Gas turbine system
View Patent ↗A gas turbine system comprises a compressor for compressing air, a combustor for burning the air compressed by the compressor and fuel, a turbine driven by combustion gases produced from the combustor, and a spraying apparatus for adding water to working air at least upstream or in an intermediate stage of the compressor. A rotationally symmetric groove or projection is formed in an inner wall surface defining a channel through which the working air added with the water flows, or in a channel-defining surface of a rotor or a casing of the gas turbine. A larger amount of water can be supplied to the compressor while improving the reliability of the gas turbine.
1. A gas turbine system comprising:
a compressor for compressing air;
a combustor for burning the air compressed by said compressor and fuel;
a turbine driven by combustion gases produced from said combustor; and
a spraying apparatus for adding water to working air at least upstream or in an intermediate stage of said compressor,
a casing defining a channel through which the working air with added water flows;
wherein a rotationally symmetric groove or projection is formed in an inner wall surface of said casing, and
wherein said rotationally symmetric groove or projection is formed at an inlet of a bell mouth of said casing.
2. The gas turbine system according to claim 1 , further including plural ones of said rotationally symmetric groove or projection formed in adjacent relation.
3. The gas turbine system according to claim 1 , wherein said rotationally symmetric groove or projection has an edge on the downstream side in a direction of flow of intake air.
4. The gas turbine system according to claim 1 , wherein said rotationally symmetric groove or projection has a rectangular sectional shape.
5. The gas turbine system according to claim 1 wherein at least one side wall of said rotationally symmetric groove is inclined in a direction opposing the direction of flow of the intake air near said groove.
6. The gas turbine system according to claim 1 , wherein a porous medium is inserted in said rotationally symmetric groove.
7. The gas turbine system according to claim 1 , wherein said rotationally symmetric groove or projection is fonned in a channel-defining surface of a rotor or a casing of said gas turbine.
8. The gas turbine system according to claim 1 , wherein said rotationally symmetric groove or projection is formed in a mainstream channel surface near an inlet casing of said compressor.
9. The gas turbine system according to claim 1 , wherein a drain channel is provided below said rotationally symmetric groove or projection in the direction of gravity.