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

A technology of turbine blades and cooling structures, applied in the directions of blade support elements, engine elements, machines/engines, etc., can solve the problems of affecting the cooling effect of turbine blades, reducing the cooling efficiency of the outer air film, and the large air flow rate of air film cooling, etc. To achieve the effect of improving the wall attachment effect, improving the cooling effect and improving the cooling efficiency

Inactive Publication Date: 2019-05-28
SHANGHAI JIAO TONG UNIV
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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 wa

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

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Embodiment Construction

[0024] The following describes a preferred embodiment of the present invention with reference to the accompanying drawings to make its technical content clearer and easier to understand. The present invention can be embodied in many different forms of embodiments, and the protection scope of the present invention is not limited to the embodiments mentioned herein.

[0025] In the drawings, components with the same structure are denoted by the same numerals, and components with similar structures or functions are denoted by similar numerals. The size and thickness of each component shown in the drawings are shown arbitrarily, and the present invention does not limit the size and thickness of each component. In order to make the illustration clearer, the thickness of parts is appropriately exaggerated in some places in the drawings.

[0026] Such as figure 1 As shown, the double wall cooling structure of the turbine blade with transverse air holes in this embodiment includes t...

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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...

Claims

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Application Information

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IPC IPC(8): F01D5/18
Inventor 饶宇刘宇阳陈冠江
Owner SHANGHAI JIAO TONG UNIV
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