Turbine blade compound cooling structure with sunken internal pin

Abstract

The invention relates to a turbine blade compound cooling structure with sunken internal pins, comprising a blade passage and a pin; the cooling structure is characterized by further comprising a sunken part, pins are arranged in the blade passage, the blade passage has at least one internal wall surface provided with sunken parts; the sunken parts are arranged in the blade passage in a dislocation way; the sunken parts are of semisphere or part of the semisphere or cone with top part cut off. In the invention, the pins are respectively connected with two wall surfaces in the blade passage, thus on one hand increasing heat exchange area of cooling fluid and on the other hand consolidating the passage; the sunken parts cause the flowing through to generate vortex, thus improving convection and heat exchange effect between the air stream and wall surface of the blade passage and pin surface; meanwhile, when the air stream flows through the sunken parts, direct impact on the pins by the lower reaches of the fluid body is reduced, thus avoiding increase of flow losses while increasing heat exchange area.

Description

technical field [0001] The invention relates to an internal cooling device for a turbine blade of a gas turbine, in particular to a composite cooling structure with pin-fin recesses inside the turbine blade. Background technique [0002] It is a major trend in the development of modern gas turbines to increase the gas temperature before the turbine, thereby improving the total efficiency of gas turbine energy conversion. The temperature of the gas before the turbine of a modern gas turbine has exceeded the melting temperature of the materials used. Therefore, with the further increase of the gas temperature at the turbine inlet, more efficient and advanced cooling technologies are urgently needed to ensure the temperature level in high-temperature components such as the turbine blades of the gas turbine, and Control the temperature gradient within a reasonable range to ensure normal operation and a sufficient life cycle. In addition, the enhanced cooling technology means th...

AI Technical Summary

Problems solved by technology

However, due to the increased wall thickness, the cooling efficiency of the blades is reduced and the overall efficiency of the gas turbine is thus reduced

[0004] On the other hand, the pin-fin array structure is usually used inside the trailing edge of the existing turbine blades to enhance the convective heat transfer performance. Although the pin-fins can significantly improve the convective heat transfer performance of the fluid, it will bring great resistance to the flow.

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