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Combined removable nozzle test device

A nozzle test, combined technology, applied in the direction of measuring device, mechanical component testing, machine/structural component testing, etc., can solve the problem that fuel and oxidant nozzles cannot be replaced, avoid repeated production, reduce costs, and test cycle. short effect

Inactive Publication Date: 2016-03-09
BEIJING AEROSPACE PROPULSION INST
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  • Abstract
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Problems solved by technology

[0004] The technical problem to be solved by the present invention is: to overcome the deficiencies in the structure of the existing devices, to solve the problem that the fuel and oxidant nozzles cannot be replaced in the high-pressure low-temperature medium nozzle test device, to provide a combined removable nozzle test device, from the structural design Easier disassembly and interchange between fuel and oxidizer nozzles and collectors

Method used

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  • Combined removable nozzle test device

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Embodiment Construction

[0012] A combined removable nozzle test device according to the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0013] Such as figure 1 As shown, a combined detachable nozzle test device according to the present invention includes a fuel passage inlet collector 4 with a cavity inside, and fuel passage inlets 2 are respectively arranged on both sides of the fuel passage inlet collector 4, The fuel nozzle 6 is arranged on the upper part of the fuel road inlet collector 4, and the fuel nozzle 6 is provided with a fuel inlet in the cavity of the fuel road inlet collector 4;

[0014] The oxidant nozzle 5 is arranged on the upper part of the fuel nozzle 6, and the lower part of the oxidant nozzle 5 extends into the bottom of the fuel nozzle 6; the oxidizer inlet collector 3 is arranged on the upper part of the oxidizer nozzle 5, and the oxidizer inlet 1 is arranged above the oxidizer inlet collecto...

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Abstract

The invention provides a combined removable nozzle test device, which includes a fuel path inlet collector provided internally with a cavity. Two sides of the fuel path inlet collector are provided with fuel path inlets. A fuel nozzle is disposed at the upper portion of the fuel path inlet collector. The portion, which is located in the cavity of the fuel path inlet collector, of the fuel nozzle is provided with a fuel inlet. An oxidant nozzle is disposed at the upper portion of the fuel nozzle. The lower portion of the oxidant nozzle extends into the bottom in the fuel nozzle. An oxidant path inlet collector is disposed at the upper portion of the oxidant nozzle. An oxidant inlet is disposed above the oxidant path inlet collector. The fuel enters from the fuel path inlets at the two sides, and an oxidant enters from the oxidant inlet. The structure of the invention is easy to install and remove, reliable sealing of high pressure low temperature media can be achieved, the increase in test efficiency is facilitated. The invention is excellent in sealing and short in test cycle when used for an atomization test of high pressure low temperature liquid-propellant rocket engine materials and an oxidant nozzle.

Description

technical field [0001] The invention relates to a novel nozzle test device suitable for high-pressure and low-temperature medium, which can be used in aerospace, petrochemical, automobile and other fields involving spray and atomization technology research. Background technique [0002] The nozzle test device is widely used in aerospace, petrochemical, automobile and other fields involving injection and atomization technology research, such as a test device used to study the injection, mixing and atomization laws of two propellants of rocket engines. [0003] In the existing cryogenic liquid rocket engine nozzle test devices, the fuel and oxidant nozzles are mostly connected to the collector by brazing structure. Due to the limitation of the welding structure, the fuel and oxidizer nozzles cannot be replaced, so each test device can only be used for A nozzle structure is studied, which increases the cost and time of the test, which is not conducive to cost reduction and effi...

Claims

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Application Information

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IPC IPC(8): G01M13/00
CPCG01M13/00
Inventor 张晋博丁兆波王仙赵世红许晓勇田原刘红珍姬威信潘刚王召刘中祥陶瑞峰郑孟伟
Owner BEIJING AEROSPACE PROPULSION INST
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