Fuel injector manifold having a variable fuel flow system for a turbine engine
A fuel injector manifold for a turbine engine includes a fuel manifold ring, a plurality of fuel injectors, and a variable fuel flow system. The fuel manifold flowpath within the fuel manifold ring, the fuel manifold flowpath receiving fuel therein. The plurality of fuel injectors in fluid communication with the fuel manifold flowpath, each of the plurality of fuel injectors having one or more fuel injector flowpaths. The variable fuel flow system disposed within the fuel manifold flowpath, the variable fuel flow system including a closed state, a partially opened state, and a fully opened state to vary a flow of the fuel from the fuel manifold flowpath to the one or more fuel injector flowpaths of each of the plurality of fuel injectors.
1. A fuel injector manifold for a turbine engine, the fuel injector manifold comprising:
a fuel manifold ring that defines a fuel manifold flowpath within the fuel manifold ring, the fuel manifold flowpath being annular about the fuel manifold ring and receiving fuel therein;
a plurality of fuel injectors in fluid communication with the fuel manifold flowpath, each of the plurality of fuel injectors having one or more fuel injector flowpaths; and
a variable fuel flow system disposed within the fuel manifold flowpath, the variable fuel flow system including one or more pistons disposed within the fuel manifold flowpath and moving substantially perpendicularly to the fuel manifold flowpath between a closed state, a partially opened state, and a fully opened state to vary a flow of the fuel from the fuel manifold flowpath to the one or more fuel injector flowpaths of each of the plurality of fuel injectors.
2. The fuel injector manifold of claim 1 , wherein the one or more fuel injector flowpaths are disposed at a circumferential fuel injector flowpath angle with respect to a lateral centerline axis of the fuel injector manifold, the circumferential fuel injector flowpath angle being non-zero.
3. The fuel injector manifold of claim 1 , wherein the one or more fuel injector flowpaths are disposed at an axial fuel injector flowpath angle with respect to a lateral centerline axis of the fuel injector manifold, the axial fuel injector flowpath angle being non-zero.
4. The fuel injector manifold of claim 1 , wherein the plurality of fuel injectors is oriented to inject the fuel substantially radially from the one or more fuel injector flowpaths of each of the plurality of fuel injectors.
5. The fuel injector manifold of claim 1 , wherein each of the one or more pistons includes one or more piston flowpaths in fluid communication with the fuel manifold flowpath and the one or more fuel injector flowpaths of each of the plurality of fuel injectors, the one or more piston flowpaths directing the fuel from the fuel manifold flowpath to the one or more fuel injector flowpaths of each of the plurality of fuel injectors.
6. The fuel injector manifold of claim 5 , wherein the one or more pistons split the fuel manifold flowpath into an upstream fuel manifold flowpath and a downstream fuel manifold flowpath, and the fuel flows from the upstream fuel manifold flowpath into the downstream fuel manifold flowpath, and through the one or more piston flowpaths into the one or more fuel injector flowpaths of each of the plurality of fuel injectors.
7. The fuel injector manifold of claim 1 , wherein the variable fuel flow system includes one or more actuation mechanisms coupled to the one or more pistons, the one or more actuation mechanisms moving the one or more pistons.
8. The fuel injector manifold of claim 7 , wherein the one or more actuation mechanisms are passive actuation mechanisms.
9. The fuel injector manifold of claim 7 , wherein the one or more actuation mechanisms are active actuation mechanisms.
10. A turbine engine comprising:
a combustor; and
a fuel injector manifold comprising:
a fuel manifold ring disposed about the combustor, the fuel manifold ring defining a fuel manifold flowpath within the fuel manifold ring, and the fuel manifold flowpath being annular about the fuel manifold ring and receiving fuel therein;
a plurality of fuel injectors in fluid communication with the fuel manifold flowpath and the combustor, each of the plurality of fuel injectors having one or more fuel injector flowpaths; and
a variable fuel flow system disposed within the fuel manifold flowpath, the variable fuel flow system including one or more pistons disposed within the fuel manifold flowpath and moving substantially perpendicularly to the fuel manifold flowpath between a closed state, a partially opened state, and a fully opened state to vary a flow of the fuel from the fuel manifold flowpath to the one or more fuel injector flowpaths of each of the plurality of fuel injectors for injecting the fuel into the combustor.
11. The turbine engine of claim 10 , wherein the one or more fuel injector flowpaths are disposed at a circumferential fuel injector flowpath angle with respect to a lateral centerline axis of the fuel injector manifold, the circumferential fuel injector flowpath angle being non-zero.
12. The turbine engine of claim 10 , wherein the one or more fuel injector flowpaths are disposed at an axial fuel injector flowpath angle with respect to a lateral centerline axis of the fuel injector manifold, the axial fuel injector flowpath angle being non-zero.
13. The turbine engine of claim 10 , wherein the plurality of fuel injectors is oriented to inject the fuel substantially radially from the one or more fuel injector flowpaths of each of the plurality of fuel injectors.
14. The turbine engine of claim 10 , wherein each of the one or more pistons includes one or more piston flowpaths in fluid communication with the fuel manifold flowpath and the one or more fuel injector flowpaths of each of the plurality of fuel injectors, the one or more piston flowpaths directing the fuel from the fuel manifold flowpath to the one or more fuel injector flowpaths of each of the plurality of fuel injectors.
15. The turbine engine of claim 14 , wherein the one or more pistons split the fuel manifold flowpath into an upstream fuel manifold flowpath and a downstream fuel manifold flowpath, and the fuel flows from the upstream fuel manifold flowpath into the downstream fuel manifold flowpath, and through the one or more piston flowpaths into the one or more fuel injector flowpaths of each of the plurality of fuel injectors.
16. The turbine engine of claim 10 , wherein the variable fuel flow system includes one or more actuation mechanisms coupled to the one or more pistons, the one or more actuation mechanisms moving the one or more pistons.
17. The turbine engine of claim 16 , wherein the one or more actuation mechanisms are passive actuation mechanisms.
18. The turbine engine of claim 16 , wherein the one or more actuation mechanisms are active actuation mechanisms.
19. The turbine engine of claim 10 , wherein the fuel manifold flowpath extends circumferentially about the fuel manifold ring, and the one or more pistons move generally axially within the fuel manifold flowpath.
20. The fuel injector manifold of claim 10 , wherein the fuel manifold flowpath extends circumferentially about the fuel manifold ring, and the one or more pistons move generally axially within the fuel manifold flowpath.