Low-cost inside diameter-variable combustion chamber and design and test method thereof

Abstract

The invention relates to a low-cost inside diameter-variable combustion chamber and a design and test method thereof, which belongs to the field of a combustion chamber structural design method. The combustion chamber comprises a head part, a body part and a spray pipe part. The combustion chamber adopts a heat containing type structure and is made of a pure copper material with high thermal conductivity, and the body part is divided into an inner part and an outer part, i. e. an inner lining and an outer sleeve. The method comprises the following steps of: firstly obtaining the size and the number of the outer sleeve by adopting thermal analysis computation according to the requirement of inside diameter variation; and matching one outer sleeve with a plurality of inner linings to achieve an inside diameter-variable test. The inner lining and the outer sleeve are matched in the aspect of processing, and a gap is between the inner lining and the outer sleeve ensured through a tolerance, thereby saving the material of the combustion chamber, lowering the test cost and shortening the test cycle of the combustion chamber.

Description

【Technical field】 [0001] The invention relates to a low-cost variable internal diameter combustion chamber and its design and test method. The invention particularly relates to a combustion chamber with a variable inner diameter applied to a liquid rocket engine and its design and test method. 【Background technique】 [0002] In the development process of rocket engine thrust chamber, especially in the development process of the injector as the main component of the thrust chamber, in a large number of initial research stages, in order to fully carry out experimental research, it is often necessary to change the diameter of the combustion chamber. Obtain data under different working conditions. [0003] In the combustion test research on the ground, two types of combustion chamber structures are generally used, namely heat capacity type and water cooling type. Compared with the regenerative cooling method, the heat capacity structure has the advantages of simple structure, ...

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Problems solved by technology

In order to have good thermal protection in the high-temperature and high-pressure environment of the rocket engine, the parts are designed to be large in size and heavy in weight, but when a large number is used, the cost will increase linearly, and the weight is not easy to replace

2. Only one heat-capacity combustion chamber is used, and the test progress is arranged according to the test needs: first conduct the test of the small-sized inner diameter, and then expand the inner diameter to carry out the experimental research of the large-sized inner diameter. This method uses only one combustion chamber , the cost is the lowest; but the exchange test between different inner diameters cannot be flexibly carried out. For example, in the experimental research, it is often necessary to conduct a small-scale test after a large-scale inner-diameter test, so this method is not applicable. It strictly limits the process used; and this method needs to continuously modify the inner diameter, which will inevitably increase the time cost

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