Liquid rocket thrust chamber test run inner wall temperature calculation method and calculation equipment

A technology of liquid rockets and calculation methods, applied in design optimization/simulation, special data processing applications, etc., can solve the problems of incomparability and the inability to obtain the wall temperature of the thrust chamber, and achieve the effect of improving the probability of success and facilitating structural parameters.

Pending Publication Date: 2020-11-17
江苏深蓝航天有限公司
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Problems solved by technology

However, only the temperature of the outer wall can be obtained from the experimental results, and the temperature of the inner wall of the thrust cannot be obtained from the existing test r

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  • Liquid rocket thrust chamber test run inner wall temperature calculation method and calculation equipment
  • Liquid rocket thrust chamber test run inner wall temperature calculation method and calculation equipment
  • Liquid rocket thrust chamber test run inner wall temperature calculation method and calculation equipment

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[0033] The present disclosure will be further described below with reference to the drawings and embodiments. It will be appreciated that the specific embodiments described herein are for explanation of the related content, and is not limited to the present disclosure. It will also be noted that only the portions associated with the present disclosure are shown in the drawings for ease of description.

[0034] It should be noted that the features of the present disclosure and the features in the present disclosure may be combined with each other in the case of an unable conflict. The following embodiment with reference to accompanying drawings and embodiments of the present disclosure will be described in detail.

[0035] See figure 2 A simplified schematic diagram of the heat transfer structures shown thrust chamber, and image 3 An enlarged schematic view of the structure shown. Thrust chamber sidewall surrounding the thrust chamber into the cylindrical axis extending from the in...

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Abstract

The invention provides a liquid rocket thrust chamber test run inner wall temperature calculation method and calculation equipment. The calculation method comprises the steps that distribution data ofan outer wall temperature measurement value of a thrust chamber along the axis of the thrust chamber are acquired; the thrust chamber is divided into n temperature sections in the axis direction of the thrust chamber, wherein n is larger than or equal to 2; the outer wall temperature measurement value i of the ith temperature section is greater than or equal to 1 and less than or equal to n; thevalue of i is gradually increased in the direction from the upstream of a cooling flow path to the downstream of the cooling flow path; according to a heat transfer function relationship, calculationis conducted to obtain the heat transfer amount of the inner wall of the ith temperature section when the calculated value of the outer wall temperature of the ith temperature section is equal to themeasured value of the outer wall temperature of the ith temperature section, and calculation is conducted to obtain the cooling outlet temperature Tci and the inner wall temperature of the ith temperature section corresponding to the heat transfer amount of the inner wall of the ith temperature section. According to the calculation method disclosed by the invention, the thrust chamber inner wall temperature can be obtained according to a test run experiment result.

Description

technical field [0001] The present disclosure relates to the technical field of liquid rocket thrust chamber test run, and in particular to a calculation method and computing equipment for the inner wall temperature of liquid rocket thrust chamber test run. Background technique [0002] In the thrust chamber of a liquid rocket engine, the propellant components are burned at high temperature (3000-4000K) and high pressure (5-20MPa or higher), and the high-temperature and high-pressure gas flow rate is high (throat flow rate is as high as 1000-1500m / s) , the heat flux passing through the wall of the thrust chamber is high (10~160MW / m 2 ), therefore, thermal protection is an important consideration in thrust chamber design. In order to ensure the thermal strength and structural stability of the thrust chamber structure, thermal protection measures need to be taken, which can usually be divided into external cooling (regenerative cooling, discharge cooling, radiation cooling), ...

Claims

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Application Information

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IPC IPC(8): G06F30/20
CPCG06F30/20
Inventor 不公告发明人
Owner 江苏深蓝航天有限公司
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