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For the purpose of reduced NOx gas emission, a gas turbine engine comprises 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 on the cylinder and having opening ends on the cylin

For the purpose of reduced NOx gas emission, a gas turbine engine comprises 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 on the cylinder and having opening ends on the cylinder.

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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; andsound absorption holes formed in the cylinder and having opening ends on the cylinder, whereina diameter of a sound absor

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; andsound absorption holes formed in the cylinder and having opening ends on the cylinder, whereina 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, anda 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; anda 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; anda 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; andsound absorption holes formed in the cylinder,wherein a plurality of fluid grooves are provided at intervals on the cylinder, andwherein 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; andsound 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, andwherein 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.