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A machining method for high Mach number throat in a shock tunnel

A technology of high Mach number and shock wave wind tunnel, which is applied in the field of surface processing in the high Mach number throat of shock wave wind tunnel, which can solve the problems of high price, difficulty in guaranteeing machining accuracy and roughness, and cutting edge, so as to reduce damage , Improving the quality of the flow field and improving the effect of machining accuracy

Active Publication Date: 2020-06-09
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The position with the smallest diameter in the throat is called the throat hole, which is generally processed by turning. During the processing, due to the small diameter and deep depth, there is a serious phenomenon of tool give-up, and the final processing accuracy and roughness are difficult to guarantee.
[0003] The airflow passing through the throat of a high Mach number nozzle usually has a high enthalpy value (above 4000K), which requires higher resistance to ablation and erosion resistance of the throat. The current solution often uses high-temperature-resistant metals. Such as tungsten-zirconium-molybdenum alloy, expensive

Method used

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  • A machining method for high Mach number throat in a shock tunnel

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Embodiment Construction

[0030] Such as figure 1 The inner profile of the throat section shown includes constriction section ao, throat hole o, and expansion section od. Among them, the profile diameter is relatively large (for example, the diameter is greater than 50mm), and the parts that are easy to process are sections ab and cd, and the parts that are difficult to process For bo, oc segment.

[0031] Set the first front section forming reamer, the mold line mn of the blade and the throat b 2 o 2 Segment type lines are consistent;

[0032] Set the first post-forming reamer, the profile ts of the blade and the throat o 2 c 2 Segment type lines are consistent;

[0033] A method for processing an inner profile of a high Mach number throat in a shock tunnel, the steps are as follows:

[0034] Step 1: adopt the drilling machine to drill the inner hole, the aperture is less than the diameter of the throat hole, as the turning bottom hole;

[0035] Step 2: The lathe uses a rough turning tool for r...

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Abstract

The invention relates to a processing method of a shock tunnel high Mach number throat channel inner profile. Theprocessing method is characterized by comprising the steps that step 1, an inner hole is drilled, wherein the diameter of the inner hole is smaller than that of a throat hole, and the inner hole is used as a turning bottom hole; step 2,rough turning is carried out, excess materials arequickly removed, and preparation is made for finish turning; step 3, finish turning is carried out, an area far away from the throat hole and with larger diameter of the profile is subjected tofinish turning to the required final size; an area,close to the throat hole,with smaller profile diameter is subjected tofinish turning to leave a machining allowance of about 0.15 mm; and step 4, reaming iscarried out, a forming reamer isused for processinga throat channelto the final profile requirement.The processing method processes the inner profile near the throat hole by using the forming reamer,the seriousreamer back-off problem in the turning process is avoided, the processing precision is improved, the high-precision processing problem of the inner profile of a shock tunnel high Mach number throat channel is solved, and the flow field quality is improved.

Description

technical field [0001] The invention relates to a processing method for a profile surface in a high Mach number throat of a shock wave wind tunnel, and belongs to the field of hypersonic shock wave wind tunnel engineering. Background technique [0002] The shock tunnel is a special hypersonic wind tunnel. The shock tunnel is to increase the total temperature of the wind tunnel through the compression of the shock wave. The shock tunnel structure is very simple and the cost is relatively low. With the modern test The development of technology, which can undertake most of the hypersonic aerodynamic and aerothermal measurement tests, plays an increasingly important role in the development of the new model's aerodynamic shape. The shock tunnel nozzle is a pipe fitting device that generates hypersonic airflow. Because the nozzle is long, it is generally processed in sections. The inner surface of the throat section of the nozzle shrinks first and then expands, which affects the q...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P15/00
CPCB23P15/008
Inventor 宋可清谌君谋陈星蒋博姚大鹏马雁捷毕志献李辰
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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