Supersonic nozzle jet mixing experiment device

Abstract

The invention discloses a supersonic nozzle jet mixing experiment device, which is characterized in that the device comprises a main flow nozzle and a jet nozzle. The main flow nozzle is in a rectangular tube structure; one end of a rectangular tube serves as a jet inlet end; the two sides of the jet inlet end are respectively provided with a plurality of circular holes; the circular holes are provided with a pressure sensor and a thermocouple; the other end of the rectangular tube is internally provided with an incoming flow acceleration section, which comprises a first convergence section, afirst flat and straight section and a first expansion section in sequence; the jet nozzle is communicated with the expansion section of the main flow nozzle; the jet nozzle is internally provided with a second convergence section, a second flat and straight section and a second expansion section in sequence, wherein the second expansion section is connected with the main flow nozzle; the first expansion section is provided with a plurality of through holes; the through hole is provided with a pressure sensor; the two sides of the rectangular tube are respectively provided with an observationwindow; and the observation windows are arranged at the two sides of the incoming flow acceleration section respectively. The experiment device can simulate air jet mixing phenomenon under supersonicflight.

Description

technical field [0001] The invention belongs to the field of experimental testing devices, in particular to a supersonic nozzle jet mixing experimental device. Background technique [0002] The scramjet only needs to carry fuel, inhale fresh air from the surrounding environment, and convert the chemical energy contained in the fuel into mechanical energy in the form of supersonic combustion in the scramjet combustion chamber. This idea provides a reference for improving the performance of solid rocket motors. For example, fresh air is injected into the tail nozzle of the solid rocket motor, and after burning with the propellant of the solid rocket motor, it is rich in H 2 The further combustion of combustible substances such as , CO and metal additives may further increase the thrust of the engine. For the combustion problem under supersonic conditions, the sufficient mixing of fuel and air is one of the key issues to improve its combustion efficiency. The mixing degree o...

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Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a supersonic nozzle jet mixing experimental device to solve the problem that the existing experimental device cannot simulate the air jet mixing experiment under supersonic flight, and the test jet parameters and flow field cannot be visualized. question

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