Combustor liner
AssigneeUnited Technologies Corporation
InventorHoyt Y. Chang
Life of this patent
Estimating the term…
Abstract
A combustor includes a liner and a support. The liner includes first and second spaced apart liner walls defining a combustion chamber therebetween, and an end wall joining the first and second liner walls at a forward end. The support is configured to resiliently support the liner and includes first and second spaced apart support walls having first and second retainers configured to capture aft ends of the first and second liner walls. A gas turbine engine and a method of assembling a combustor are also disclosed.
Claims20
A combustor, comprising:
- a liner including a first liner wall and a second liner wall spaced apart from the first liner wall, the first and second liner walls defining a combustion chamber therebetween, an end wall joining the first and second liner walls at a forward end;
- and
- support configured to resiliently support the liner, the support including a first support wall and a second support wall spaced apart from the first support wall, the first and second support walls having a first retainer and a second retainer, respectively, the first retainer configured to capture an aft end of the first liner wall and the second retainer configured to capture an aft end of the second liner wall.
A gas turbine engine, comprising:
- a fuel nozzle;
- a combustion chamber in fluid communication with the fuel nozzle, the combustion chamber defined by a liner, the liner including a first liner wall and a second liner wall spaced apart from the first liner wall, and an end wall joining the first and second liner walls at a forward end;
- and
- a support configured to resiliently support the liner, the support including a first support wall and a second support wall spaced apart from the first support wall, the first and second support walls having a first retainer and a second retainer, respectively, the first retainer configured to capture an aft end of the first liner wall and the second retainer configured to capture an aft end of the second liner wall.
A method of assembling a combustor for a gas turbine engine, comprising:
- providing a support, the support including a first support wall and a second support wall spaced apart from the first support wall, the first and second support walls having a first retainer and a second retainer, respectively;
- resiliently mounting a liner to the support, the liner including a first liner wall and a second liner wall spaced apart from the first liner wall, the first and second liner walls defining a combustion chamber therebetween, an end wall joining the first and second liner walls at a forward end;
- and
- capturing an aft end of the first liner wall and an aft end of the second liner wall in the first and second retainers, respectively.
Dependencies are inferred from the claim text.