A New Type of Cooling Structure of Multi-inclined Orifice Plate Ellipsoid Pendulum for Aerospace Engine

Abstract

The invention discloses a novel cooling structure of an ellipsoidal pendulum with multi-slanted orifices for an aerospace engine. The cooling slant holes are connected with an air-inducing channel, which extends to the inner side of the combustion chamber flame tube and communicates with a spherical axis. The ellipsoid is located at the Between the front and rear adjacent cooling inclined holes on the inner side of the flame tube wall of the combustion chamber, the long axis of the ellipsoid is forward and backward. The ellipsoid is provided with an inner cavity, and the ball axis is located in the inner cavity of the ellipsoid. The exhaust passage of the inner chamber is provided with a hole on the ball shaft, the ellipsoid can rotate around the ball shaft, and the ball shaft is connected with the ellipsoid through a spring. The present invention can ensure the normal delivery of cold air to the downstream and enhance the cooling effect when the amount of cooling gas is not much. When the amount of cooling gas is large, it can avoid the problem that the downstream cannot stabilize the air film coverage due to the jet flow falling off the wall when the wind speed of blowing cold air is relatively high. question.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a novel multi-slope hole plate ellipsoidal pendulum cooling structure for aerospace engines. Background technique [0002] During the development of aviation gas turbine engines and gas turbines, in order to improve their cycle efficiency, the boost ratio of the compressor and the gas temperature at the inlet of the turbine have been continuously increased. At present, the thrust-to-weight ratio of an engine with a thrust-to-weight ratio of 10 has reached a compressor pressure ratio of 30, and the gas temperature at the turbine inlet has reached 2000K, which exceeds the temperature resistance limit of aviation materials, and puts forward higher requirements for the cooling of the combustion chamber flame tube wall and turbine blades , so the development of high-efficiency cooling technology has become one of the hot research issues in the field of aviation. Air film cooling is t...

AI Technical Summary

Problems solved by technology

It is mainly based on the flat plate model. The traditional circular hole air film jet will form a kidney-shaped vortex pair downstream of the hole, which will intensify the mixing of cold air and hot air, resulting in a decrease in cooling performance.

And when the blowing rate is relatively high, due to the jet flow falling off the wall, the downstream cannot stably cover the air film, and it is also difficult to achieve a uniform cooling effect in the circumferential direction

Moreover, it is difficult to control the intake air volume of the cold air, and it is easy to cause waste of cold air if the intake ratio is too large, and the cooling effect is not good if the intake ratio is too small.

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