Supersonic flow mixing device based on partition plate rear edge jet flow disturbance

A technology of supersonic flow and mixing device, which is applied in rocket engine devices, jet propulsion devices, machines/engines, etc., can solve problems such as unsatisfactory effects, and achieve the effects of simple structure, strong engineering applicability, and controllable jet flow

Active Publication Date: 2021-07-16
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

However, considering the uncontrollable factors of background noise in supersonic flow, the effect of this method is not ideal in practical engineering applications

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  • Supersonic flow mixing device based on partition plate rear edge jet flow disturbance
  • Supersonic flow mixing device based on partition plate rear edge jet flow disturbance

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[0017] In order to make the purpose, technical solution and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present application, and are not intended to limit the present application.

[0018] The supersonic flow mixing device based on the jet disturbance at the trailing edge of the dividing plate provided by this application can be applied in the mixing chamber of rocket-based combined cycle engine ejection mode. Among them, the first supersonic airflow is compressed supersonic inflow air entering from the intake port, and the second supersonic airflow is the supersonic fuel-rich gas that is expanded and accelerated by the rocket combustion chamber through the tail nozzle. Part of it is jetted out at supersonic speed from the jet hole on the rear edge of...

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Abstract

The invention relates to a supersonic flow mixing device based on partition plate rear edge jet flow disturbance. The device comprises a rigid partition plate arranged between two supersonic flows; and jet flow holes are formed in the rear edge of the partition plate and are used for injecting jet flow. According to the supersonic flow mixing device based on the partition plate rear edge jet flow disturbance, an independent channel is provided for the two supersonic air flows based on the partition plate, and the jet flow is injected through the jet flow holes formed in the rear edge of the partition plate. Under the disturbance of the jet flow of the partition plate, the flow of a mixing layer is unstable in advance, a large-scale vortex structure of the mixing layer is broken into a large number of small-scale vortex structures, and the contact area of upper and lower air flows can be effectively increased in the downstream evolution process so as to realize efficient mixing. The provided supersonic flow mixing device does not need additional excitation energy, is high in working condition adaptability and simple in structure, overcomes the defects of large flow resistance and total pressure loss, realizes efficient mixing through interaction of a jet vortex and a mixing layer vortex structure, and has relatively high engineering applicability.

Description

technical field [0001] The present application relates to the field of high-efficiency mixing technology in the field of aerospace propulsion, in particular to a supersonic flow mixing device based on jet disturbance at the trailing edge of a partition. Background technique [0002] With the development of hypersonic propulsion technology, new power forms such as combined cycle and scramjet have received extensive attention. In engine combustion chambers, the efficient mixing of supersonic gas and air has always been a difficult problem for researchers. For supersonic flows, the presence of compression effects combined with the size constraints of the combustor makes mixing of the flows inefficient. Efficient mixing is an important prerequisite for full combustion, and it is also an important basis for tapping the performance potential of the engine and improving the efficiency of the propulsion system. [0003] In order to achieve efficient mixing in the supersonic mixing...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/44F02K9/60
CPCF02K9/44F02K9/60Y02T50/60
Inventor 张冬冬谭建国姚霄刘瑶
Owner NAT UNIV OF DEFENSE TECH
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