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A nozzle liquid flow performance test tooling structure

A technology for testing tooling and nozzles, applied in the field of nozzle liquid flow performance testing tooling structure, to achieve the effect of ingenious design, solving the problem of nozzle clamping and saving materials

Active Publication Date: 2019-02-05
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the existing test tooling cannot solve the above problems

Method used

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  • A nozzle liquid flow performance test tooling structure
  • A nozzle liquid flow performance test tooling structure
  • A nozzle liquid flow performance test tooling structure

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Experimental program
Comparison scheme
Effect test

Embodiment

[0037] see image 3 , in order to be able to clamp the tested nozzle 2 while ensuring that the medium flows out from the rectangular groove 202 and the outer shell of the nozzle during the liquid flow test, the present invention lengthens the outer upper end of the inner shell of the tested nozzle 2, adding at least 4 mm of cylindrical lengthening section 205 (preferably 4mm), and an annular groove 204 is opened in the cylindrical extension section 205 for pulling and fixing the nozzle 2 under test.

[0038] see Figure 4 , the tooling part of the nozzle liquid flow performance testing tooling structure provided by the present invention is mainly composed of a housing 1, an upper cover 4, a flange 5, a lining ring 6, a tight hoop 7, a hoop 8, a gasket 9, an O-shaped Circles (12, 13, 14, 15), bolts and nuts assist in completing their functions. The shell is used to introduce the water of the test system into the tooling, and also provides support for the upper cover 4; The u...

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Abstract

In order to solve a technical problem that the existing test tooling can not meet the requirement of nozzle liquid flow performance testing, the invention provides a tool structure for nozzle liquid flow performance testing, so that the liquid flow performance testing requirement of the nozzle is met. According to structural characteristics of a tested nozzle and a liquid flow test design requirement of the tested nozzle, an annular slot with an area of 1.5*1.5mm is formed in the upper end of the outer side of a housing inside the tested nozzle so as to realize lifting and fixation; and on the basis of cooperation of a clamping hoop and a fastening element, the tested nozzle is lifted and clamped at the annular slot. The tool structure based on ingenious design can be installed conveniently. The internal diameter of the cavity of the tool is designed to be phi 86mm and the drift diameter of each incoming connection pipe nozzle at the cavity is designed to be phi 20mm. Therefore, the flowing speed requirement of entrance of a medium into the cavity and a liquid flowing speed requirement of overflowing in a tested nozzle housing by the medium are met.

Description

technical field [0001] The invention relates to a tooling structure for testing nozzle liquid flow performance, which is used in the nozzle liquid flow test of rocket engines. Background technique [0002] In the process of rocket engine development, it is necessary to figure 1 , 2 The nozzle shown is subjected to a liquid test. The liquid test needs to measure the flow rate of the nozzle under a given pressure drop, obtain its performance parameters and verify whether the structural performance of the nozzle meets the technical requirements (the nozzle is required to pass through the rectangular groove and the shell under a given pressure drop of 1MPa The sum of the flow rate of the body into the water hole is: 3.255±0.065kg / s). Twelve rectangular grooves of 3 mm (length) × 2.1 mm (width) × 9 mm (height) are uniformly opened on the outer circle of the lower end surface of the nozzle, and there is no place for clamping and fixing. [0003] Therefore, in the design figure...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M13/00
CPCG01M13/00
Inventor 徐亚丽
Owner XIAN AEROSPACE PROPULSION INST