. The combustor liner of claim 1, wherein the generally cylindrical liner includes an aft cylindrical portion that is joined to the aft end of the second inclined portion, and wherein at least one turbulator ring is located on the aft cylindrical portion, each at least one turbulator ring projecting from the exterior of the aft cylindrical portion and extending around a circumference of the aft cylindrical portion. 17. The combustor liner of claim 16, wherein the at least one turbulator ring comprises a plurality of turbulator rings that are spaced from one another along the aft cylindrical portion. 18. A combustor liner of claim 1, provided on a turbine engine. 19. A combustor liner for a combustor of a turbine engine, comprising: a liner that extends from a head end to an aft end, wherein a reduced diameter portion is formed in the liner between the head end and the aft end, the reduced diameter portion forming a venturi in the interior of the liner; andan air deflector mounted on an exterior of the liner such that it at least partially surrounds the reduced diameter portion of the liner and such that there is an annular space between an interior of the air deflector and an exterior of the liner, wherein the air deflector deflects a portion of a flow of air that is passing along the exterior of the liner from the aft end toward the head end onto an exterior of the reduced diameter portion of the liner, and wherein air passing through the annular space continues to travel along the exterior of the liner and toward the head end of the liner where it turns 180° and enters an interior of the liner.