Gas turbine engine with resonator rings
A gas turbine engine has a resonator ring that is formed by two circumferentially extending rings. The first and second circumferentially extending rings have located within them baffles. Both the first ring and the second ring are able to mitigate acoustic frequencies generated by the gas turbine engine.
1. A gas turbine engine comprising:
a combustor located within a combustor basket;
a resonator ring connected to the combustor basket; wherein the resonator ring comprises a first ring and a second ring, wherein the first ring is located upstream of the second ring;
wherein the first ring comprises a first perimeter wall and a second perimeter wall extending in a circumferential direction, wherein located between the first perimeter wall and the second perimeter wall is a first bottom portion and a first top portion, wherein the first bottom portion has a first plurality of holes, wherein the first top portion has a second plurality of holes;
further wherein located between the first perimeter wall and the second perimeter wall is a first plurality of baffles, wherein each of the first plurality of baffles extends orthogonally with respect to the first perimeter wall and the second perimeter wall;
wherein the second ring comprises the second perimeter wall and a third perimeter wall extending in a circumferential direction, wherein located between the second perimeter wall and the third perimeter wall is a second bottom portion and a second top portion, wherein the second bottom portion has a third plurality of holes, wherein the second top portion has a fourth plurality of holes;
further wherein located between the second perimeter wall and the third perimeter wall is a second plurality of baffles, wherein each of the second plurality of baffles extends orthogonally with respect to the second perimeter wall and the third perimeter wall,
wherein a distribution of the second plurality of holes formed in first top portion is different than a distribution of the fourth plurality of holes formed in the second top portion, and
wherein the distribution comprises spacing or size of the second plurality of holes and the fourth plurality of holes,
wherein the first perimeter wall comprises a first plurality of slots and the second perimeter wall comprises a second plurality of slots, and
wherein each of the first plurality of baffles is inserted to a respective slot of the first plurality of slots and a respective slot of the second plurality of slots.
2. The gas turbine engine of claim 1 , wherein a length of each baffle of the first plurality of baffles is different than a length of each of the second plurality of baffles.
3. The gas turbine engine of claim 1 , wherein a distance between adjacent baffles of the first plurality of baffles is greater than a distance between adjacent baffles of the second plurality of baffles.
4. The gas turbine engine of claim 1 , wherein a total number of baffles in the first plurality of baffles is different than a total number of baffles in the second plurality of baffles.
5. The gas turbine engine of claim 1 , wherein a distribution of the first plurality of holes formed in the first bottom portion is different than a distribution of the third plurality of holes formed in the second bottom portion, and wherein the distribution comprises spacing or size of the first plurality of holes and the third plurality of holes.
6. The gas turbine engine of claim 1 , wherein the first top portion is formed from a plurality of top portion sections.
7. The gas turbine engine of claim 1 , wherein an area of the first bottom portion between adjacent baffles of the first plurality of baffles is greater than an area of the second bottom portion between adjacent baffles of the second plurality of baffles.
8. The gas turbine engine of claim 1 , wherein a volume formed between adjacent baffles of the first plurality of baffles is greater than a volume formed between adjacent baffles of the second plurality of baffles.
9. The gas turbine engine of claim 1 , wherein a diameter of each hole in the first plurality of holes is smaller than a diameter of each hole in the second plurality of holes.
10. The gas turbine engine of claim 1 , wherein each of the first plurality of baffles is secured with a labyrinth seal.
11. A resonator ring connected to a combustor basket comprising:
a first ring and a second ring, wherein the first ring is located upstream of the second ring;
wherein the first ring comprises a first perimeter wall and a second perimeter wall extending in a circumferential direction, wherein located between the first perimeter wall and the second perimeter wall is a first bottom portion and a first top portion, wherein the first bottom portion has a first plurality of holes, wherein the first top portion has a second plurality of holes;
further wherein located between the first perimeter wall and the second perimeter wall is a first plurality of baffles, wherein each of the first plurality of baffles extends orthogonally with respect to the first perimeter wall and the second perimeter wall;
wherein the second ring comprises the second perimeter wall and a third perimeter wall extending in a circumferential direction, wherein located between the second perimeter wall and the third perimeter wall is a second bottom portion and a second top portion, wherein the second bottom portion has a third plurality of holes, wherein the second top portion has a fourth plurality of holes;
further wherein located between the second perimeter wall and the third perimeter wall is a second plurality of baffles, wherein each of the second plurality of baffles extends orthogonally with respect to the second perimeter wall and the third perimeter wall,
wherein a distribution of the second plurality of holes formed in the first top portion is different than a distribution of the fourth plurality of holes formed in the second top portion, and
wherein the distribution comprises spacing or size of the second plurality of holes and the fourth plurality of holes,
wherein the first perimeter wall comprises a first plurality of slots and the second perimeter wall comprises a second plurality of slots, and
wherein each of the first plurality of baffles is inserted to a respective slot of the first plurality of slots and a respective slot of the second plurality of slots.
12. The resonator ring of claim 11 , wherein a length of one of the first plurality of baffles is different than a length of one of the second plurality of baffles.
13. The resonator ring of claim 11 , wherein a distance between adjacent baffles of the first plurality of baffles is greater than a distance between adjacent baffles of the second plurality of baffles.
14. The resonator ring of claim 11 , wherein a total number of baffles in the first plurality of baffles is different than a total number of baffles in the second plurality of baffles.
15. The resonator ring of claim 11 , wherein a distribution of the first plurality of holes formed in the first bottom portion is different than a distribution of the third plurality of holes formed in the second bottom portion, and wherein the distribution comprises spacing or size of the first plurality of holes and the third plurality of holes.
16. The resonator ring of claim 11 , wherein the first top portion is formed from a plurality of top portion sections.
17. The resonator ring of claim 11 , wherein an area formed between adjacent baffles of the first plurality of baffles is less than an area formed between adjacent baffles of the second plurality of baffles.
18. The resonator ring of claim 11 , wherein a volume formed between adjacent baffles of the first plurality of baffles is less than a volume formed between adjacent baffles of the second plurality of baffles.
19. The resonator ring of claim 11 , wherein a diameter of each hole in the first plurality of holes is smaller than a diameter of each hole in the second plurality of holes.
20. The resonator ring of claim 11 , wherein each of the first plurality of baffles is secured with a labyrinth seal.