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An improved flame tube or “liner” (112) for a combustion chamber (110) of a gas turbine with low emission of pollutants, of the type comprising a cylindrical structure connected to the outlet of a premixing chamber (114) by means of a truncated conical end (120), in which the premixing chamber (114)

An improved flame tube or “liner” (112) for a combustion chamber (110) of a gas turbine with low emission of pollutants, of the type comprising a cylindrical structure connected to the outlet of a premixing chamber (114) by means of a truncated conical end (120), in which the premixing chamber (114) is supplied with air which is guided by a cavity (116) which is located between the flame tube (112) and outer walls (118) of the combustion chamber (110), this air circulating in the opposite direction to the flow of combustion products; a first cylindrical region (122) of the flame tube (112) is surrounded by a cylindrical casing (136) which creates an annular chamber (138).

대표청구항 ▼

1. A combustor for a gas turbine, comprising;an outer wall, a liner within the outer wall, said outer wall and said liner defining a cavity therebetween;a premixing chamber;a combustion chamber within said liner;said liner including a cylindrical structure connected to an outlet of said premixing ch

1. A combustor for a gas turbine, comprising;an outer wall, a liner within the outer wall, said outer wall and said liner defining a cavity therebetween;a premixing chamber;a combustion chamber within said liner;said liner including a cylindrical structure connected to an outlet of said premixing chamber by a truncated conical end, said premixing chamber being supplied with air flowing along said cavity in an opposite direction to a flow of combustion products through the combustor;said cylindrical structure including a first cylindrical region of said liner surrounded by a cylindrical casing within said outer wall and forming an annular chamber with said liner, said cylindrical structure including a first set of apertures in said first cylindrical region for admitting air from said annular chamber through the liner into the combustion chamber enabling a damping of pressure oscillations within the liner.2. A combustor according to claim 1 wherein said first set of apertures of the said first cylindrical region are positioned at the nodes of square meshes and formed in a first portion of said first cylindrical region axially close to said truncated conical end.3. A combustor according to claim 1 wherein said cylindrical casing has annular joints at axially opposite ends which connect said cylindrical casing to the first cylindrical region and enclose said annular chamber.4. A combustor according to claim 1 including a second set of apertures formed in said cylindrical casing for impingement cooling of said first cylindrical region.5. A combustor according to claim 4 wherein said second set of apertures are positioned on the nodes of square meshes.6. A combustor according to claim 5 wherein said first set of apertures of the said first cylindrical region are positioned at the nodes of square meshes and formed in a first portion of said first cylindrical region axially close to said truncated conical end;said meshes of said second set of apertures in said cylindrical casing being identical to said meshes of said first set of apertures in said first cylindrical region.7. A combustor according to claim 4 wherein said second set of apertures in said cylindrical casing are smaller than the said first set of apertures in the said first cylindrical region and are staggered relative to one another.8. A combustor according to claim 1 wherein said first cylindrical region has a first cylindrical portion without apertures located in a part axially opposite said truncated conical end.9. A combustor according to claim 8 wherein said first cylindrical region has a second cylindrical portion with said first set of apertures, annular separator element in said annular chamber between said first cylindrical portion of said first cylindrical region without said apertures and said second cylindrical portion with said first set of apertures.10. A combustor according to claim 1 including a second cylindrical region longer than said first cylindrical region, said second cylindrical region having a further set of apertures.11. A combustor for a gas turbine, comprising:an outer wall, a liner within the outer wall, said outer wall and said liner defining a cavity therebetween;a premixing chamber;a combustion chamber within said liner;said liner including a cylindrical structure connected to an outlet of said premixing chamber by a truncated conical end, said premixing chamber being supplied with air flowing along said cavity in an opposite direction to a flow of combustion products through the combustor;said cylindrical structure including a first cylindrical region of said liner surrounded by a cylindrical casing within said outer wall and forming an annular chamber with said liner;said first cylindrical region having a first cylindrical portion without apertures located axially opposite said truncated conical end and a second cylindrical portion having a first set of apertures, an annular separator element in said annular chamber between said first cylindrical portion without apertures and said second cylindrical portion having said first set of apertures, said annular separator element having at least one orifice for connecting the first cylindrical portion and the second cylindrical portion of the annular chamber defined in part by said separator element.12. A combustor according to claim 11 including a circumferential set of holes formed in said first cylindrical portion of the cylindrical region without apertures adjacent an annular joint between said liner and said cylindrical casing.