Compressor rotor, gas turbine rotor provided therewith, and gas turbine
A ventilation flow path for guiding a compressed gas flowing between two blade rows adjacent in an axial direction to an interior of a compressor rotor shaft is formed in the compressor rotor shaft. The ventilation flow path has an introduction part, a plurality of branch parts, and a collection part. The introduction part guides the compressed gas flowing between the two blade rows into the compressor rotor shaft. The plurality of branch parts branch out from the introduction part, and are formed in mutually different positions in the axial direction. The collection part is connected to each of the plurality of branch parts. The compressed gas flows into the collection part after passing through the plurality of branch parts, and then, the compressed gas that has flowed in flows outside through the collection part.
1. A compressor rotor comprising:
a compressor rotor shaft that rotates about an axial line and which has a plurality of rotor discs stacked in an axial direction; and
a plurality of blade rows attached to an outer circumference of the compressor rotor shaft and aligned in the axial direction, wherein
a ventilation flow path for guiding compressed gas flowing between two blade rows adjacent in the axial direction among the plurality of blade rows to an interior of the compressor rotor shaft is formed in the compressor rotor shaft,
the ventilation flow path has
an introduction part for guiding the compressed gas flowing between the two blade rows into the compressor rotor shaft,
a plurality of branch parts which branch from the introduction part and are formed in mutually different positions in the axial direction, and into which the compressed gas flows from the introduction part, and
a collection part which is connected to each of the plurality of branch parts, into which the compressed gas flows after passing through the plurality of branch parts, and through which the compressed gas that has flowed in flows outside,
each of the plurality of branch parts has a cavity, and
the introduction part comprises:
an inflow part in which an inflow port into which the compressed gas flowing between the two blade rows flows among the plurality of the blade rows, and into which the compressed gas flowing between two other blade rows adjacent in the axial direction does not flow is formed, and which extends toward a radially inner side with respect to the axial line from the inflow port, and
a distribution part which is located at a radially inner side of the inflow part,
wherein
the distribution part is formed between the inflow part and the plurality of the branch parts in the radial direction, and is connected to the plurality of the branch parts.
2. The compressor rotor according to claim 1 , wherein
the distribution part extends in the axial direction from the inflow part.
3. The compressor rotor according to claim 2 , wherein
the distribution part extends toward an axially upstream side from the inflow part.
4. The compressor rotor according to claim 2 , wherein
the distribution part extends toward an axially downstream side from the inflow part.
5. The compressor rotor according to claim 1 , wherein
the collection part extends toward the axially downstream side from the branch part farthest on the axially upstream side out of the plurality of branch parts, and an outflow port through which compressed gas that has passed through the interior flows outside is formed in the collection part.
6. The compressor rotor according to claim 1 , wherein
the collection part is formed farther on the radially inner side with respect to the axial line than the introduction part.
7. The compressor rotor according to claim 1 , wherein
an outflow port through which the compressed gas flows out in the axial direction from an end surface in the axial direction of the compressor rotor shaft is formed in the collection part.
8. A gas turbine rotor comprising:
the compressor rotor according to claim 1 ; and
a turbine rotor that is positioned on the axial line, is connected to the compressor rotor, and rotates together with the compressor rotor about the axial line, wherein
a cooling air flow path which is connected to the ventilation flow path of the compressor rotor and into which the compressed gas flows from the ventilation flow path is formed in the turbine rotor.
9. The gas turbine rotor according to claim 8 , wherein
the turbine rotor has a turbine rotor shaft that rotates about the axial line, and a plurality of blade rows attached to an outer circumference of the turbine rotor shaft and aligned in the axial direction, and
the cooling air flow path is connected through an interior of the turbine rotor shaft to a blade row farther on the axially downstream side than a first blade row of the plurality of blade rows that is farthest on the axially upstream side.
10. The gas turbine rotor according to claim 9 , wherein
a cooling air flow path for guiding cooling air, having a lower temperature than the compressed gas flowing through the ventilation flow path, to the first blade row is formed in the turbine rotor shaft.
11. A gas turbine comprising:
the gas turbine rotor according to claim 8 ; and
a gas turbine casing covering the gas turbine rotor.