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An annular type gas turbine combustor having a plurality of fuel nozzle assemblies (10) on a circumference includes a pilot nozzle unit (12) for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle (34) into a combustion chamber (8), a main nozzle unit (14) provided so as to

An annular type gas turbine combustor having a plurality of fuel nozzle assemblies (10) on a circumference includes a pilot nozzle unit (12) for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle (34) into a combustion chamber (8), a main nozzle unit (14) provided so as to surround the pilot nozzle unit (12) for spraying a fuel for premix combustion, and a flow guide (27) disposed on a downstream side of each of the fuel nozzle assemblies (10) and having a sectional area of a passage for air and air-fuel mixture from each of the fuel nozzle assemblies (10), which gradually increase in a downstream direction.

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1. An annular gas turbine combustor comprising: one or more fuel nozzle assemblies disposed on a circumference, each fuel nozzle assembly of the one or more fuel nozzle assemblies comprising:a respective first fuel injection unit configured to spray a first fuel from a respective spraying nozzle int

1. An annular gas turbine combustor comprising: one or more fuel nozzle assemblies disposed on a circumference, each fuel nozzle assembly of the one or more fuel nozzle assemblies comprising:a respective first fuel injection unit configured to spray a first fuel from a respective spraying nozzle into a combustion chamber,a respective second fuel injection unit surrounding each respective first fuel injection unit and configured to spray a second fuel into the combustion chamber,a respective main outlet flare forming a respective outlet, each respective main outlet flare flaring outwardly towards a respective downstream side of each fuel nozzle assembly of the one or more fuel nozzle assemblies,wherein the first fuel and the second fuel are provided to the combustion chamber through each respective main outlet flare; anda respective flow guide mounted on a respective downstream side of each respective second fuel injection unit, each respective flow guide having a respective cross sectional area of a respective passage for an air and an air-fuel mixture from the respective second fuel injection unit, the respective cross sectional area of each flow guide increasing towards a respective downstream side of each flow guide;wherein the respective flow guide is disposed radially outwardly of the respective main outlet flare, andwherein each flow guide comprises:a respective annular radially inner portion separated from a respective annular radially outer portion by a respective annular conduit;each annular radially inner portion and each annular radially outer portion having a respective upstream portion, wherein a respective inner surface of each respective upstream portion is sloped relative to a respective central axis so as to diverge away from the respective central axis in a downstream direction;each annular radially inner portion and each annular radially outer portion each having a respective downstream portion, wherein a respective inner surface of each respective downstream portion is either sloped less relative to the respective central axis than the respective upstream portion or is at a respective constant distance from the respective central axis. 2. The annular gas turbine combustor as claimed in claim 1, wherein each flow guide has a respective transverse cross sectional shape that is round and has a respective upstream end a respective inner diameter which is equal to or greater than a respective air outlet diameter of the respective second fuel injection unit. 3. The annular gas turbine combustor as claimed in claim 1, wherein the respective upstream portion of each annular radially inner portion and each annular radially outer portion comprises a respective conical portion of a respective shape flared in a respective conical shape from a respective upstream side of the respective second fuel injection unit towards the respective downstream side of the respective second fuel injection unit. 4. The annular gas turbine combustor as claimed in claim 3, wherein a respective angle of each conical portion relative to each respective central axis is between 25 and 50 degrees. 5. The annular gas turbine combustor as claimed in claim 3, wherein the respective downstream portion of each annular radially inner portion and each annular radially outer portion comprises a respective cylindrical portion continued with a respective downstream end of the respective conical portion. 6. The annular gas turbine combustor as claimed in claim 3, wherein each conical portion a respective downstream end, and a respective outer diameter of the respective downstream end each conical portion is greater than or equal to 0.9HL where H represents a radial width of the combustion chamber that is formed inside of the combustor. 7. The annular gas turbine combustor as claimed in claim 1, wherein each flow guide has a respective downstream end positioned at a location upstream of a maximum diameter portion of a circulation region of the combustion chamber. 8. The annular gas turbine combustor as claimed in claim 1, wherein a respective outer diameter of a respective downstream end of each flow guide is greater than or equal to 0.9H, where H represents a radial width of the combustion chamber.