Gas turbine and method for discharging gas from gas turbine

Abstract

In order to provide a gas turbine and a gas bleeding method which can prevent the loss of drive power due to gas bleeding to the rotor disk, bleed gas is imparted with swirling flow in the same rotational direction as that of a first stage rotor disk by being passed through a set of TOBI nozzles which constitute a flow conduit therefor, and is supplied to this first stage rotor disk, with a portion of this bleed gas flow being bypassed and being supplied between first stage stationary blades and first stage moving blades.

Description

technical field [0001] The present invention relates to a gas turbine and a gas discharge method thereof, which perform sealing by supplying discharge gas from a compressor between movable blades and fixed blades while cooling the movable blades. Background technique [0002] In a gas turbine plant, the compressed air from the compressor is supplied to the combustor, where it is combusted with fuel to produce high temperature gas, which is sent to the gas turbine to drive the gas turbine. In the usual structure, a part of the compressed air is sent to the cooling device as exhaust gas at the same time, and after cooling, the exhaust gas is supplied to the fixed blades and movable blades on the side of the gas turbine, thereby cooling and sealing the movable blades and fixed blades. In this prior art, to The structure of the gas turbine in which the fixed blades and movable blades of the first-stage turbine provide exhaust gas will be described below with reference to FIG. 3 ...

AI Technical Summary

Problems solved by technology

[0009] That is, the discharge gas flow f1 supplied from the discharge gas chamber 5 hardly has any rotational velocity component in the circumferential direction of the rotation axis as the center because it enters the disk hole 3a1 (a plurality of perforated so as to diverge from the axis of rotation), thus, the problem of drive energy loss arises

[0010] That is to say, although each cooling air flow duct 3a rotates at a high speed with the first-stage rotor disk 3 of the main rotating body, since in this high-speed rotation state, there is hardly any The cooling air flow f2 of the high rotational speed component flows into and passes through the first-stage rotor disk 3, and accordingly, this cooling air flow f2 produces an unsuitable braking force, which restricts the rotation operation of the first-stage rotor disk 3; moreover, the rotation includes The driving energy required for the rotating body including the first stage rotor disk 3 is unfavorably increased

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