Gas turbine combustor and gas turbine

A gas turbine combustor having a combustion chamber for effecting combustion therein, a fuel air premixing device for premixing and supplying fuel and combustion air into said combustion chamber, the supplied fuel air being burnt in said combustion chamber to generate a flame, and a stabilizer for stabilizing the flame, characterized in that said stabilizer comprises a cylindrical part axially extending from an upstream end to a downstream end and having a plurality of through holes arranged in a circumferential direction with intervals, and a stabilizing part axially extending from the downstream end of said cylindrical part toward a downstream side and having a section which is taken along an axis of said stabilizer and increases in thickness thereof toward a downstream side, and said stabilizer is disposed so that said stabilizing portion is positioned near and downstream of an outlet of said fuel air premixing device, and mounted on an inside of said combustor by a mounting device, said mounting device comprising a plurality of members each radially extending and secured to the inside of said combustor at ends thereof and having a section slidably fitted in one of said holes formed in said cylindrical part to restrict axial movement of said stabilizer while allowing deformation due to thermal stress and another section to restrict radial movement of said stabilizer.

A gas turbine provided with a combustor having a combustion chamber for effecting combustion therein, a fuel air supply device for supplying fuel and combustion air into said combustion chamber, the supplied fuel air being burnt in said combustion chamber to generate a flame, and a stabilizer for stabilizing the flame, characterized in that said stabilizer is cylindrical as a whole and comprises a cylindrical part axially extending from an upstream end thereof and to a downstream end and a stabilizing part axially extending from said downstream end of said cylindrical part toward a downstream side for stabilizing the flame, said cylindrical part having a plurality of openings arranged at internals in a circumferential direction of said cylindrical part, and a mounting device is disposed in fuel and combustion air in said fuel air supply device and mounted for mounting said stabilizer on an inside of said combustor, said mounting device including a plurality of members each secured to the inside of said combustor and slidably inserted in one of said plurality of openings and connected to said cylindrical part so as to restrict axial and radial movement of said stabilizer while allowing deformation of said stabilizer due to thermal stress caused therein.

A gas turbine provided with a combustor having a combustion chamber for effecting combustion therein, a fuel air supply device for supplying fuel and combustion air into said combustion chamber, the supplied fuel air being burnt in said combustion chamber to generate a flame, and a stabilizer for stabilizing the flame, characterized in that said stabilizer comprises a cylindrical part axially extending from an upstream end to a downstream end and having a plurality of openings arranged in a circumferential direction with intervals, and a stabilizing part axially extending from the downstream end of said cylindrical part toward a downstream side and having a section which is taken along an axis of said stabilizer and increases in thickness thereof, and said stabilizer is disposed so that said stabilizing portion is positioned near and downstream of an outlet of said fuel air remixing device, and mounted on an inside of said combustor by a mounting device said mounting device comprising a plurality of members each radially extending and secured to the inside of said combustor at ends thereof and having a section slidably fitted in one of said openings formed in said cylindrical part to restrict axial movement of said stabilizer while allowing deformation due to thermal stress and another section of each of said members to restrict radial movement of said stabilizer.