Adjustable low-pressure ignition experiment system for researching sub-super mixed flow

Abstract

The invention discloses an adjustable low-pressure ignition experiment system for researching sub-super mixed flow, which comprises: an experiment section provided with a gas inlet and a gas outlet, wherein a through mixed gas flow channel is arranged between the gas inlet and the gas outlet; a subsonic gas flow channel, wherein the gas outlet end of the subsonic gas flow channel is connected withthe first inlet of the gas inlet; a gas inlet joint which is connected with the gas inlet end of the subsonic gas flow channel; a supersonic gas flow channel, wherein the gas outlet end of the supersonic gas flow channel is connected with the second inlet of the gas inlet; a combustion chamber which is connected with the gas inlet end of the supersonic gas flow channel; an outlet flow channel which is connected to the gas outlet and is provided with a heat exchange section; and a back pressure adjusting mechanism which is connected with the gas outlet of the outlet flow channel and used for adjusting the back pressure of the experiment system in a vacuumizing mode in the experiment process. The outlet flow channel is connected with the back pressure adjusting mechanism, the back pressureof the experiment system can be adjusted according to experiment requirements, the working environment of the rocket engine can be better simulated, and the back pressure of the experiment system canbe adjusted more accurately.

Description

technical field [0001] The invention belongs to the technical field of aerospace experimental instruments, and in particular relates to an adjustable low-pressure ignition experimental system for studying sub-supermixed flow. Background technique [0002] In the embedded rocket ramjet combustion chamber, the mixture of the main rocket gas and the incoming air is a typical large-gradient sub-supershear mixed flow, and the large velocity difference and large temperature difference between the two jets make the difference between the jets The thickness of the formed shear mixing layer grows abnormally slowly with the flow direction, which will affect the energy and momentum transfer between the two jets, and then cause the overall combustion efficiency of the main ram combustion chamber to be low, and the fuel energy cannot be fully utilized, which will seriously affect the ram combination The working characteristics of the engine have become one of the technical bottlenecks in...

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Problems solved by technology

[0005] However, the current experimental devices for measuring sub-supershear mixed flow are only under constant back pressure conditions, while the high-altitude engine actually works under low back pressure conditions, which makes the existing experimental devices very useful for obtaining The flow field structure and characteristics of sub-supershear mixed flow have little reference significance

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