Manufacturing method for airspace engine combustion chamber inner wall blank

Abstract

The invention discloses a manufacturing method for an airspace engine combustion chamber inner wall blank. The manufacturing method comprises the steps that S1, Cu, Cr and Zr materials are weighed; S2, the materials obtained in the step S1 is subjected to vacuum induction melting, and an alloy solution is obtained; S3, the alloy solution obtained in the step S2 is poured to obtain an alloy cast ingot; S4, the alloy cast ingot obtained in the step S3 is subjected to forging, upsetting, drawing-out and punching treatment, and a combustion chamber inner wall blank is obtained; S5, the combustion chamber inner wall blank obtained in the step S4 is subjected to solid heat melting treatment; S6, the combustion chamber inner wall blank treated in the step S5 is subjected to upsetting and secondary chambering treatment; S7, the treated combustion chamber inner wall blank is subjected to rough turning, aging heat treatment, performance detection and finish turning treatment, and the combustion chamber inner wall blank is obtained; and S8, size detection and appearance detection are conducted on the combustion chamber inner wall blank obtained in the step S7, and packaging is conducted. The manufacturing method for the airspace engine combustion chamber inner wall blank is reasonable in process design, the obtained combustion chamber inner wall blank can meet the high-strength and high-heat-dissipation requirements of an airspace engine combustion chamber, and the manufacturing method is suitable for large-scale popularization.

Description

technical field [0001] The invention relates to the technical field of manufacturing a combustion chamber of an aerospace engine, in particular to a method for manufacturing an inner wall blank of a combustion engine of an aerospace engine. Background technique [0002] Liquid hydrogen and liquid oxygen engines are being widely used as the power of launch vehicles. The inner wall of this liquid rocket engine is subjected to high temperature, high pressure, and high-speed airflow, and is subjected to high thermal stress caused by pressure loads and temperature gradients on both sides of the inner wall. The reason why copper alloy and copper-based composite materials can be used as inner wall material for rocket engine parts is that it has higher thermal conductivity than other engineering materials. The engine combustion chamber is the core component to ensure the normal operation of the rocket, and the working conditions are very harsh. If the engine is overheated during us...

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Problems solved by technology

[0003] At present, the most common blank material for the inner wall of aerospace engine combustion is T2 copper. The electrical conductivity of this material can reach 100% IACS, and the thermal conductivity can reach 380W/(m·k). Typical values ​​are: 200MPa, 80MPa and 35%. The softening temperature is only 330°C. The strength and softening temperature are far lower than the working environment of aerospace engines. It is difficult to adapt to the new generation o

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