Premixer for gas turbine combustor
A gas turbine engine includes a combustor and a turbine. The combustor includes a pre-mixer having a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein the pre-mixer is configured to receive fuel from a fuel supply, receive air from an air supply, mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air, and supply the air-fuel mixture to a combustion zone. The combustor is configured to combust the air-fuel mixture, generating combustion fluids. The turbine is configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.
1. A gas turbine engine, comprising:
a combustor, comprising:
a pre-mixer comprising a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein a cross sectional area of each fluid passage of the plurality of fluid passages decreases from a first end of the pre-mixer to a second end of the pre-mixer, downstream from the first end, wherein the pre-mixer is configured to:
receive fuel from a fuel supply;
receive air from an air supply;
mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air; and
supply the air-fuel mixture to a combustion zone;
wherein the combustor is configured to combust the air-fuel mixture, generating combustion fluids; and
a turbine configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.
2. The gas turbine engine of claim 1 , wherein the one or more features comprise semi-circular lobes disposed about the fluid passages and extending radially outward into the body.
3. The gas turbine engine of claim 1 , wherein the body of the pre-mixer is tapered from the first end of the pre-mixer to the second end of the pre-mixer, downstream from the first end.
4. The gas turbine engine of claim 1 , wherein the pre-mixer is configured to mix a liquid fuel with the air.
5. The gas turbine engine of claim 1 , wherein the pre-mixer comprises a fuel inlet configured to supply fuel to a fluid passage of the plurality of fluid passages.
6. The gas turbine engine of claim 5 , wherein the fuel inlet is configured to supply fuel at an angle perpendicular to or oblique to the axis of the fluid passage.
7. A pre-mixer for a gas turbine combustor, comprising:
a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein a cross sectional area of each fluid passage of the plurality of fluid passages decreases from a first end of the pre-mixer to a second end of the pre-mixer, downstream from the first end, wherein the pre-mixer is configured to:
receive fuel from a fuel supply;
receive air from an air supply; and
mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air.
8. The pre-mixer of claim 7 , wherein the one or more features comprise semi-circular lobes disposed about the fluid passages and extending radially outward into the body.
9. The pre-mixer of claim 7 , wherein the one or more features comprise protrusions about the fluid passages and extending radially into each of the plurality of fluid passages.
10. The pre-mixer of claim 7 , wherein the body of the pre-mixer is tapered from the first end of the pre-mixer to the second end of the pre-mixer, downstream from the first end.
11. The pre-mixer of claim 7 , wherein fuel and air enter each fluid passage of the plurality of fluid passages at an inlet disposed at a first end of the fluid passage.
12. The pre-mixer of claim 7 , comprising a fuel inlet configured to supply fuel to a fluid passage of the plurality of fluid passages.
13. The pre-mixer of claim 12 , wherein the fuel inlet is configured to supply fuel at an angle perpendicular to or oblique to the axis of the fluid passage.
14. A method of mixing fuel and air in a pre-mixer of a gas turbine engine combustor, comprising:
receiving fuel from a fuel supply;
receiving air from an air supply;
directing the air and fuel through a plurality of fluid passages of a pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein a cross sectional area of each fluid passage of the plurality of fluid passages decreases from a first end of the pre-mixer to a second end of the pre-mixer, downstream from the first end; and
directing the fuel and air to a combustion zone of a combustor.
15. The method of claim 14 , wherein the fuel is a liquid fuel.
16. The method of claim 14 , wherein the one or more features comprise semi-circular lobes disposed about the fluid passages and extending radially outward into a body of the pre-mixer.
17. The method of claim 14 , wherein fuel is received via a fuel inlet configured to supply fuel at an angle perpendicular to or oblique to the axis of the fluid passage.