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A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions. The

A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions. The first liner is a first dual walled liner having a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends. A first liner seal is configured to seal the second end of the first liner cavity and to accommodate relative movement of the first hot wall and first cold wall generally in the axial and radial directions.

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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 and having a longitudinal axis that defines axial and radial directions,the first l

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 and having a longitudinal axis that defines axial and radial directions,the first liner being a first dual walled liner comprising a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends; anda first liner seal configured to seal the second end of the first liner cavity and to accommodate relative movement of the first hot wall and first cold wall generally in the axial and radial directions,the second liner being a second dual walled liner comprising a second hot wall facing the combustion chamber and a second cold wall that forms a second liner cavity with the second hot wall, the second liner cavity having first and second ends; anda second liner seal configured to seal the second end of the second liner cavity and to accommodate relative movement of the second hot wall and second cold wall generally in the axial and radial directions,wherein the second hot wall includes radially extending second hot wall flange, and wherein the second liner seal comprises first and second portions, the first portion of the second liner seal having a first inner flange and a second inner flange that define an inner groove, the second hot wall flange being positioned within the inner groove of the second liner seal,wherein the first portion of the second liner seal further includes a first outer flange and a second outer flange that define an outer groove, wherein the second liner seal further includes a second portion with a first leg and a second leg extending perpendicularly to the first leg, and wherein the first leg of the second portion is positioned within the outer groove of the second liner seal such that the second portion is movable within the outer groove of the second liner seal generally in the radial direction and is generally retained by the first and second outer flanges of the second liner seal in the axial direction. 2. The combustor of claim 1, wherein the first hot wall includes radially extending first and second hot wall flanges that define a first hot wall groove, and wherein the first liner seal includes a radially extending liner seal flange positioned within the first hot wall groove. 3. The combustor of claim 2, wherein the liner seal flange is movable within the first hot wall groove relative to the first and second hot wall flanges generally in the radial direction and is generally retained by the first and second hot wall flanges in the axial direction. 4. The combustor of claim 3, wherein the first liner seal and the first hot wall define a first axial cavity, and wherein one end of the first cold wall is positioned within the first axial cavity. 5. The combustor of claim 4, wherein the first cold wall is movable within the first axial cavity relative to the first hot wall and first liner seal generally in the axial direction and is generally retained by the first hot wall and first liner seal in the radial direction. 6. The combustor of claim 2, wherein the first liner seal and the first hot wall define a first axial cavity, one end of the first cold wall being positioned within the first axial cavity, and wherein the first cold wall is movable within the first axial cavity relative to the first hot wall and first liner seal generally in the axial direction and is generally retained by the first hot wall and first liner seal in the radial direction. 7. The combustor of claim 1, wherein the first liner is an inner liner and the first liner seal is an inner liner seal. 8. The combustor of claim 1, wherein the first end of the first liner is a forward end and the second end of the first liner is an aft end, and wherein the first end of the first liner has a fixed seal. 9. The combustor of claim 1, wherein the first liner seal is a split ring, single piece liner seal. 10. The combustor of claim 1, wherein first portion further includes an axial flange extending from the first outer flange, the second leg of the second portion and the axial flange of the first portion defining an axial cavity for receiving one end of the second cold wall, and wherein the second cold wall is movable within the axial cavity relative to the axial flange of the first portion and the second leg of the second portion generally in the axial direction and is generally retained by the axial flange of the first portion and the second leg of the second portion in the radial direction. 11. The combustor of claim 1, wherein the second liner is an outer liner and the second liner seal is an outer liner seal. 12. A combustor for a turbine engine, comprising: an inner liner;an outer liner forming a combustion chamber with the inner liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions,the inner liner being a dual walled liner comprising a first hot wall facing the combustion chamber and a first cold wall that forms an inner liner cavity with the first hot wall,the outer liner being a dual walled liner comprising a second hot wall facing the combustion chamber and a second cold wall that forms an outer liner cavity with the second hot wall, each of the outer and inner liner cavities having first and second ends;an inner liner seal configured to seal the second end of the inner liner cavity and to accommodate relative movement of the first hot wall and first cold wall generally in the axial and radial directions; andan outer liner seal configured to seal the second end of the outer liner cavity and to accommodate relative movement of the second hot wall and second cold wall generally in the axial and radial directions,wherein the second hot wall includes radially extending second hot wall flange, and wherein the first liner seal comprises first and second portions, the first portion being H-shaped in cross section and defining inner and outer radial grooves, the second portion having a radial leg and an axial leg,wherein the radial leg of the second portion is positioned within the outer radial groove such that the second portion is movable within the outer radial groove generally in the radial direction and is generally retained by the first portion in the axial direction, andwherein second hot wall flange is positioned within the inner radial groove such that second hot wall flange is movable within the inner radial groove generally in the radial direction and is generally retained by the first portion in the axial direction. 13. The combustor of claim 12, wherein the first hot wall includes radially extending first and second hot wall flanges that define a first hot wall groove, and wherein the inner liner seal includes a radially extending liner seal flange positioned within the first hot wall groove such that the liner seal flange is movable within the first hot wall groove relative to the first and second hot wall flanges generally in the radial direction and is generally retained by the first and second hot wall flanges in the axial direction. 14. The combustor of claim 13, wherein the first liner seal and the first hot wall define a first axial cavity, and wherein one end of the first cold wall is positioned within the first axial cavity such that the first cold wall is movable within the first axial cavity relative to the first hot wall and inner liner seal generally in the axial direction and is generally retained by the first hot wall and inner liner seal in the radial direction. 15. The combustor of claim 12, wherein first portion further includes an axial flange, the axial leg of the second portion and the axial flange of the first portion defining an axial cavity for receiving one end of the second cold wall, and wherein the second cold wall is movable within the axial cavity relative to the axial flange of the first portion and the axial leg of the second portion generally in the axial direction and is generally retained by the axial flange of the first portion and the axial leg of the second portion in the radial direction. 16. A combustor for a turbine engine, comprising: an inner liner;an outer liner forming a combustion chamber with the inner liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions,the inner liner being a dual walled liner comprising a first hot wall facing the combustion chamber and a first cold wall that forms an inner liner cavity with the first hot wall,the outer liner being a dual walled liner comprising a second hot wall facing the combustion chamber and a second cold wall that forms an outer liner cavity with the second hot wall, each of the outer and inner liner cavities having first and second ends;an inner liner seal configured to seal the second end of the inner liner cavity and to accommodate relative movement of the first hot wall and first cold wall in the axial and radial directions; andan outer liner seal configured to seal the second end of the outer liner cavity and to accommodate relative movement of the second hot wall and second cold wall in the axial and radial directions,wherein the first hot wall includes radially extending first and second hot wall flanges that define a first hot wall groove, and wherein the inner liner seal includes a radially extending liner seal flange positioned within the first hot wall groove such that the liner seal flange is movable within the first hot wall groove relative to the first and second hot wall flanges in the radial direction and is generally retained by the first and second hot wall flanges in the axial direction, and wherein the first liner seal and the first hot wall define a first axial cavity, and wherein one end of the first cold wall is positioned within the first axial cavity such that the first cold wall is movable within the first axial cavity relative to the first hot wall and inner liner seal in the axial direction and is generally retained by the first hot wall and inner liner seal in the radial direction, andwherein the second hot wall includes radially extending second hot wall flange, and wherein the outer liner seal comprises first and second portions, the first portion being H-shaped in cross section and defining inner and outer radial grooves, the second portion having a radial leg and an axial leg, wherein the radial leg of the second portion is positioned within the outer radial groove such that the second portion is movable within the outer radial groove generally in the radial direction and is generally retained by the first portion in the axial direction, and wherein second hot wall flange is positioned within the inner radial groove such that second hot wall flange is movable within the inner radial groove generally in the radial direction and is generally retained by the first portion in the axial direction, andwherein first portion further includes an axial flange, the axial leg of the second portion and the axial flange of the first portion defining a second axial cavity for receiving one end of the second cold wall, and wherein the second cold wall is movable within the second axial cavity relative to the axial flange of the first portion and the axial leg of the second portion generally in the axial direction and is generally retained by the axial flange of the first portion and the axial leg of the second portion in the radial direction.