Turbine blade double-layer wall cooling structure with transverse vent holes

Abstract

The invention discloses a turbine blade double-layer wall cooling structure with transverse vent holes, and relates to the field of turbine blade cooling structures. The turbine blade double-layer wall cooling structure is characterized by comprising an outer-layer wall, an inner-layer wall, short partitions and long partitions; and air film holes are formed in the outer-layer wall of a turbine blade, jet holes are formed in the inner-layer wall of the turbine blade, the short partitions are connected between the outer-layer wall and the inner-layer wall to divide the space between the outer-layer wall and the inner-layer wall into at least two cooling units, , the transverse vent holes are formed in the short partitions, and a cavity defined by the inner-layer wall is divided into at least two air inflow cavities by the long partitions. The wall attachment of a cooling air film is improved, and the cooling efficiency of the air film is improved; the flow of cooling gas of the air filmholes in the upstream and downstream portions of the turbine blade is balanced, the turbine blade is more uniformly cooled, and meanwhile the cooling effect of the tail edge of the turbine blade is improved; and the heat exchange area is increased, the weight of the turbine blade is reduced, and the turbine blade double-layer wall cooling structure is easy to machine and achieve.

Description

technical field [0001] The invention relates to the field of cooling structures of turbine blades, in particular to a double-walled cooling structure of turbine blades with transverse air holes. Background technique [0002] The development of modern gas turbines pursues higher thermal efficiency, and increasing the gas temperature before the turbine is an important technical means. To solve this problem, in addition to the continuous development of new materials and new processes, one of the decisive factors is to use advanced and efficient enhanced cooling technology for turbine blades to ensure reliable work of turbine blades. On the other hand, in order to meet the fatigue strength and Lifetime requirements require that the internal cooling of the turbine blades provide as uniform a heat transfer performance as possible. The cooling technology of turbine blades is mainly carried out in two aspects: one is to strengthen the disturbance of the cooling air inside the turbi...

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Problems solved by technology

[0005] In view of the above-mentioned defects in the prior art, the technical problem to be solved by the present invention is that in the existing turbine blade double-wall cooling structure scheme, the air film cooling air velocity is relatively high, so that the cooling air flow is separated from the outer wall surface of the blade, reducing the outer surface of the blade. The air film cooling efficiency reduces the aerodynamic efficiency of the turbine; the uneven pressure of the upper and lower air film holes on the outer wall leads to uneven cooling, which affects the overall cooling effect of the turbine blades

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