Turbine blades, manufacturing methods of turbine blades, gas turbines and technical features

Technical characteristics:

1. A turbine blade provided with a cooling passage along the blade height direction, wherein the cooling passage has: a first cooling hole, one end of which is open to the front end side, and the inner diameter is the same along the blade height direction; and Two cooling holes, one end of which communicates with the other end of the first cooling hole without height difference, and the inner diameter increases toward the base end side, from one end of the first cooling hole to the first cooling hole and The length to the communicating position of the second cooling hole is 40% to 60% of the length from one end of the first cooling hole to the gas passage surface on the proximal end side. 2. The turbine blade according to claim 1, wherein the cooling passage has: a base end side cooling hole, one end of which is open to the base end side; and a cavity portion whose inner diameter is larger than that of the base end side cooling hole The inner diameter is large, and it communicates with the other end of the second cooling hole and the other end of the base end side cooling hole. The turbine blade according to claim 1 or 2, wherein the second cooling hole has a tapered shape whose inner diameter continuously increases toward the base end side. The turbine blade according to claim 2, wherein the turbine blade has a blade portion, a platform, and a blade root portion, and the cavity portion is provided on the platform. The turbine blade according to claim 2 or 4, wherein the inner diameter of the base end side cooling hole is larger than the maximum inner diameter of the second cooling hole. The turbine blade according to any one of claims 1 to 5, wherein the expansion rate of the inner diameter of the second cooling hole is greater than 100% and less than 200%. 7. A turbine blade provided with a plurality of cooling passages along the height direction of the blade at intervals in the front-rear direction of the blade, wherein the cooling passage includes: a first cooling passage having a direction from the front end side The base end side has a cooling hole whose inner diameter is increased at a first expansion rate; and a second cooling passage having a second expansion rate increasing from the front end side to the base end side with a constant inner diameter or a second expansion rate smaller than the first expansion rate Large cooling holes. 8. The turbine blade according to claim 7, wherein the turbine blade has a shape in which the width of the blade cross section is narrowed from a middle portion in the front-rear direction toward the front edge side and the rear edge side, and the second cooling passage Located at the front or rearmost side. The turbine blade according to claim 7 or 8, wherein the first expansion rate is an expansion rate of the inner diameter size, which is 100% to 250%. 10. The turbine blade according to claim 7 or 8, wherein the first expansion rate is a passage area expansion rate based on an inner diameter size, which is 100% to 306%. 11. The turbine blade according to any one of claims 7 to 10, wherein the interval between the first cooling passages adjacent to the middle portion in the front-rear direction of the blade is greater than that of other adjacent cooling passages. The interval is large. The turbine blade according to any one of claims 7 to 11, wherein an intermediate portion in the front-rear direction has a non-cooling portion without the cooling passage. The turbine blade according to any one of claims 7 to 12, wherein the first cooling passage has: a first cooling hole, one end of which is open to the tip side and inward along the blade height direction

The diameter is the same; and the second cooling hole, one end of which communicates with the other end of the first cooling hole, and the inner diameter increases toward the base end side. 14. The turbine blade according to claim 13, wherein a length from one end of the first cooling hole to a communication position between the first cooling hole and the second cooling hole is from the first cooling hole The length from one end of the cooling hole to the gas passage surface on the proximal side is 40% to 60%. The turbine blade according to claim 13 or 14, wherein the second cooling hole has a tapered shape whose inner diameter continuously increases toward the base end side. 16. The turbine blade according to any one of claims 7 to 15, wherein the cooling passage has: a base end side cooling hole, one end of which is open to the base end side; and a cavity part whose inner diameter is larger than the The base end side cooling hole has a large inner diameter and communicates with the other end of the first cooling passage or the other end of the second cooling passage and communicates with the other end of the base end side cooling hole. The turbine blade according to claim 16, wherein the turbine blade has a blade portion, a platform, and a blade root portion, and the cavity portion is provided on the platform. 18. A method for manufacturing a turbine blade, wherein the method for manufacturing the turbine blade includes the steps of forming a first cooling with a constant inner diameter along the height direction of the blade by electrolytic machining from the front end side of the turbine blade toward the base end side. Hole; and from the first cooling hole, in a manner that communicates with no height difference, while changing at least any one of the current value and the processing speed, the first cooling hole whose inner diameter increases along the height direction of the blade is formed by electrolytic machining Two cooling holes, the length from one end of the turbine blade in the first cooling hole to the communicating position of the first cooling hole and the second cooling hole is from the first cooling hole One end of the hole reaches 40% to 60% of the length from the gas passage surface on the base end side of the turbine blade. 19. The method of manufacturing a turbine blade according to claim 18, wherein the method of manufacturing the turbine blade includes the step of forming the edge by electrochemical machining from the base end side so that the current value and the machining speed are constant. The base end side cooling hole with the same inner diameter in the height direction of the blade; and at the end of the base end side cooling hole, the machining speed is slowed down or stopped, so that the inner diameter is larger than the inner diameter of the base end side cooling hole by electrolytic machining The cavity is large and communicates with the other end of the second cooling hole and the other end of the base end side cooling hole. 20. The method of manufacturing a turbine blade according to claim 18 or 19, wherein the step of forming the second cooling hole by electrochemical machining includes the step of forming by electrochemical machining so that the current value and the machining speed are constant. A basic second cooling hole with the same inner diameter along the blade height direction; and a second cooling hole with an increased inner diameter along the blade height direction by electrolytic machining while changing at least one of the current value and the machining speed. 21. The method of manufacturing a turbine blade according to any one of claims 18 to 20, wherein in the step of forming the second cooling hole by electrochemical machining, the current value is made constant at a predetermined value and the machining speed is changed , Thereby forming a second cooling hole whose inner diameter increases along the height direction of the blade. 22. A method of manufacturing a turbine blade, wherein the turbine blade is provided at intervals in the front-rear direction of the blade

A plurality of cooling passages along the height direction of the blade, wherein the manufacturing method of the turbine blade includes the steps of passing the turbine blade from the front end side to the base end side while adjusting at least one of the current value and the processing speed The electrochemical machining forms a first cooling passage whose inner diameter increases at a first expansion rate along the height direction of the blade; and while adjusting at least one of the current value and the machining speed from the front end side of the turbine blade toward the base end side, On one side, a second cooling passage having a constant inner diameter along the height direction of the blade or increased at a second expansion rate smaller than the first expansion rate is formed by electrolytic machining. 23. The method of manufacturing a turbine blade according to claim 22, wherein the first cooling passage has: a first cooling hole, one end of which is open to the front end side and having the same inner diameter along the height direction of the blade; and a second cooling hole One end of the cooling hole communicates with the other end of the first cooling hole without a height difference, and the inner diameter increases toward the base end side, starting from the end of the turbine blade on the front end side of the first cooling hole The length to the communication position of the first cooling hole and the second cooling hole is 40% of the length from one end of the first cooling hole to the gas passage surface on the base end side of the turbine blade ~60%. 24. The method of manufacturing a turbine blade according to claim 23, wherein when the second cooling hole is formed by electrochemical machining, the current value is constant at a predetermined value or more, and the machining speed is changed while the edge is formed by electrochemical machining. The second cooling hole whose inner diameter increases in the height direction of the blade. 25. A gas turbine, wherein the gas turbine includes: a compressor that compresses air; a combustor that mixes and burns compressed air compressed by the compressor and fuel; and a turbine that passes through the compressor The combustion gas generated by the combustor obtains rotational power, and the turbine has the turbine blade according to any one of claims 1 to 17.

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