Gas turbine combustor, gas turbine, and jet engine

1. A gas turbine combustor comprising:

a cylinder having a combustion region inside of the cylinder;

a resonator having a cavity and provided around the surface of the cylinder; and

sound absorption holes formed in the cylinder and having opening ends on the cylinder, wherein

a diameter of a sound absorption hole in the cylinder is approximately 1 to 3 mm;

a height of the resonator is approximately 6 to 25 mm, and

a plurality of fluid grooves are provided at intervals on the cylinder.

2. A gas turbine combustor according to claim 1 , wherein the resonator and the sound absorption holes correspond to the natural resonance frequency of the cylinder.

3. A gas turbine combustor according to claim 1 , wherein the resonator and the sound absorption holes are disposed near the combustion region.

4. A gas turbine combustor according to claim 1 , wherein the sound absorption holes are formed among the fluid grooves.

5. A gas turbine combustor according to claim 1 , wherein a resistive member which generates friction loss is formed in the cavity of the resonator.

6. A gas turbine combustor according to claim 5 , wherein the resistive member which generates friction loss is formed around the surface of the cylinder on which the sound absorption holes are formed.

7. A gas turbine comprising:

the gas turbine combustor according to claim 1 ;

a compressor which compresses air and supplies a flow of air; and

a turbine which expands high temperature high pressure gas supplied from the gas turbine combustor and rotates in order to generate a shaft output.

8. A jet engine comprising:

the gas turbine combustor according to claim 1 ;

a compressor which compresses air and supplies flow of air; and

a turbine to which high temperature high pressure gas is supplied from the gas turbine combustor.

9. A gas turbine combustor according to claim 1 , wherein the plurality of grooves are formed at intervals in a peripheral direction of the cylinder.

10. A gas turbine combustor according to claim 1 , wherein the plurality of grooves are passages extending within a wall of the cylinder, the passages having semicircular cross-sections.

11. A gas turbine combustor according to claim 1 , further comprising a cooling hole provided on the surface of the cylinder, wherein the cooling hole communicates with at least one fluid groove of the plurality of fluid grooves.

12. A gas turbine combustor according to claim 11 , wherein the cooling hole is provided at an upstream location from the at least one fluid groove.

13. A gas turbine combustor according to claim 1 , further comprising a cooling hole provided on an internal surface of the cylinder, wherein the cooling hole communicates with at least one fluid groove of the plurality of fluid grooves.

14. A gas turbine combustor according to claim 13 , wherein the cooling hole is provided at a downstream location from the at least one fluid groove.

15. A gas turbine combustor comprising:

a cylinder having a combustion region inside of the cylinder;

a resonator having a cavity and provided around the surface of the cylinder; and

sound absorption holes formed in the cylinder,

wherein a plurality of fluid grooves are provided at intervals on the cylinder, and

wherein the plurality of grooves are passages extending within a wall of the cylinder, the passages having semicircular cross-sections.

16. A gas turbine combustor comprising:

a cylinder having a combustion region inside of the cylinder;

a resonator having a cavity and provided around the surface of the cylinder; and

sound absorption holes formed in the cylinder,

wherein a plurality of fluid grooves are provided at intervals on the cylinder,

wherein the plurality of grooves are passages extending within a wall of the cylinder, the passages having semicircular cross-sections, and

wherein a cooling hole is provided on the cylinder, wherein the cooling hole communicates with at least one fluid groove of the plurality of fluid grooves.

17. A gas turbine combustor according to claim 16 , wherein the cooling hole is provided on the surface of the cylinder at an upstream location from the at least one fluid groove.

18. A gas turbine combustor according to claim 16 , wherein the cooling hole is provided on an internal surface of the cylinder at a downstream location from the at least one fluid groove.