System and method for fuel injection in turbine section of gas turbine engine
A system includes at least one component of a turbine section. The at least one component includes an inert gas port formed into a wall of the at least one component. The inert gas port is configured to inject an inert gas into a chamber of the turbine section in a downstream direction. The at least one component also includes a fuel port formed into the wall upstream of the inert gas part. The fuel port is configured to inject a fuel in the downstream direction toward the injected inert gas. The inert gas causes the injected fuel to be lifted away from the surface of the wall and propelled into the hot gas flow path, where the fuel can be ignited by the combustion gases to increase gas turbine engine efficiency and performance.
1 . A system, comprising:
at least one component of a turbine section comprising:
an inert gas port formed into a wall of the at least one component, wherein the inert gas port is configured to inject an inert gas into a chamber of the turbine section in a downstream direction;
a fuel port formed into the wall upstream of the inert gas port, wherein the fuel port is configured to inject a fuel in the downstream direction toward the injected inert gas; and
a hump protruding from a surface of the wall, wherein an opening of the inert gas port is disposed downstream of a crest of the hump, and an opening of the fuel port is disposed upstream of the crest.
2 . The system of claim 1 , wherein a first intersection of the inert gas port and the surface forms a first cross-section, a second intersection of the fuel port and the surface forms a second cross-section, and a distance spanning a first centroid of the first cross-section and a second centroid of the second cross-section is between two times a hydraulic diameter of the fuel port and one hundred times the hydraulic diameter.
3 . The system of claim 1 , wherein a first angle between a first central axis of the inert gas port and the surface is between 15 and 25 degrees, and a second angle between a second central axis of the fuel port and the surface is between 15 and 25 degrees.
4 . The system of claim 1 , wherein the wall is defined between successive circumferentially spaced airfoils of the turbine section.
5 . The system of claim 1 , wherein the opening of the fuel port is at least partially formed into an upstream portion of the hump.
6 . The system of claim 1 , wherein the opening of the inert gas port is at least partially formed into a downstream portion of the hump.
7 . The system of claim 1 , wherein the inert gas port comprises:
a vertical portion extending crosswise to the surface into an interior of the hump; and
a downstream portion fluidly coupled to the vertical portion and the opening of the inert gas port, wherein the downstream portion extends crosswise relative to the vertical portion in the downstream direction.
8 . The system of claim 1 , wherein the chamber is disposed between successive circumferentially spaced airfoils of the turbine section.
9 . The system of claim 8 , wherein the successive circumferentially spaced airfoils comprise blades, vanes, or a combination thereof.
10 . The system of claim 9 , wherein the wall of the at least one component comprises a blade wall of at least one of the blades, a vane wall of at least one of the vanes, an inner diameter wall of the turbine section, an outer diameter wall of the turbine section, or a combination thereof.
11 . The system of claim 1 , wherein a first pressure ratio of the fuel is between 1.5 and 1.7, and a second pressure ratio of the inert gas is between 1.0 and 1.2.
12 . The system of claim 1 , wherein the inert gas comprises carbon dioxide, nitrogen, argon, recirculated exhaust gas, or a combination thereof, and the fuel comprises methane, natural gas, syngas, hydrogen, ammonia, or a combination thereof.
13 . A system, comprising:
a turbine section including circumferentially spaced airfoils;
at least one component of the turbine section comprising:
an inert gas port formed into a wall of the at least one component, wherein the inert gas port is configured to direct an inert gas between successive circumferentially spaced airfoils of the turbine section in a downstream direction;
a fuel port formed into the wall upstream of the inert gas port, wherein the fuel port is configured to inject a fuel between the successive circumferentially spaced airfoils in the downstream direction toward the inert gas; and
a hump protruding from a surface of the wall, wherein an opening of the inert gas port is disposed downstream of a crest of the hump, and an opening of the fuel port is disposed upstream of the crest.
14 . The system of claim 13 , wherein the wall is defined between the successive circumferentially spaced airfoils of the turbine section.
15 . The system of claim 13 , wherein a first sign of a first curvature of lateral sides of the hump matches a second sign of a second curvature of lateral surfaces of the successive circumferentially spaced airfoils.
16 . The system of claim 13 , wherein a first intersection of the inert gas port and the surface forms a first cross-section, a second intersection of the fuel port and the surface forms a second cross-section, and a distance spanning a first centroid of the first cross-section and a second centroid of the second cross-section is between two times a hydraulic diameter of the fuel port and one hundred times the hydraulic diameter.
17 . The system of claim 13 , wherein a first angle between a first central axis of the inert gas port and the surface is between 15 and 25 degrees, and a second angle between a second central axis of the fuel port and the surface is between 15 and 25 degrees.
18 . A method, comprising:
injecting an inert gas from an inert gas port formed into a wall of at least one component of a turbine section;
injecting a fuel in a downstream direction toward the injected inert gas from a fuel port formed into the wall, wherein an opening of the inert gas port is disposed downstream of a crest of a hump protruding from a surface of the wall, and an opening of the fuel port is disposed upstream of the crest; and
causing the injected inert gas to occupy at least a portion of a region downstream of the fuel port and adjacent to the wall.
19 . The method of claim 18 , wherein a portion of the fuel port and a portion of the inert gas port are formed into the hump.
20 . The method of claim 18 , wherein the wall is defined between successive circumferentially spaced airfoils of the turbine section.