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A gas turbine combustor includes a combustion liner in which a combustion region is formed; and a housing provided for a wall of the combustion liner in a predetermined circumferential region of the combustion liner to form a resonance space between the combustion liner and the housing. The combust

A gas turbine combustor includes a combustion liner in which a combustion region is formed; and a housing provided for a wall of the combustion liner in a predetermined circumferential region of the combustion liner to form a resonance space between the combustion liner and the housing. The combustion region and the resonance space are connected by a plurality of combustion liner through-holes, and a circumferential length of the housing is longer than a diameter of the combustion liner.

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What is claimed is: 1. A gas turbine combustor, comprising: a combustion liner in which a combustion region is formed; and a housing provided for a wall of said combustion liner in a predetermined circumferential region of said combustion liner to form a resonance space between said combustion line

What is claimed is: 1. A gas turbine combustor, comprising: a combustion liner in which a combustion region is formed; and a housing provided for a wall of said combustion liner in a predetermined circumferential region of said combustion liner to form a resonance space between said combustion liner and said housing, wherein said combustion region and said resonance space are connected by a plurality of combustion liner through-holes; a circumferential length of said housing is longer than a diameter of said combustion liner; and said housing comprises: an upper section opposing to the wall of said combustion liner; and side sections extending from said upper section and connected with the wall of said combustion liner to form said resonance space, wherein holes are opened in at least one of said side sections. 2. The gas turbine combustor according to claim 1, wherein a distance between said wall of said combustion liner and said housing is in a range of 10 mm to 30 mm, the diameter of each of said plurality of combustion liner through-holes is in a range of 1 mm to 5 mm, a percentage of a total of areas of said plurality of combustion liner through-holes to an area of said predetermined circumferential region is in a range of 3 percent to 10 percent, and a thickness of the wall of said combustion liner is in a range of 2 mm to 7 mm. 3. The gas turbine combustor according to claim 1, wherein each of said side sections comprises: a flat plate section; and a curved section smoothly connecting said flat plate section and said upper section, such that an angle between said flat plate section and said upper section is obtuse. 4. The gas turbine combustor according to claim 3, wherein a thickness of said housing is in a range of 1.6 mm to 5 mm, and a radius of curvature of said curved section is in a range of 5 mm to 20 mm. 5. The gas turbine combustor according to claim 1, wherein each of said side sections is connected with the wall of said combustion liner such that an angle between the wall of said combustion liner and a surface of said side section opposite to said resonance space is obtuse. 6. The gas turbine combustor according to claim 1, wherein said resonance space occupies an entire interior of said housing which is free of partition walls. 7. The gas turbine combustor according to claim 6, having only one said housing. 8. The gas turbine combustor according to claim 1, wherein said housing is connected with an outer surface of the wall of said combustion liner, and an inner surface of the wall of said combustion liner corresponding to said housing has a heat-resistant coating layer. 9. The gas turbine combustor according to claim 1, wherein said combustion liner through-holes are uniformly distributed in said predetermined circumferential region. 10. The gas turbine combustor according to claim 1, wherein said combustion liner through-holes are ununiformly distributed in said predetermined circumferential region based on a temperature distribution in said combustion region. 11. The gas turbine combustor according to claim 1 further comprising: a swirler support pipe connected with said combustion liner; and a swirler support pipe housing provided for a wall of said swirler support pipe in a predetermined circumferential region of said swirler support pipe to form a further resonance space between said swirler support pipe and said swirler support pipe housing; wherein said combustion region and said further resonance space are connected by a plurality of swirler support pipe through-holes; and a circumferential length of said swirler support pipe housing is longer than a diameter of said swirler support pipe. 12. A gas turbine generation plant, comprising a gas turbine combustor according to claim 1. 13. A gas turbine combustor, comprising: a swirler support pipe; a combustion liner connected with said swirler support pipe, a combustion region being formed in said combustion liner; and a swirler support pipe housing provided for a wall of said swirler support pipe in a predetermined circumferential region of said swirler support pipe to form a resonance space between said swirler support pipe and said swirler support pipe housing; wherein an inner space within said swirler support pipe and said resonance space are connected by a plurality of swirler support pipe through-holes; a circumferential length of said swirler support pipe housing is longer than a diameter of said swirler support pipe; and said swirler support pipe housing comprises: an upper section opposing to the wall of said swirler support pipe; and side sections extending from said upper section and connected with the wall of said swirler support pipe to form said resonance space, wherein holes are opened in at least one of said side sections. 14. The gas turbine combustor according to claim 13, wherein a distance between said wall of said swirler support pipe and said swirler support pipe housing is in a range of 10 mm to 30 mm, the diameter of each of said plurality of swirler support pipe through-holes is in a range of 1 mm to 5 mm, a percentage of a total of areas of said plurality of swirler support pipe through-holes to an area of said predetermined circumferential region is in a range of 3 percent to 10 percent, and a thickness of the wall of said swirler support pipe is in a range of 2 mm to 7 mm. 15. The gas turbine combustor according to claim 13, wherein each of said side sections comprises: a flat plate section; and a curved section smoothly connecting said flat plate section and said upper section, such that an angle between said flat plate section and said upper section is obtuse. 16. The gas turbine combustor according to claim 15, wherein a thickness of said swirler support pipe housing is in a range of 1.6 mm to 5 mm, and a radius of curvature of said curved section is in a range of 5 mm to 20 mm. 17. The gas turbine combustor according to claim 13, wherein each of said side sections is connected with the wall of said swirler support pipe such that an angle between the wall of said swirler support pipe and a surface of said side section opposite to said resonance space is obtuse. 18. The gas turbine combustor according to claim 13, wherein said resonance space occupies an entire interior of said swirler support pipe housing which is free of partition walls. 19. The gas turbine combustor according to claim 18, having only one said swirler support pipe housing. 20. The gas turbine combustor according to claim 13, wherein said swirler support pipe housing is connected with an outer surface of the wall of said swirler support pipe, and an inner surface of the wall of said swirler support pipe corresponding to said swirler support pipe housing has a heat-resistant coating layer. 21. The gas turbine combustor according to claim 13, wherein said swirler support pipe through-holes are uniformly distributed in said predetermined circumferential region. 22. The gas turbine combustor according to claim 13, wherein said swirler support pipe through-holes are ununiformly distributed in said predetermined circumferential region based on a temperature distribution in said combustion region. 23. A gas turbine generation plant, comprising a gas turbine combustor according to claim 13. 24. A method manufacturing a gas turbine combustor, comprising: providing a combustion liner in which a combustion region is to be formed; forming a plurality of combustion liner through-holes through a wall of said combustion liner and in a predetermined circumferential region of said combustion liner; providing a plate for forming a combustion liner housing, said plate having a first slag hole and a plurality of further holes; welding said plate to said combustion liner to form the combustion liner housing; and removing weld slag left in said combustion liner housing via said first slag hole; wherein the plate is provided and welded to the combustion liner so that the formed combustion liner housing (i) extends over the predetermined circumferential region of said combustion liner, (ii) defines a resonance space located between said combustion liner and said housing and connected to the combustion region by the combustion liner through-holes, and (iii) comprises: an upper section opposing to the wall of said combustion liner; and side sections extending from said upper section and connected with the wall of said combustion liner to form said resonance space, wherein some of said further holes of the plate are opened in at least one of said side sections. 25. The method according to claim 24, further comprising: blocking said first slag hole after said removing. 26. The method according to claim 24, further comprising: coupling a swirler support pipe to said combustion liner; welding a swirler support pipe housing with a second slag hole to said swirler support pipe; and removing weld slag left in said swirler support pipe housing via said second slag hole. 27. The method according to claim 26, further comprising: blocking said second slag hole after removing weld slag via said second slag hole. 28. A method of manufacturing a gas turbine combustor, comprising: providing a swirler support pipe; forming a plurality of swirler support pipe through-holes through a wall of said swirler support pipe and in a predetermined circumferential region of said swirler support pipe; providing a plate for forming a swirler support pipe housing, said plate having a first slag hole and a plurality of further holes; welding said plate to said swirler support pipe to form the swirler support pipe housing; and removing weld slag left in said swirler support pipe housing via said first slag hole; wherein the plate is provided and welded to the swirler support pipe so that the formed swirler support pipe housing (i) extends over the predetermined circumferential region of said swirler support pipe, (ii) defines a resonance space located between said swirler support pipe and said housing and connected to an inner space of said swirler support pipe by the swirler support pipe through-holes, and (iii) comprises: an upper section opposing to the wall of said swirler support pipe; and side sections extending from said upper section and connected with the wall of said swirler support pipe to form said resonance space, wherein some of said further holes of the plate are opened in at least one of said side sections. 29. The method according to claim 28, further comprising: blocking said first slag hole after said removing.