Test device for identifying combustion stability of liquid rocket engine
A combustion stability, liquid rocket technology, applied in rocket engine devices, machines/engines, jet propulsion devices, etc., can solve problems such as limitations, affect combustion sensitivity, and engine damage, and achieve the effect of overcoming structural limitations
Active Publication Date: 2021-07-27
BEIJING AEROSPACE PROPULSION INST
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Problems solved by technology
[0004] (1) Head-mounted type, only applicable to the bomb disturbance method, the orientation of the bomb may affect the combustion sensitivity, and the non-uniform heating or ablation of the shell may introduce directional effects
Most conventional structural designs are prone to thermal explosions and fragments that can cause damage to the engine
[0005] (2) Body-mounted type, limited by the wall structure of the body chamber, it is difficult to apply to the regenerative cooling engine
Method used
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[0022] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific implementation.
[0023] Such as figure 1 As shown, a liquid rocket engine combustion stability appraisal test device includes a combustion chamber head 1, a combustion chamber body 2, a transition ring 3, an upper connecting ring 4, a lower connecting ring 5, and a high-frequency speed-variable chamber pressure sensor 14, Perturbation device 15. Each part is connected by screw connection, flange or welding structure.
[0024] The combustion chamber head 1 is provided with an oxidant inlet 10; the transition ring 3 is placed between the combustion chamber head 1 and the combustion chamber body 2, and the transition ring 3 is respectively connected to the combustion chamber head 1 and the combustion chamber through the upper connection ring 4 and the lower connection ring 5. Combustion chamber body 2 one ends. The other end of the combustion chamb...
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A test device for identifying combustion stability of a liquid rocket engine comprises a combustion chamber head, a combustion chamber body, a transition ring, an upper connecting ring and a lower connecting ring. The combustion chamber head is provided with an oxidant inlet; the transition ring is arranged between the combustion chamber head and the combustion chamber body and connected with one end of the combustion chamber head and one end of the combustion chamber body through the upper connecting ring and the lower connecting ring respectively; a fuel-coolant inlet liquid collecting cavity is formed in the other end of the combustion chamber body, a fuel-coolant inlet is formed in the fuel-coolant inlet liquid collecting cavity, a fuel-coolant cooling channel is formed in the side wall of the combustion chamber body, and the fuel-coolant cooling channel communicates with an inner cavity of the lower connecting ring; and the transition ring is respectively communicated with the inner cavities of the upper connecting ring and the lower connecting ring through the fuel-coolant flow guide holes. According to the method, the influence of the regenerative cooling result on the combustion stability is truly reflected, and the requirements of reliable excitation in different stages of starting, stage switching and shutdown can be met.
Description
technical field [0001] The invention relates to a test device for evaluating the combustion stability of a liquid rocket engine. Background technique [0002] The occurrence of unstable combustion of liquid rocket engines is very random. In general engine tests, even if combustion instability does not occur many times, it is still impossible to confirm that its dynamic stability meets the requirements. For example, a dinitrogen tetroxide / hydrazine-50 engine has 9 high-frequency unstable combustions in 1800 test runs, and the probability of instability is 0.5%. The stability level of this engine cannot meet the requirements of use. Dynamic combustion stability qualification test is an effective method to determine engine combustion stability margin and boundary with as few test times as possible. One of the key technologies is the design and realization of the identification test device. [0003] Currently, there are two commonly used test device design structures for dynam...
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IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 丁兆波孙纪国岳文龙龚杰峰刘倩牛旭东杜宁陶瑞峰宋德坤
Owner BEIJING AEROSPACE PROPULSION INST