Gas turbine, method of controlling air supply and computer program product for controlling air supply
View Patent ↗The present invention provides a gas turbine capable of reducing energy consumption while suppressing a so-called cat back phenomenon. The gas turbine includes a combustor-accommodating chamber casing for accommodating therein a combustor which burns fuel and air compressed by a compressor to generate combustion gas and which injects the combustion gas to a turbine. The gas turbine also includes a first air supply passage and a second air supply passage on an upper portion of the combustor-accommodating chamber casing in the vertical direction. The first air supply passage discharges air toward the compressor in the combustor-accommodating chamber casing. The second air supply passage discharges air in a direction different from that of the first air supply passage.
1. A gas turbine comprising:
a combustor-accommodating chamber for accommodating therein a combustor which burns fuel and air compressed by a compressor to generate combustion gas and which injects the combustion gas to a turbine;
first air supply means provided on an upper portion of the combustor-accommodating chamber in a vertical direction for discharging air toward the combustor and the compressor in the combustor-accommodating chamber in an inclined direction to a rotor shaft; and
second air supply means provided on the upper portion of the combustor-accommodating chamber in a vertical direction for discharging air into the combustor-accommodating chamber in a direction different from that of the first air supply means and towards a rotation center axis of the rotor shaft.
2. The gas turbine according to claim 1 , wherein the second air supply means discharges air toward a lower portion of the combustor-accommodating chamber in the vertical direction.
3. The gas turbine according to claim 1 , wherein a plurality of combustors are provided as the combustor and the first air supply means discharges air toward a space between the plurality of combustors.
4. The gas turbine according to claim 1 , wherein when the engine revolution number of the gas turbine becomes smaller than a predetermined revolution number after operation of the gas turbine is stopped, at least one of the first air supply means and the second air supply means discharges air into the combustor-accommodating chamber.
5. The gas turbine according to claim 1 , wherein an amount of air discharged into the combustor-accommodating chamber from at least one of the first air supply means and the second air supply means is varied based on the temperature of an upper portion of the combustor-accommodating chamber in the vertical direction, and the temperature of a lower portion of the combustor-accommodating chamber in the vertical direction.