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Modularized reusable multiunit circle-to-square compression ratio plug nozzle testing device

A plug-type nozzle and test device technology, which is applied to jet propulsion devices, rocket engine devices, machines/engines, etc., can solve the problems of difficult work, high cost, limited experimental tasks, etc., and achieves convenient replacement, convenient disassembly, The effect of low cost of continued use

Inactive Publication Date: 2014-04-30
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the current experimental research work is difficult, costly, and takes a long time to prepare for the test. The experimental tasks completed by the test piece are limited, especially for the heat flow test of the engine, and the number of use of the test piece is limited.

Method used

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  • Modularized reusable multiunit circle-to-square compression ratio plug nozzle testing device
  • Modularized reusable multiunit circle-to-square compression ratio plug nozzle testing device
  • Modularized reusable multiunit circle-to-square compression ratio plug nozzle testing device

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Effect test

Embodiment Construction

[0033] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0034] The present invention is a kind of modularized reusable multi-unit circular rotary square reduction ratio plug nozzle test device, such as figure 1 , figure 2 As shown, it includes a combustion chamber casing 1 , an injector assembly 2 , a combustion chamber assembly 3 , a plug cone assembly 4 and a support connection assembly 5 .

[0035] The combustion chamber housing 1 is processed by 1Cr18Ni9Ti material, and n cylindrical inner cavities 101 are arranged side by side, n>1, such as image 3 As shown, the specific number of inner chambers 101 is determined according to the outlet width of the circular inner nozzle 301 and the width of the plug cone 401, and the two ends of each inner chamber 101 pass through the front and rear ends of the combustion chamber housing 1; A set of injector assembly 2 and a set of combustion chamber assembly 3. ...

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Abstract

The invention discloses a modularized reusable multiunit circle-to-square compression ratio plug nozzle testing device which comprises a combustion chamber shell, injector assemblies, combustion chamber assemblies, a plug cone assembly and a supporting connecting assembly, wherein a plurality of injector assemblies are arranged in the combustion chamber shell; each injector assembly is correspondingly connected with one combustion chamber assembly; the inside of each injector assembly is provided with an oxygen cavity and a hydrogen cavity; hydrogen-oxygen gas smooth-bore tips for independently spraying and injecting gaseous oxygen and gaseous hydrogen are arranged in the hydrogen cavities; circle-to-square inner spray pipes are arranged inside the combustion chamber assemblies; and the plug cone assembly is connected with the combustion chamber assemblies and is supported by the supporting connecting assembly. The testing device disclosed by the invention not only can be used for carrying out cold flow test, but also can be used for carrying out ignition hot flow test; the modularized design, assembly and disassembly of the assemblies are implemented; the modularized reusable multiunit circle-to-square compression ratio plug nozzle testing device can be repeatedly used by replacing ablated parts; and the modularized reusable multiunit circle-to-square compression ratio plug nozzle testing device adopts an ablation and heat sinking passive cooling mode, has a simple structure, and is low in continuing cost.

Description

technical field [0001] The invention relates to the technical field of aerospace engine testing, in particular to a modularized and reusable multi-unit circular-to-square reduction plug-type nozzle test device. Background technique [0002] Improving nozzle efficiency and reducing nozzle weight are the main goals of rocket engine design. Because aerospace vehicles have to experience different flight altitudes during flight, the traditional bell nozzle can only achieve the best performance at the design altitude, and higher or lower design altitudes will cause a certain performance loss, that is, under-expansion loss or overexpansion loss. Due to the open flow structure on the outside of the pneumatic plug nozzle, the gas is connected to the ambient pressure on one side, and the expansion state is automatically adjusted under the influence of the environmental back pressure. The gas is in a fully or nearly fully expanded state at the entire flight height. High performance w...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/96F02K9/97
Inventor 覃粒子张文电张晓源王一白刘宇
Owner BEIHANG UNIV
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