A double-walled stator turbine blade with corrugated impingement plates

Abstract

A double-walled stator turbine blade adopting a corrugated impact plate, including an impact plate, a target plate and a spoiler column, the impact plate and the target plate form a gap between the plates, the spoiler column is located in the gap between the plates, and the impact plate There are impact holes, and air film holes are set on the target plate; the impact plate adopts a corrugated impact plate; the ratio of the distance between the gaps between the plates to the thickness of the impact plate is (4~6):1; the diameter of the spoiler column and the diameter of the impact hole The ratio is (0.5~0.8):1; the ratio of target plate thickness to impact plate thickness is (1~2):1; the ratio of gas film hole diameter to impact hole diameter is (0.4~0.6):1; the corrugated structure is When the corrugation is V-shaped or semi-circular arc, the impact hole and the corrugated structure of the impact plate are set as a ring-shaped plate structure, and the ratio of its diameter to the diameter of the impact hole is (4-6): 1; when the corrugation structure is V-shaped or trapezoidal corrugation, The corrugation angle is 30°~60°; the ratio of the peak / valley distance of the V-shaped corrugation, the length of the bottom edge of the trapezoidal corrugation to the aperture of the impact hole is (1~2):1; the arc diameter of the semicircular arc corrugation and the impact hole The ratio of aperture is (2~3):1.

Description

technical field [0001] The invention belongs to the technical field of aero-engine blade design, in particular to a double-walled stator turbine blade using a corrugated impact plate. Background technique [0002] For the domestic military aircraft that have been put into production and the domestic civil passenger aircraft that are about to be put into production, the development of matching engines has been slow, which seriously restricts the achievement of national defense deterrence and economic benefits of these high-performance aircraft. [0003] As the turbine components of aero-engines need to work in the harsh environment of high temperature, high pressure and high speed, how to carry out the cooling design of turbine blades to ensure the safe and reliable operation of aero-engines has become an important issue in the development of aero-engines. [0004] When the aircraft is in the stage of take-off, landing or passing through volcanic ash clouds, the aero-engine w...

AI Technical Summary

Problems solved by technology

At present, in order to improve the dust removal ability of the stator turbine blades, technicians have considered adding a screen to the cooling pipeline of the aero-engine to intercept the dust, but the increase of the screen will lead to a rapid increase in the flow resistance of the cold air, which in turn will lead to a decrease in the flow of cold air. Insufficient, but affects the cooling effect of the blade

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