Reducing noise from a combustor of a gas turbine engine
A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.
1. A combustor comprising a plurality of swirlers that are circumferentially spaced from one another and a corresponding plurality of fuel nozzles such that each swirler of the plurality of swirlers is axially aligned with a different fuel nozzle of the plurality of fuel nozzles, the plurality of fuel nozzles comprising a plurality of duplex fuel nozzles and a plurality of simplex fuel nozzles, the duplex fuel nozzles being structurally different from the simplex fuel nozzles, each fuel nozzle of the plurality of fuel nozzles comprising:
a distal tip,
wherein the distal tip comprises:
a tubular portion;
a distal portion; and
a conical portion concentrically orientated and axially disposed between the tubular portion and the distal portion;
a plurality of fuel spray apertures circumferentially spaced from one another and communicating through the conical portion and configured to produce a fuel spray into a combustion chamber,
the distal portion projecting in a direction of and being recessed from a downstream rim of the plurality of swirlers corresponding with the plurality of fuel nozzles,
an immersion depth measured between the distal portion of the distal tip and the downstream rim,
wherein the immersion depth comprises less than 0.500 inches, wherein the combustor comprises four nozzle groupings that are circumferentially disposed relative to an axis of the combustor, wherein a first nozzle grouping of the nozzle groupings and a third nozzle grouping of the nozzle groupings each comprise six of the plurality of duplex fuel nozzles, wherein a second nozzle grouping of the nozzle groupings and a fourth nozzle grouping of the nozzle groupings each comprise three of the plurality of simplex fuel nozzles, and that are circumferentially located between the first nozzle grouping and the third nozzle grouping.
2. The combustor of claim 1 , wherein the fuel spray apertures are angled at least partially radially outward and at least partially axially along a centerline of the plurality of fuel nozzles.
3. The combustor of claim 1 , wherein each of the plurality of fuel nozzles comprises a distal aperture communicating through a planar portion of the distal tip and configured to produce a fuel spray along a centerline of the plurality of fuel nozzles.
4. The combustor of claim 1 , wherein the first nozzle grouping is diametrically opposed to the third nozzle grouping, and wherein the second nozzle grouping is diametrically opposed to the fourth nozzle grouping.
5. The combustor of claim 1 , wherein the second nozzle grouping is adjacent to each of the first nozzle grouping and the third nozzle grouping on one side of the combustor, and wherein the fourth nozzle grouping is adjacent to each of the first nozzle grouping and the third nozzle grouping on an opposite side of the combustor.
6. The combustor of claim 1 , wherein each swirler of the plurality of swirlers converges relative to a centerline of the corresponding fuel nozzle of the plurality of fuel nozzles proceeding to the downstream rim, and wherein the downstream rim of each swirler of the plurality of swirlers defines an open discharge end.
7. A combustor comprising a plurality of fuel nozzles comprising a distal tip,
wherein the distal tip comprises:
a tubular portion;
a distal portion; and
a conical portion concentrically orientated and axially disposed between the tubular portion and the distal portion;
a plurality of fuel spray apertures spaced from one another and communicating through the conical portion and configured to produce a fuel spray into a combustion chamber of the combustor,
an immersion depth measured between the distal portion of the distal tip and a downstream rim of a corresponding swirler of the combustor, the distal portion projecting in a direction of and being recessed from a downstream rim of the corresponding swirler,
wherein the immersion depth is no more than about 0.500 inches,
wherein the combustor comprises a first nozzle grouping, a second nozzle grouping, a third nozzle grouping, and a fourth nozzle grouping, wherein the first nozzle grouping and the third nozzle grouping each include a common first number of a plurality of duplex nozzles of the plurality of plurality of fuel nozzles, wherein the second nozzle grouping and the fourth nozzle grouping each include a common second number of a plurality of simplex nozzles of the plurality of fuel nozzles, wherein the plurality of simplex nozzles are structurally different from the plurality of duplex nozzles, and wherein the first number is of a different magnitude than the second number.
8. The combustor of claim 7 , wherein the immersion depth is from between about 0.250 inches to about 0.500 inches.
9. The combustor of claim 7 , wherein the first nozzle grouping, the second nozzle grouping, the third nozzle grouping, and the fourth nozzle grouping are collectively disposed in a circumferential arrangement.
10. The combustor of claim 9 , wherein the second nozzle grouping is disposed between the first nozzle grouping and the third nozzle grouping on one side of the circumferential arrangement, and wherein the fourth nozzle grouping is disposed between the first nozzle grouping and the third nozzle grouping on a different side of the circumferential arrangement.
11. The combustor of claim 10 , wherein the first number for each of the first nozzle grouping and the third nozzle grouping of the plurality of duplex nozzles is larger than the second number for each of the second nozzle grouping and the fourth nozzle grouping of the plurality of simplex nozzles.
12. The combustor of claim 10 , wherein the first nozzle grouping and the third nozzle grouping are disposed in opposing relation in the circumferential arrangement, and wherein the second nozzle grouping and the fourth nozzle grouping are disposed in opposing relation in the circumferential arrangement.
13. The combustor of claim 12 , wherein the first number for each of the first nozzle grouping and the third nozzle grouping of the plurality of duplex nozzles is larger than the second number for each of the second nozzle grouping and the fourth nozzle grouping of the plurality of simplex nozzles.
14. The combustor of claim 9 , wherein the first nozzle grouping and the third nozzle grouping each include six duplex nozzles of the plurality of duplex nozzles, and wherein the second nozzle grouping and the fourth nozzle grouping each include three simplex nozzles of the plurality of simplex nozzles.
15. The combustor of claim 7 , wherein the first number for each of the first nozzle grouping and the third nozzle grouping of the plurality of duplex nozzles is larger than the second number for each of the second nozzle grouping and the fourth nozzle grouping of the plurality of simplex nozzles.
16. The combustor of claim 15 , wherein the first nozzle grouping and the third nozzle grouping of the plurality of duplex nozzles are disposed in opposing relation to one another, and wherein the second nozzle grouping and the fourth nozzle grouping of the plurality of simplex nozzles are disposed in opposing relation to one another.
17. The combustor of claim 7 , wherein the first nozzle grouping and the third nozzle groupings each include six duplex nozzles of the plurality of duplex nozzles, and wherein the second nozzle grouping and the fourth nozzle grouping each include three simplex nozzles of the plurality of simplex nozzles.
18. The combustor of claim 17 , wherein the first nozzle grouping and the third nozzle grouping of the plurality of duplex nozzles are disposed in opposing relation to one another, and wherein the second nozzle grouping and the fourth nozzle grouping of the plurality of simplex nozzles are disposed in opposing relation to one another.
19. The combustor of claim 7 , wherein the corresponding swirler of the combustor converges relative to a centerline of the fuel nozzle of the plurality of fuel nozzles proceeding to the downstream rim, and wherein the downstream rim of the corresponding swirler of the combustor defines an open discharge end.