Forming method for airspace engine spray tube part

Abstract

The invention provides a forming method for an airspace engine spray tube part. The method comprises the following steps: step I, cutting out a plurality of coaxial circular table rings on a plate; step II, performing spinning and shape-correcting on the circular table rings with too great dimensions or similar dimensions; step III, turning out circular ring surfaces which are welded with one another at large hole ends and small hole ends of all circular table rings; and step IV, sequentially welding the circular table rings into an integer according to the dimensions of the large hole ends from small to big or from big to small. The forming method for the airspace engine spray tube part provided by the invention has the advantages of being simple in process, not limited by an axle diameter ratio and a dimension, being capable of detecting and measuring the process, capable of being integrally formed, being high in production quality stability, being suitable for large-batch automaticproduction, and the like.

Description

technical field [0001] The invention relates to the field of aerospace engine nozzles, and in particular to a molding method of aerospace engine nozzle parts. Background technique [0002] The thrust chamber is the part responsible for the mixed combustion of fuel in the liquid rocket engine to generate high-temperature and high-pressure gas, which is accelerated and discharged through the throat to obtain reverse thrust. The thrust chamber is generally a Laval profile structure consisting of a cylindrical section, a contracting section and an expanding section. In order to withstand the high temperature of the gas, the nozzle generally adopts regenerative cooling technology, which is composed of the inner wall and the outer wall of the milling groove. At the same time, because the gas temperature is as high as 3500K and the heat exchange power of the wall surface can reach 100 megawatts, the inner wall material of the thrust chamber is mostly made of copper alloy. [0003...

AI Technical Summary

Problems solved by technology

Among them, the specific method of machining rods, forging rings and flat plates is: take a bar, forging ring, and plate for material reduction processing, obtain the required nozzle parts, and then carry out tailor welding. The disadvantages of this method are: The material utilization rate is low, the amount of machining is huge, and at the same time, it is difficult to process large-sized nozzle parts due to the limitation of the thickness of the material

The specific method of spinning the flat plate and the cylinder is: the forming process of forcibly spinning the flat or barrel-shaped parts onto the mold mold. The disadvantages of this method are: 1. For large diameter and large shaft-to-diameter ratio Parts are difficult to process, and defects such as cracks are prone to be scrapped; 2. The manufacturing process requires a series of spinning tires such as the first pass, the second pass, and the third pass, especially when the diameter is large. The size of the tire will be very large; 3. The spinning process is usually accompanied by heating, heat treatment and other heating processes during hot spinning, which changes the properties of raw materials

The disadvantages of this precaution are: 1. The process is relatively complicated; 2. The requirements for equipment are high, requiring large-scale forming tires and stamping equipment, and welds are prone to problems during the stamping process; 3. The product is deformed and the product consistency is poor; 3. It can only process single-shrinkage or single-expansion structural parts, and it is impossible to obtain parts with both shrinkage and expansion sections at one time

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