A fluid test tool
A technology of tooling and liquid flow, which is applied in the field of liquid flow test tooling and combined sealing structure, can solve the problems of no liquid flow test tooling, etc., and achieve the effect of tight combination
Active Publication Date: 2020-08-18
XIAN AEROSPACE PROPULSION INST
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- Application Information
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Problems solved by technology
[0004] For the components to be tested with this structure, there is no corresponding liquid flow test tooling at present.
Method used
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Embodiment Construction
[0036] The present invention will be described in detail below in conjunction with the accompanying drawings.
[0037] as attached figure 1 As shown, the liquid flow test tooling of the present invention consists of three parts: the housing 3 , the upper cover 31 and the base 2 . The shell 3 and the upper part 11 of the component to be tested form a water inlet ring cavity to ensure that water enters the component 1 to be tested evenly. The shell 3 is fastened together with the base 2 by multiple bolts, so that the upper end of the base 2 faces the shell 3 and the component to be tested. The test part 1 forms a supporting lifting effect. The base 2 can be fixed to the test bench by two bolts (not shown in this part of the structural diagram), so as to ensure that the component to be tested 1 is safely fixed. The upper cover 31 of the present invention is to prevent water from overflowing from the upper end of the component to be tested 1 during a large flow rate, and can be ...
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The invention relates to a liquid flow test tool. In order to solve the liquid flow test problems that water is fed in the circumferential direction of an upper portion, the water is drained in the axial direction of a lower portion, and a part with an annular step mounting surface is arranged on the outer side of the lower portion. The tool comprises a shell, an upper cover and a base; the shellis a hollow cavity with an opening at the lower end, the to-be-tested part can be placed into the hollow cavity with a lower end opening, a water inlet ring cavity can be formed between the hollow cavity and the to-be-tested part, water inlet holes which lead to a water inlet annular cavity are formed in the upper part of the shell, and water inlet nozzles are arranged at the water inlet holes; and an annular groove used for containing a second sealing element is formed in the position, opposite to the to-be-tested part, of the hollow cavity; a pressure measuring nozzle which leads to the hollow cavity is further arranged in the circumferential direction of the shell; the top of the shell is further provided with an upper cover installation hole, and the upper cover is arranged at the position of the upper cover installation hole and is in sealed connection with the shell; the base is provided with a central through hole matched with the to-be-tested part, and the base is located on the periphery of the to-be-tested part and is positioned below the shell; and the base is fixedly connected with the shell.
Description
technical field [0001] The invention relates to the technical field of liquid flow test, in particular to a combined sealing structure and a liquid flow test tool adopting the combined sealing structure. Background technique [0002] During the thrust chamber development process, some components need to be tested for fluid flow. [0003] figure 1 Shown is the structural diagram of the component to be tested. The component to be tested 1 is provided with a water cavity 15 in the axial direction, and the component to be tested is divided into an upper part 11 and a lower part 13 along the axial direction. The outer diameter of 11 is consistent with the outer diameter of the upper end of the lower part 13, and water can flow into the water chamber 15 from the water inlet channel 12. The liquid flow test needs to measure the inlet pressure of the part to be tested under a large flow rate, and visually check the form formed in the water chamber 15 when the part to be tested flo...
Claims
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IPC IPC(8): G01M15/14G01M15/02G01M13/00
CPCG01M13/00G01M15/02G01M15/14
Inventor 徐亚丽王昕卢永乐李军熊建华张彤李强
Owner XIAN AEROSPACE PROPULSION INST