Hydrogen-oxygen fuel-rich precombustion chamber for full flow staged combustion cycle engine

Abstract

The invention discloses a hydrogen-oxygen fuel-rich precombustion chamber used for a full flow staged combustion cycle engine system, and belongs to the field of structural design of a rocket engine. The hydrogen-oxygen fuel-rich precombustion chamber comprises an ignition tube 1, an oxygen cavity 2, an oxygen nozzle component 3, a hydrogen nozzle component 4, a hydrogen cavity 5, a choke plug 6 or an ignition tube (6), a connecting section 7, a body part 8, a threaded flange 9 and a contraction section 10. In the precombustion chamber, a hydrogen-oxygen pneumatic resonance igniter for combusting the hydrogen and oxygen is adopted, and the hydrogen and oxygen are supplied by a hydrogen ignition line and an oxygen ignition line respectively. The igniter has three mounting positions so as to form the following three ignition schemes: 1, ignition of the head; 2, ignition of the front part of the body part; and 3, ignition of the rear part of the body part. The three ignition schemes can form the hydrogen-oxygen-hydrogen combustion mode and are favorable for mixing combustion of propellants. The oxygen nozzle component 3 and the hydrogen nozzle component 4 can be detached and replaced and can meet different flow requirements. The length of the whole precombustion chamber is variable and is adjusted by increasing the number of the body part 8 or increasing the dimension of the body part 8. Due to the adoption of the threaded flange, the material is saved and the weight is lightened. The whole structural scheme of the precombustion chamber is favorable for deeply researching the ignition schemes, the hydrogen-oxygen-hydrogen combustion mode, the influence of a spoiler ring on fuel gas uniformity, and other problems.

Description

【Technical field】 [0001] The invention relates to a scheme design of a gas-hydrogen-oxygen-rich combustion pre-combustion chamber for a full-flow post-combustion cycle engine system, and belongs to the field of rocket engine structure design. 【Background technique】 [0002] The full-flow afterburning cycle system is a new type of rocket engine cycle system. It is the staged combustion technology with the highest combustion performance at present, and it is one of the important development directions of liquid rocket engine technology. In a full-flow afterburning cycle engine system, since all of its propellant will enter the rich pre-chamber and the oxygen-rich pre-chamber for combustion, its rich pre-chamber mixing ratio is very low. At such low mixing ratios, propellant blending and combustion is a big problem. [0003] The fuel-rich pre-chamber of the full-flow afterburning cycle engine has a mixing ratio far away from the equivalent mixing ratio, and it is difficult to ...

AI Technical Summary

Problems solved by technology

As described in the document L.Schoenman, "(Fuel / Oxidizer-Rich High-Pressure Preburners" NASA 3-21753, 1981, the head of the pre-chamber adopts the injection mode of multiple injection holes, but the injection hole arrangement is unreasonable In some cases, the local heat load of the injection panel is too large, and in some cases, the local ablation of the injection panel is serious, and even the entire head of the pre-combustion chamber is burned.

[0004] The traditional pre-combustion chamber design often uses welding to connect components. Although it can ensure the tightness between components and the strength requirements of the structure, it is easy to accumulate stress during welding and deform after cooling, such as the injection panel. deformation problem

To solve the deformation problem caused by accumulated stress, the method of increasing the thickness of the pre-chamber components is usually used, which will inevitably lead to an increase in the weight of the pre-chamber

It should be pointed out that the welding method is adopted, and the components of the pre-chamber cannot be disassembled or replaced, and can only be applied to a single working condition, and cannot meet the requirements of different flow rates, which is not conducive to the development of research work

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