Combustion section for a turbine engine
A combustion section for a turbine engine. The combustion section has a circumferential casing, a combustor, multiple fuel nozzles and a fuel supply system. The circumferential casing defines an interior. The combustion has an annular liner located within the interior. The fuel supply system has a fuel manifold and multiple fuel line branches.
1 . A combustion section for a turbine engine, the combustion section having a centerline and comprising:
a circumferential casing defining an interior;
a combustor having an annular liner located within the interior, the combustor having a combustion chamber;
multiple fuel nozzles opening to the combustion chamber; and
a fuel supply system comprising:
a fuel manifold located within the interior radially inward of the combustion chamber, the fuel manifold defining a fuel path configured to guide fuel in a circumferential direction about the centerline; and
multiple fuel line branches, with each fuel line branch of the multiple fuel line branches extending between a respective portion of the fuel manifold and a respective portion of the combustor or a corresponding one of the multiple fuel nozzles.
2 . The combustion section of claim 1 , wherein the fuel supply system includes a fuel supply located within the interior and fluidly coupling the fuel manifold to a portion of the fuel supply system exterior the combustion section.
3 . The combustion section of claim 2 , wherein the fuel supply is coupled to the circumferential casing at a first joint.
4 . The combustion section of claim 3 , wherein the multiple fuel line branches are coupled to the multiple fuel nozzles at a set of second joints.
5 . The combustion section of claim 4 , wherein the fuel supply and the fuel manifold are integrally formed.
6 . The combustion section of claim 5 , wherein the fuel supply and the fuel manifold are 3D printed.
7 . The combustion section of claim 1 , further comprising a bracket extending between the fuel manifold and a respective portion of the circumferential casing, the bracket coupling the fuel manifold to the circumferential casing.
8 . The combustion section of claim 1 , wherein each fuel line branch of the multiple fuel line branches includes:
a bend;
a first leg extending from a respective portion of the fuel manifold and to the bend; and
a second leg extending from the bend and to the corresponding one of the multiple fuel nozzles.
9 . The combustion section of claim 1 , wherein each fuel line branch of the multiple fuel line branches has a branch centerline, with each fuel line branch extending a total axial length along the branch centerline to define an attenuation distance.
10 . The combustion section of claim 1 , wherein the fuel manifold forms a continuous annulus about the centerline.
11 . The combustion section of claim 1 , wherein the fuel manifold includes multiple discrete segments circumferentially spaced about the centerline.
12 . The combustion section of claim 1 , wherein the fuel manifold extends less than 360 degrees about the centerline.
13 . The combustion section of claim 1 , wherein the fuel manifold is included in multiple fuel manifolds, and the fuel supply system comprises two or more discrete bodies within the combustion section, with each body of the two or more discrete bodies including a respective fuel manifold of the multiple fuel manifolds and a respective portion of the multiple fuel line branches.
14 . The combustion section of claim 1 , wherein:
each fuel line branch of the multiple fuel line branches includes a branch centerline;
a circumferential distance is defined by an arcuate distance between the branch centerline of a first fuel line branch of the multiple fuel line branches where the fuel line branch opens to the combustion chamber and the branch centerline of a second fuel line branch, circumferentially adjacent the first fuel line branch, of the multiple fuel line branches where the second fuel line branch opens to the combustion chamber; and
the circumferential distance is greater than or equal to 1 inch and less than or equal to 3 inches.
15 . The combustion section of claim 1 , wherein:
the circumferential casing comprises an inner casing and an outer casing, and the annular liner comprises an inner liner and an outer liner; and
the fuel manifold is located radially between the inner casing and the inner liner.
16 . The combustion section of claim 1 , wherein at least one fuel nozzle of the multiple fuel nozzles extends through a respective portion of the annular liner.
17 . The combustion section of claim 1 , wherein a compressed air passage is formed between the circumferential casing and the combustion section.
18 . The combustion section of claim 17 , wherein the circumferential casing comprises a first body and a second body removably coupled to the first body, and further including a deswirler assembly at least partially defined by the first body.
19 . The combustion section of claim 18 , wherein the deswirler assembly comprises a diffuser and a deswirler.
20 . The combustion section of claim 1 , wherein the fuel manifold is configured to supply a flow of gaseous hydrogen-containing fuel to the combustion chamber.