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Combined-type multifunctional combustion device

A technology for combustion devices and combustion test pieces, which is applied in the direction of jet propulsion devices, rocket engine devices, machines/engines, etc., can solve the problems of test times, costs, and cycle requirements, so as to save development costs, realize performance comparison research, The effect of shortening the cycle

Active Publication Date: 2016-02-17
BEIJING AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to obtain the influence law of each of the above parameters, it is necessary to design test pieces of dozens of schemes and conduct dozens of thermal test assessments, so the number of tests and the cost and cycle requirements are too much

Method used

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Embodiment Construction

[0017] A combined multifunctional combustion device according to the present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0018] Such as figure 2 Shown, a kind of combustion test article of the present invention, it comprises injector 16, installation section 17, 1# cylindrical section 18, 2# cylindrical section 19 and nozzle section 20 connected in sequence; An oxidant inlet 33 is provided at one end, and a fuel inlet 34 is provided on the injector 16 perpendicular to the oxidant inlet 33; a coolant outlet 22 and a 1# cylindrical section coolant inlet 26 are provided on the 1# cylindrical section 18; #Cylinder section 19 is provided with 2# cylinder section coolant inlet 24 and 2# cylinder section coolant outlet 25; nozzle section 20 is provided with coolant inlet 21 and nozzle section coolant outlet 23;

[0019] During the working process, the oxidant enters through the oxidant inlet 33; the f...

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Abstract

The invention provides a combined-type multifunctional combustion device. The combined-type multifunctional combustion device comprises a plurality of combustion test articles and a propellant supply system, wherein the combustion test articles are arranged in parallel. The propellant supply system comprises an oxidizing agent storage tank which is connected with oxidizing agent inlets of the combustion test articles through pipelines. An oxidizing agent flow adjustment element is arranged on the pipeline for connecting the oxidizing agent storage tank and the oxidizing agent inlet of each combustion test article. The propellant supply system further comprises a fuel storage tank which is connected with fuel inlets of the combustion test articles through pipelines. A fuel flow adjustment element is arranged on the pipeline for connecting the fuel storage tank and the fuel inlet of each combustion test article. Parallel type tests are performed through the segmental series-connection combined-type combustion device so that multifunctional measurement of combustion efficiency and heat flow distribution can be achieved; the axial length of a combustion chamber can be adjusted, and performance comparison research on different injector schemes under the same working condition can be achieved to the maximum extent.

Description

technical field [0001] The invention relates to a segmented series combined combustion device which is suitable for performance research of a high-pressure and large-heat-flow thrust chamber of a liquid rocket engine and can realize multi-functional measurements such as combustion efficiency, heat-flow distribution and acoustic characteristics. Background technique [0002] At present, my country does not yet have the conditions for high-pressure extrusion hot test run of the thrust chamber of a large-thrust liquid rocket engine. Therefore, in order to optimize the design of the thrust chamber and improve the combustion performance, the simulation research can only be carried out through the hot test run of a single nozzle or a reduced-scale injector. . Research results at home and abroad in recent years have shown that many injector structural details, including oxidizer nozzle retraction, outlet diameter, outlet pipe wall thickness, fuel nozzle annular gap and single nozzle...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F02K9/44F02K9/64F02K9/42
Inventor 丁兆波王仙张晋博赵世红许晓勇田原刘红珍姬威信潘刚于槟恺王召刘中祥陶瑞峰郑孟伟
Owner BEIJING AEROSPACE PROPULSION INST
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