Combustors with quench inserts

1. A combustor for a turbine engine, comprising:

a first liner having a first hot side and a first cold side;

a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween, the combustion chamber configured to receive an air-fuel mixture for combustion therein; and

an insert comprising a body portion extending through the first liner, a shoulder circumscribing the body portion and abutting the first hot side, and an inlet portion coupled to the body portion and abutting the first cold side such that the inlet portion and the shoulder capture the first liner therebetween to retain the insert, wherein the body portion, the shoulder, and the inlet portion are integral with one another,

wherein the body portion projects into the combustion chamber,

wherein the inlet portion is flared,

wherein the body portion is generally tubular and extends beyond the shoulder into the combustion chamber,

wherein the first liner is a single-walled liner, and

wherein the insert is retained within the first liner in a first radial direction solely by the inlet portion abutting the first cold side and in a second radial direction solely by the shoulder abutting the first hot side.

2. The combustor of claim 1 , wherein the combustion chamber defines a rich burn zone, a quench zone, and a lean burn zone, and the insert is configured to introduce air into the quench zone.

3. The combustor of claim 1 , wherein the inlet portion is configured to guide air into the insert.

4. The combustor of claim 1 , wherein the inlet portion has an elliptical curvature.

5. The combustor of claim 1 , wherein the insert has a cylindrical configuration.

6. The combustor of claim 1 , wherein the insert is retained in a first radial direction relative to the first liner by the inlet portion contacting the first cold side of the first liner.