A compressor compresses air to produce compressed air. A mixture of fuel and the compressed air is combusted in a combustor to produce combustion gas. The combustion gas is supplied to a turbine to obtain rotational power. High-temperature gas accumulated in a space partitioned by an exhaust-side bearing portion that rotatably supports a turbine shaft and an exhaust diffuser is discharged through an exhaust gas passage. The high-temperature gas is sucked into the exhaust gas passage by exhaust gas flowing in the exhaust diffuser.
1. A gas turbine, comprising:
a compressor configured to compress air to produce compressed air;
a combustor configured to combust a mixture of fuel and the compressed air to produce combustion gas;
a turbine having a turbine shaft configured to be rotationally driven by the combustion gas;
an exhaust diffuser configured to exhaust the combustion gas, as exhaust gas, from the turbine;
an exhaust-side bearing portion rotatably supporting the turbine shaft; and
an exhaust gas passage through which high-temperature gas accumulated in a space partitioned by the exhaust-side bearing portion and the exhaust diffuser is to be discharged, wherein
the high-temperature gas is arranged to be sucked into the exhaust gas passage by the exhaust gas flowing in the exhaust diffuser,
the space is partitioned by
a bearing box defining the exhaust-side bearing portion,
an inner cylindrical portion of the exhaust diffuser, and
a partition wall that connects end portions of the bearing box and the inner cylindrical portion on a side of the turbine,
the exhaust gas passage includes a plurality of exhaust holes formed on the partition wall,
the gas turbine further comprises a flow-rate control unit configured to control a flow rate of the high-temperature gas through at least one of the plurality of exhaust holes,
the gas turbine further comprises a plurality of exhaust connecting pipes which are connected at first ends to the plurality of exhaust holes, project into the space and include the flow-rate control unit,
each of the plurality of exhaust connecting pipes includes a pipe portion bent at a right angle,
second ends of the exhaust connecting pipes disposed on an upper side of the partition wall face downward in a circumferential direction of the partition wall, and
second ends of the exhaust connecting pipes disposed on a lower side of the partition wall face downward.
2. The gas turbine according to claim 1 , wherein the flow-rate control unit is a cap that covers the second end of one of one of the plurality of exhaust connecting pipes.
3. The gas turbine according to claim 2 , wherein
the cap is configured to change a size of a cross section of the second end of the exhaust connecting pipe according to an amount of rotation of the cap.
4. The gas turbine according to claim 1 , wherein the second ends of the exhaust connecting pipes disposed on the upper side of the partition wall are oriented in directions oblique to a downward direction in which the second ends of the exhaust connecting pipes disposed on the lower side of the partition wall are oriented.
5. The gas turbine according to claim 4 , wherein the gas turbine comprises a plurality of flow-rate control units provided to the plurality of exhaust connecting pipes, respectively, to control the flow rate of the high-temperature gas through the plurality of exhaust holes, respectively.