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A combustor includes a first liner; and a second liner forming a combustion chamber with the first liner. The combustion chamber is configured to receive an air-fuel mixture for combustion therein, and the first liner is a first dual wall liner having a first hot wall facing the combustion chamber a

A combustor includes a first liner; and a second liner forming a combustion chamber with the first liner. The combustion chamber is configured to receive an air-fuel mixture for combustion therein, and the first liner is a first dual wall liner having a first hot wall facing the combustion chamber and a first cold wall. The first cold wall has a first cold wall orifice and the first hot wall has a first hot wall orifice. A first insert is mounted in the first hot wall orifice and is configured to receive a first air jet of pressured air from the first cold wall orifice, and guide the first jet through the first hot wall orifice and into the combustion chamber.

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1. A combustor for a turbine engine, comprising: a first liner;a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein,the first liner being a first dual wall liner comprising a first hot wall facing th

1. A combustor for a turbine engine, comprising: a first liner;a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein,the first liner being a first dual wall liner comprising a first hot wall facing the combustion chamber and a first cold wall, the first cold wall having a first cold wall orifice and the first hot wall having a first hot wall orifice; anda first insert has a divergent inlet portion between the first cold wall and the first hot wall, the insert mounted in the first hot wall orifice configured to receive a first air jet of pressured air from the first cold wall orifice, and guide the first jet through the first hot wall orifice and into the combustion chamber,wherein the first jet has a first flow rate through the first cold wall orifice and a second flow rate through the first insert, and wherein the first flow rate is approximately equal to the second flow rate or differs from the second flow rate by approximately +10%. 2. The combustor of claim 1, wherein the second liner is a second dual wall liner comprising a second hot wall facing the combustion chamber and a second cold wall, the second cold wall having a second cold wall orifice and the second hot wall having a second hot wall orifice, and wherein the combustor further comprises a second insert mounted in the second hot wall orifice for receiving a second air jet of pressured air from the second cold wall orifice, and guiding the second jet through the second hot wall orifice and into the combustion chamber. 3. The combustor of claim 1, wherein the first cold wall includes a plurality of impingement cooling holes and the first hot wall includes a plurality of effusion cooling holes. 4. The combustor of claim 3, wherein the plurality of impingement cooling holes includes impingement holes oriented about 90° relative the first cold wall, and the plurality of effusion cooling holes include effusion cooling holes oriented about 15° to 45° relative to the first hot wall. 5. The combustor of claim 1, wherein the combustion chamber defines a rich burn zone, a quench zone, and a lean burn zone, and the first jet introduces pressurized air into the quench zone. 6. The combustor of claim 1, wherein the first cold wall orifice has a first diameter and the insert has a second diameter, greater than the first diameter. 7. The combustor of claim 1, wherein the insert is spaced apart from the first cold wall at a first distance. 8. The combustor of claim 7, wherein the first distance is less than approximately 0.1 inches. 9. The combustor of claim 1, wherein the insert has a cylindrical configuration. 10. The combustor of claim 1, wherein the insert has a body portion coupled to the first hot wall orifice, and the divergent inlet portion extending from the body portion. 11. The combustor of claim 1, wherein at least a portion of the insert projects into the combustion chamber. 12. The combustor of claim 10, wherein the portion of the insert projecting into the combustion chamber includes a thermal barrier coating (TBC). 13. The combustor of claim 1, wherein at least a portion of the insert is flush with the first hot wall. 14. The combustor of claim 1, wherein the first cold wall is strain isolated with respect to the first hot wall. 15. The combustor of claim 1, wherein the first insert is metallic. 16. A combustor liner, comprising: a first wall including a plurality of impingement cooling holes and a first primary orifice;a second wall proximate to the first wall to form a dual wall structure with the first wall, the second wall including a plurality of effusion cooling holes and a second primary orifice generally aligned with the first primary orifice; andan insert has a divergent inlet portion between the first wall and the second wall, the insert mounted in the second primary orifice configured to receive an air jet from the first primary orifice and to guide the air jet through the second wall, wherein the first wall is strain isolated with respect to the second wall. 17. A combustor for a turbine engine, comprising: a first liner;a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein,the first liner being a first dual wall liner comprising a first hot wall facing the combustion chamber and a first cold wall, the first cold wall having a first cold wall orifice and the first hot wall having a first hot wall orifice; anda first insert mounted in the first hot wall orifice configured to receive a first air jet of pressured air from the first cold wall orifice, and guide the first jet through the first hot wall orifice and into the combustion chamber,wherein the first cold wall includes a plurality of impingement cooling holes and the first hot wall includes a plurality of effusion cooling holes, and wherein the plurality of impingement cooling holes includes impingement holes oriented about 90° relative the first cold wall, and the plurality of effusion cooling holes include effusion cooling holes oriented about 15° to 45° relative to the first hot wall,wherein the combustion chamber defines a rich burn zone, a quench zone, and a lean burn zone, and the first jet introduces pressurized air into the quench zone,wherein the first insert is spaced apart from the first cold wall at a first distance,wherein the first insert has a body portion coupled to the first hot wall orifice, and a mouth portion extending from and angled relative to body, the mount portion disposed between the first hot wall and the first cold wall,wherein at least a portion of the insert projects into the combustion chamber, andwherein the first cold wall is strain isolated with respect to the first hot wall.