Turbine blade of gas turbine engine with V-shaped airflow differential plates

Abstract

The invention discloses a turbine blade of a gas turbine engine with V-shaped airflow differential plates. The turbine blade comprises a blade body and a tenon, wherein the blade body is arranged on the end wall side of the tenon; the blade body comprises a blade front edge, a blade basin, a blade body middle chord area, a blade tail edge, a blade top and a blade back; a plurality of cooling cavities are formed inside the blade body; partition plates are arranged among the plurality of cooling cavities; a V-shaped airflow differential plate is arranged in each cooling cavity; air film holes are formed in the surface of the blade body; at least one blade top dust removal hole is formed in the blade top; cold air inlets are formed in an extension root of the tenon; cooling passages corresponding to the two cold air inlets, close to the front edge of the blade, of the extension root are combined into a flow path to communicate with the cooling cavities; and cooling passages correspondingto the two cold air inlets close to the tail edge of the blade are combined into a flow path to communicate with the cooling cavities. Therefore, the V-shaped airflow differential plates are fixed onto two adjacent partition plates, the structural intensity of the blade body can be favorably enhanced, and the blade can be kept at a low temperature level.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a turbine blade of a gas turbine engine with a V-shaped airflow differential plate. Background technique [0002] Gas turbine is one of the core components of aero-engine, its performance directly affects the safety and economy of aero-engine. In order to pursue high thrust-to-weight ratio and high efficiency of aero-engines, the inlet temperature of gas turbines is gradually rising, and a breakthrough in gas turbine heat transfer technology is urgently needed. [0003] Turbine blade cooling technology research is generally divided into external heat transfer, internal heat transfer, film cooling, coating technology research, turbine blade heat transfer design methods, and optimization design methods. The heat transfer of the outer wall of the turbine, that is, the distribution of the heat load on the gas side surface of the turbine blade is the main research object of the desig...

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Problems solved by technology

Therefore, its applicable range is limited, and it is generally only arranged in areas with high heat load and low strength requirements such as the leading edge of the moving blade and the middle of the chord length of the stationary blade.

Disturbance cooling generally refers to the arrangement of spoiler ribs and spoiler columns in the inner passage of the blade, which enhances heat transfer by increasing the turbulence of the flow and reducing the thickness of the heat transfer boundary layer on the wall, but the effect of turbulence cooling has a lot of room for improvement.

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