Abstract: A liner for a combustor includes a first wall and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall. The first wall defines a first wall orifice and the second wall defines a second wall orifice. The liner further includes a first insert mounted on the second wall within the second wall orifice and extending through the first wall orifice. The first insert is configured to direct a first air jet through the second wall and the first wall. The first insert is formed by a tubular body portion extending through the first wall orifice and the second wall orifice, and a shoulder extending around the body portion that abuts the first side of the second wall. The shoulder has a first diameter and the first wall orifice has a second diameter, greater than the first diameter.

Abstract: A combustor for a turbine engine 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. The first liner is a first double wall liner with a first wall forming a portion of the combustion chamber and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall. The first wall defines a first wall orifice and the second wall defines a second wall orifice. The combustor further includes a first insert mounted on the second wall within the second wall orifice and extending through the first wall orifice. The first insert is configured to direct a first air jet through the second wall, through the first wall, and into the combustion chamber.

Abstract: A liner for a combustor includes a first wall and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall. The first wall defines a first wall orifice and the second wall defines a second wall orifice. The liner further includes a first insert mounted on the second wall within the second wall orifice and extending through the first wall orifice. The first insert is configured to direct a first air jet through the second wall and the first wall. The first insert is formed by a tubular body portion extending through the first wall orifice and the second wall orifice, and a shoulder extending around the body portion that abuts the first side of the second wall. The shoulder has a first diameter and the first wall orifice has a second diameter, greater than the first diameter.

Abstract: A combustor for a turbine engine 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. The first liner is a first double wall liner with a first wall forming a portion of the combustion chamber and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall. The first wall defines a first wall orifice and the second wall defines a second wall orifice. The combustor further includes a first insert mounted on the second wall within the second wall orifice and extending through the first wall orifice. The first insert is configured to direct a first air jet through the second wall, through the first wall, and into the combustion chamber.

Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner and 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 defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, and the air admission hole may have a non-circular shape. The combustor further includes an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber.

Abstract: A combustor for a turbine engine is provided. The combustor includes 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 including 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 second liner therebetween to retain the insert.

Abstract: A combustor for a turbine engine is provided. The combustor includes a first liner and 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 defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, and the air admission hole may have a non-circular shape. The combustor further includes an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber.

Abstract: A combustor for a turbine engine is provided. The combustor includes 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 including 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 second liner therebetween to retain the insert.