Preparation method for rhenium-iridium combustion chamber
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A combustion chamber, rhenium-iridium technology, which is applied in the field of preparation of rhenium-iridium combustion chambers to achieve the effects of ensuring working life, prolonging flight life and increasing range
Active Publication Date: 2016-10-12
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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[0004] With the further development of aircraft, higher requirements are placed on engine performance, and the operating temperature reaches above 1800°C. The above-mentioned niobium alloy and coating material system cannot meet the demand. Therefore, all countries are developing a new generation of material system.
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[0040] Such as figure 1 Shown is the flow chart of the preparation method of the rhenium-iridium combustion chamber of the present invention, and the preparation method of the rhenium-iridium combustion chamber of the present invention specifically includes the following steps:
[0041] Step (1), the rhenium combustion chamber substrate 5 is prepared by powder metallurgy forming process, and in order to realize the subsequent welding process, niobium alloy rings need to be formed at the inlet ends of both ends of the rhenium combustion chamber to realize integral molding of rhenium and niobium, and strengthen through subsequent heat treatment Rhenium and niobium diffuse to improve the interface bonding strength. The material of the sheath 4 used in the powder metallurgy process is low carbon steel. The core mold 3 used in the powder metallurgy process is made of niobium-tungsten alloy, and a bevel locking structure is designed to enhance the connection with rhenium.
[0042]...
Embodiment 1
[0054] (1), using powder metallurgy technology net shape rhenium combustion chamber substrate, using figure 2 For the mold shown, the forming process conditions are: temperature 1300°C, pressure 150MPa, holding time 5h. The subsequent heat treatment process is characterized by a vacuum environment ≤ 1×10 -3 Pa, temperature 1550°C, holding time 3h.
[0055] The size of the combustion chamber is machined in place by machining. The total length of the combustion chamber is 130mm, the maximum outer diameter is Ф70mm, the straight section of the inner diameter is Ф45mm, and the throat diameter is Ф20mm.
[0056] (2), use the mixed acid of the sulfuric acid of 15% (mass concentration), 20% (mass concentration) hydrochloric acid to clean, clean with distilled water then, dry;
[0057] (3) Using the arc deposition process, the iridium target material used for preparing the iridium coating on the inner surface of the rhenium combustion chamber substrate 5 is in the shape of a trunca...
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Abstract
The invention relates to a preparation method for a rhenium-iridium combustion chamber. The preparation method comprises the following steps: preparing a rhenium combustion chamber by adopting a powder metallurgy near-net shape forming technology; preparing iridium coatings at inner and outer surfaces of the rhenium combustion chamber by adopting an electric-arc deposition technology; preparing a platinum-rhodium ring by adopting a spinning technology and assembling the platinum-rhodium ring on the inner wall surface of the combustion chamber; and preparing a metal oxide high-radiation coating on the outer surface of the combustion chamber by adopting a plasma spraying technology. According to the preparation method, by virtue of an optimized design of process methods and process conditions at different stages of a preparation process, the prepared rhenium-iridium combustion chamber is applied to an engine, so that a use and working environment of the engine can be remarkably increased, specific impulse can be improved for the engine, and technical support is provided for prolonging flight life of an aircraft, increasing effective load of the aircraft or increasing range of the aircraft.
Description
technical field [0001] The invention relates to a preparation method of a rhenium-iridium combustion chamber, in particular to a preparation method of a rhenium-iridium combustion chamber applied to an engine, and belongs to the technical field of rocket engine production and manufacture. Background technique [0002] Small-thrust dual-component liquid rocket engines are mainly used in the attitude and orbit control of space vehicles and strategic and tactical weapons. The fuel combustion temperature in the thrust chamber can reach 2700°C. After adopting the liquid film active cooling technology on the inner wall, the wall temperature is still higher than 1000°C Therefore, in order to ensure the high-temperature strength requirements of the engine thrust chamber, high-temperature refractory metals (Nb, Ta, W, Mo, Re, and platinum, etc.) must be used as body materials, but these materials have poor high-temperature oxidation resistance, such as Niobium alloys will undergo "pe...
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