Combustor with fuel plenum with mixing passages having baffles

1. A combustor for a gas turbine engine comprising:

a liner surrounding a gaseous fuel and air mixing body;

a gaseous fuel supply passage for delivering fuel into the mixing body;

a wall of the mixing body having air openings to communicate air into mixing passages, at least one fuel opening in each of the mixing passages allows fuel to flow into the mixing passages and mix with the air, and passage sections downstream of a location of the fuel openings, such that said mixed air and fuel travel downstream of the location and into a combustion chamber;

the passage sections having baffles that create a tortuous path;

the fuel from the fuel supply passage passing into a fuel plenum, then into the mixing passages through the at least one fuel opening; and

each of the mixing passages have at least one of the baffles with the at least one fuel opening to communicate fuel from the fuel plenum into the mixing passages.

2. The combustor as set forth in claim 1 , wherein a source of gaseous fuel is connected to the gaseous fuel supply passage, and the source of fuel is hydrogen.

3. The combustor as set forth in claim 2 , wherein there are also solid ones of the baffles.

4. The combustor as set forth in claim 1 , wherein said fuel supply passage is at a generally central location in the fuel mixing body, with the fuel plenum extending both circumferentially and radially on both sides of an axis of the fuel supply passage.

5. The combustor as set forth in claim 4 , wherein an inner face of the mixing body at the combustion chamber is generally non-planar.

6. The combustor as set forth in claim 5 , wherein some of said passage sections which are closer to the axis of the fuel supply passage extend for a shorter axial length than others of said passage sections spaced further from said axis.

7. The combustor as set forth in claim 1 , wherein there are also solid ones of the baffles.

8. A gas turbine engine comprising:

a compressor section and a turbine section;

a combustor intermediate said compressor section and said turbine section;

a gaseous fuel supply for delivering gaseous fuel into a mixing body in the combustor;

a liner surrounding the mixing body;

a wall of the mixing body having air openings to communicate air into mixing passages, at least one fuel opening in each of the mixing passages allows fuel to flow into the mixing passages and mix with the air, and passage sections downstream of a location of the fuel openings, such that said mixed air and fuel travel downstream of the location and into a combustion chamber;

the passage sections having baffles that create a tortuous path;

the fuel from the fuel supply passage passing into a fuel plenum, then into mixing passages through the at least one fuel opening; and

each of the mixing passages have at least one of the baffles with the at least one fuel opening to communicate fuel from the fuel plenum into the mixing passages.

9. The gas turbine engine as set forth in claim 8 , wherein a source of gaseous fuel is connected to the gaseous fuel supply passage, and the source of fuel is hydrogen.

10. The gas turbine engine as set forth in claim 9 , wherein there are also solid ones of the baffles.

11. The gas turbine engine as set forth in claim 8 , wherein said fuel supply passage is at a generally central location in the fuel mixing body, with the fuel plenum extending both circumferentially and radially on both sides of an axis of the fuel supply passage.

12. The gas turbine engine as set forth in claim 11 , wherein an inner face of the mixing body at the combustion chamber is generally non-planar.

13. The gas turbine engine as set forth in claim 12 , wherein some of the passage sections which are closer to the axis of the fuel supply passage extend for a shorter axial length than others of said passage sections spaced further from said axis.

14. The gas turbine engine as set forth in claim 8 , wherein there are also solid ones of the baffles.