Gas turbine combustor and gas turbine
The present invention reduces thermal stress that is applied to the weld zone of a cavity formed in the structural material of a burner. The burner includes the cavity distributing a fuel to fuel nozzles. The cavity is demarcated by a groove formed in the structural material of the burner so as to create a level difference at an opening, and a cover fitted into the level difference to close the groove. The cover is formed by a web covering the opening in the groove and a flange extending in the depth direction of the groove to be fitted into the level difference, and is joined by welding to the structural material in such a manner as to have an L-shaped cross-section. When viewed in a cross-section orthogonal to the groove, a cover-side inner surface that is an inner surface of the flange forming a lateral surface of the cavity is flush with a groove-side inner surface that is an inner surface of the groove forming a lateral surface of the cavity. The boundary between the cover-side inner surface and the groove-side inner surface is away from a first corner of the cavity sandwiched between the cover-side inner surface and the inner surface of the web forming a ceiling surface of the cavity.
1. A gas turbine combustor that receives compressed air discharged from a compressor, mixes the compressed air with a fuel, burns a mixture of the compressed air and the fuel to generate a combustion gas, and supplies the generated combustion gas to a turbine, the gas turbine combustor comprising:
an inner cylinder configured to form a combustion chamber therein;
an outer cylinder configured to cover the inner cylinder and form a cylindrical outer circumferential flow path between the outer cylinder and the inner cylinder to allow the compressed air to flow; and
a burner that is mounted on an end of the outer cylinder, the end being positioned on an opposite side to a side where the turbine is located, and that faces the combustion chamber, wherein
the burner includes a plurality of fuel nozzles configured to inject the fuel, and a cavity configured to distribute the fuel to the fuel nozzles,
the cavity is demarcated by a groove formed in a structural material of the burner to create a level difference at an opening, and a cover fitted into the level difference to close the groove,
the cover is formed by a web and a flange and joined by welding to the structural material in such a manner as to have an L-shaped or U-shaped cross-section, the web facing a bottom surface of the groove and covering the opening in the groove, the flange extending in a depth direction of the groove from an edge of the web and fitted into the level difference,
when viewed in a cross-section orthogonal to the groove, a cover-side inner surface that is an inner surface of the flange is flush with a groove-side inner surface that is an inner surface of the groove, the cover-side inner surface and the groove-side inner surface together forming a lateral surface of the cavity, and
a boundary between the cover-side inner surface and the groove-side inner surface is spaced away from a first corner of the cavity that is sandwiched between the cover-side inner surface and an inner surface of the web, the inner surface of the web forming a ceiling surface of the cavity.
2. The gas turbine combustor according to claim 1 , wherein
the web of the cover includes a thin section that is thinner than a section adjacent to the thin section of the web.
3. The gas turbine combustor according to claim 2 , wherein
the ceiling surface of the cavity formed by the web has a recess that forms the thin section.
4. The gas turbine combustor according to claim 3 , wherein an inner surface of the recess is flush with an other inner surface of the groove, and an other boundary between the inner surface of the recess and the other inner surface of the groove is spaced away from a second corner of the cavity formed by the recess.
5. The gas turbine combustor according to claim 1 , wherein the cavity is connected to a fuel supply source directly not via a fuel heating facility.
6. The gas turbine combustor according to claim 1 , wherein
the welding is performed by a laser welding method or an electron beam welding od.
7. The gas turbine combustor according to claim 1 , wherein
a penetration depth achieved by the welding is greater than a bead width.
8. A gas turbine comprising:
a compressor configured to compress air to generate compressed air;
the gas turbine combustor according to claim 1 that receives compressed air discharged from the compressor, mixes the compressed air with a fuel, and burns a mixture of the compressed air and the fuel to generate a combustion gas; and
a turbine configured to be driven by the combustion gas supplied from the gas turbine combustor.