Fuel distribution within a gas turbine engine combustor
A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.
1. A fuel system for a gas turbine engine comprising:
a plurality of duplex nozzles, wherein the plurality of duplex nozzles are positioned circumferentially about an engine longitudinal axis and at least two of the plurality of duplex nozzles are positioned on either side of a top center position on a common side of the engine longitudinal axis;
a plurality of simplex nozzles, wherein the plurality of simplex nozzles includes at least two simplex nozzles arranged on either side of a bottom center position on a side of the engine longitudinal axis opposite the top center position and the at least two of the plurality of duplex nozzles positioned on either side of the top center position;
a primary manifold operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles;
a secondary manifold operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles; and
an equalizer valve in communication with the primary manifold and the secondary manifold, the equalizer valve movable between an open position and a closed position, the closed position is operable to permit a supply of fuel pressure to the primary manifold that is greater than fuel pressure to the secondary manifold, and the open position is operable to permit supply of fuel pressure to the primary manifold with essentially an equal fuel pressure as the secondary manifold.
2. The fuel system as recited in claim 1 , wherein the plurality of duplex nozzles are arranged with respect to a fuel igniter.
3. The fuel system as recited in claim 1 , wherein at least one of the plurality of duplex nozzles are arranged adjacent to a fuel igniter.
4. The fuel system as recited in claim 3 , wherein at least one of the plurality of duplex nozzles are arranged opposite the fuel igniter.
5. The fuel system as recited in claim 1 , wherein the primary flow jet in each of the plurality of duplex nozzles is surrounded by the secondary flow jet.
6. The fuel system as recited in claim 1 , wherein the plurality of duplex nozzles comprise ten (10) duplex nozzles and the plurality of simplex nozzles comprises six (6) simplex nozzles.
7. The fuel system as recited in claim 6 , wherein at least two simplex nozzles are arranged next to each other and between at least two of the duplex nozzles.
8. The fuel system as recited in claim 6 , wherein the plurality of duplex nozzles comprise a first group of six duplex nozzles and a second group of four simplex nozzles with at least one of the plurality of simplex nozzles disposed between the first group of six duplex nozzles and the second group of for simplex nozzles.
9. The fuel system as recited in claim 8 , wherein the plurality of simplex nozzles comprises a first group of two simplex nozzles and a second group of four simplex nozzles.
10. The fuel system as recited in claim 9 , wherein the second group of four simplex nozzles includes the at least two simplex nozzles arranged on either side of the bottom center position.
11. The fuel system as recited in claim 10 , wherein the first group of six duplex nozzles includes the at least two duplex nozzles disposed on either side of the top dead center position.
12. A fuel system for a gas turbine engine comprising:
a plurality of duplex nozzles;
a plurality of simplex nozzles, wherein the plurality of duplex nozzles comprise ten (10) duplex nozzles and the plurality of simplex nozzles comprises six (6) simplex nozzles;
a primary manifold operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles;
a secondary manifold operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles; and
an equalizer valve in communication with the primary manifold and the secondary manifold, the equalizer valve movable between an open position and a closed position, the closed position is operable to permit a supply of fuel pressure to the primary manifold that is greater than fuel pressure to the secondary manifold, and the open position is operable to permit supply of fuel pressure to the primary manifold with essentially an equal fuel pressure as the secondary manifold.
13. The fuel system as recited in claim 12 , wherein the plurality of simplex nozzles are arranged about a longitudinal axis of the engine and the plurality of simplex nozzles includes simplex nozzles arranged on either side of a bottom center position on an opposite side of the longitudinal axis of the engine from at least two of the plurality of duplex nozzles positioned on either side of a top center position.
14. The fuel system as recited in claim 13 , wherein at least two simplex nozzles are arranged next to each other and between at least two of the duplex nozzles.
15. The fuel system as recited in claim 13 , wherein the plurality of duplex nozzles comprise a first group of six duplex nozzles and a second group of four simplex nozzles with at least one of the plurality of simplex nozzles disposed between the first group of six duplex nozzles and the second group of for simplex nozzles.
16. The fuel system as recited in claim 15 , wherein the plurality of simplex nozzles comprises a first group of two simplex nozzles and a second group of four simplex nozzles.
17. The fuel system as recited in claim 16 , wherein the second group of four simplex nozzles includes the at least two simplex nozzles arranged on either side of the bottom center position.
18. The fuel system as recited in claim 17 , wherein the first group of six duplex nozzles includes the at least two duplex nozzles disposed on either side of the top dead center position.