Disturbance device used for combustion stability qualification tests

A combustion stability and identification test technology, which is applied in the field of disturbance devices for combustion stability identification tests, can solve the problems of debris damage, easy detonation by heat, unsatisfactory disturbance effects, etc., and achieve reliable excitation and detonation effects

Active Publication Date: 2017-01-18
BEIJING AEROSPACE PROPULSION INST
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Problems solved by technology

It solves the problem that the traditional explosive bomb disturbance method is easily detonated by heat and fragments are destructive, the installation problem of the pulse gun disturbance method on the regenerative cooling engine, and the unsatisfactory disturbance effect of the directional airflow method

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  • Disturbance device used for combustion stability qualification tests

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Embodiment Construction

[0025] The basic idea of ​​the present invention is: a disturbance device for combustion stability appraisal test, that is, a disturbance device suitable for dynamic combustion stability appraisal of cryogenic liquid rocket The combined structure of the inner shell. It can not only meet the requirements of high and low temperature extreme working environment temperature, but also achieve reliable detonation in the range of 35K ~ 3600K. Among them, the disturbance device must first be subjected to a low-temperature and low-pressure environment (35K, 0.5MPa) for 3s before detonation, and then a high-temperature environment (3600K, 10MPa) for 5s, and the longest working time is about 10s. It can also meet the requirements of the vibration environment, and the structure will not be damaged under the comprehensive vibration acceleration of about 200g; at the same time, it is guaranteed that the explosion fragments will not cause damage to the inner wall of the copper alloy of the t...

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Abstract

A disturbance device used for combustion stability qualification tests is suitable for the dynamic combustion stability qualification of a cryogenic liquid rocket engine. The disturbance device is of a combined structure composed of a composite heat insulation outer shell, a non-metal middle layer and a metal inner shell. The disturbance device can meet the temperature requirements of high-low temperature extreme work environment and achieve reliable detonation in the range of 35K-3600K; before detonation, the disturbance device needs to endure the low temperature and low pressure environment (35K, 0.5MPa) for 3s and then endure the high temperature environment (3600k, 10MPa) for 5s, and the total work time is about 10s. The disturbance device can further meet the requirements of vibration environment, and the structure is not damaged under the comprehensive vibration acceleration of about 200g; and it is guaranteed that explosion debris does not cause damage to the copper alloy inner wall of a test article.

Description

technical field [0001] The invention relates to a disturbance device for a combustion stability appraisal test, in particular to a disturbance device for a combustion stability appraisal test suitable for a low-temperature liquid rocket engine, and belongs to the technical field of rocket engine combustion. 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. O...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 丁兆波许晓勇孙纪国刘红珍张晋博潘刚马志瑜刘倩卢明潘亮
Owner BEIJING AEROSPACE PROPULSION INST
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