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Multifunctional test device for realizing integrated verification of combustion and heat transfer technologies

A test device and technology integration technology, applied in the field of multi-functional test devices, can solve problems such as inability to give accurate predictions

Active Publication Date: 2020-06-19
BEIJING AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the deep coupling of the combustion heat transfer process, the current theoretical analysis and numerical calculation cannot give accurate predictions, and it is also necessary to use thermal test measurement and evaluation

Method used

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  • Multifunctional test device for realizing integrated verification of combustion and heat transfer technologies
  • Multifunctional test device for realizing integrated verification of combustion and heat transfer technologies
  • Multifunctional test device for realizing integrated verification of combustion and heat transfer technologies

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Embodiment Construction

[0023] The present invention proposes a composite function test piece of combustion and heat transfer, such as figure 1 As shown, the injector 1 and the combustion chamber 2 are included, and the injector 1 and the combustion chamber 2 are connected by bolts.

[0024] The injector 1 is composed of an oxidizer chamber and a fuel chamber, the oxidizer chamber is connected to the oxidizer inlet 3, the fuel chamber is connected to the fuel inlet 4, and the ignition source inlet 5 is used to communicate the oxidizer chamber and the fuel chamber; the surface edge of the injector 1 is processed There are 8 vocal chambers. Such as figure 2 As shown, the injector 1 is provided with three rings of nozzles from the center to the outside in the circumferential direction, the innermost ring is composed of a main nozzle 10 located at the center of the injector 1, and the second ring is composed of several main nozzles 10 , the half circle of the third circle is the side area nozzle 6, an...

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Abstract

A multifunctional test device for realizing integrated verification of combustion and heat transfer technologies comprises an injector and a combustion chamber which are connected through a bolt. Three circles of nozzles are sequentially arranged on the injector from the center to the outside in the circumferential direction. The innermost ring is composed of a main nozzle located in the center ofthe injector, the second ring is composed of a plurality of main nozzles, the half ring of the third ring is a border area nozzle, the other half ring is a partition plate nozzle and a main nozzle which are arranged at an interval, and the position of the partition plate nozzle ensures that each partition plate nozzle is surrounded by the three main nozzles. Temperature and pressure measuring points are arranged at different depths of the acoustic cavity in the circumferential direction of the combustion chamber. The positions of the measuring points are matched with the positions of the mainnozzle, the border area nozzle and the partition plate nozzle on the injector, so that the thermal protection performance of the partition plate nozzle is assessed in one test, the temperature distribution in the acoustic cavity is obtained, and meanwhile, the thermal compatibility effects of the border area nozzle, the main nozzle and the chamber wall are compared.

Description

technical field [0001] The invention relates to a multifunctional test device for realizing integrated verification of combustion and heat transfer technology, which belongs to the technical field of liquid rocket engine test. Background technique [0002] Combustion instability has always been a worldwide problem that plagues the development of liquid rocket engine technology. In the development process of almost every high-thrust liquid rocket engine, the problem of unstable combustion will be encountered, especially high-frequency unstable combustion is the most harmful, which may lead to instantaneous ablation of engine components or structural damage. The mechanism of high-frequency unstable combustion of liquid rocket engines has been studied for decades, but no effective general guidelines for injector / combustion chamber design have been formed so far. Troubleshooting engine unstable combustion often requires extensive and expensive full-scale test runs, often requir...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/14G01M15/02
CPCG01M15/14G01M15/02
Inventor 丁兆波孙纪国张晋博刘倩许晓勇
Owner BEIJING AEROSPACE PROPULSION INST