Connecting structure and exhaust system of aeroengine including the connecting structure

Abstract

The invention relates to a connecting structure which is used for connecting parts with different thermal expansion coefficients. The connecting structure comprises a first part, a second part, a sliding block and an axial connecting piece, wherein the thermal expansion coefficients of the first part and the second part are different; the sliding block comprises an inclined surface and is slidablyarranged between the first part and the second part; the first part is provided with multiple guide slots; the inclined surface is in tight contact with the side surfaces of the guide slots; the axial connecting piece is used for connecting the first part, the sliding block and the second part; a dip angle of the inclined surface is larger than a friction angle; and when the connecting structureis heated, the guide slots and the sliding block slide relatively, so that the component of the thermal expansion sliding amount of the sliding block in the axial direction is equal to the thermal deformation amount of the axial connecting piece. Correspondingly, the invention provides an exhaust system of an aero-engine comprising the connecting structure. The exhaust system of the aero-engine comprising the connecting structure has the advantages of stable structure, reliability and the like.

Description

technical field [0001] The invention relates to a connection structure, in particular to a connection structure for connecting components with different thermal expansion coefficients. Background technique [0002] The exhaust system of the aero-engine discharges the gas exhausted by the turbine into the atmosphere at a certain speed and in the required direction to generate thrust. Such as figure 1 As shown, the exhaust system of an aero-engine mainly includes an exhaust cone 46 and an exhaust nozzle 42 to control the direction of turbine exhaust. An exhaust cone 46, which is connected to the engine turbine case, controls the inboard edge of the turbine exhaust flow. The exhaust cone 46 is fixed in the exhaust nozzle 42 by the rectifying support plate, and a diffuse channel is formed between the exhaust cone 46 and the exhaust nozzle 42 to reduce the gas velocity and reduce flow friction loss. Such as figure 2 , the exhaust cone 46 is connected to the turbine casing 10...

AI Technical Summary

Problems solved by technology

[0007] However, the inventors realized that although this clearance fit structure can effectively release the thermal mismatch stress when heated, the diameter of the top of the screw must be slightly smaller than the diameter of the inner surface of the sleeve to form an effective clearance in actual machining. Cooperate, the machining accuracy of the inner surface of the shaft sleeve is very high

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