Flow Field Analysis and Structure Optimization of the Nozzle Tail Flow
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摘要: 喷嘴是水力水平钻孔设备的核心元件，改善其结构有利于提高低渗透油气资源开采的施工效率。因此基于计算流体动力学(CFD)技术，分析尾部流道结构参数对射流流场的影响，得出以下结论：尾部流道数N=6、倾角α满足15°＜α＜30°，喷嘴出口直径d=1.4mm时，喷嘴的破岩和排屑性能较好；合理设计N和d，有利于实现喷嘴自推进和射流破岩两项功能；合理设计α，能有效改善尾部流道的磨损情况，延长喷嘴使用寿命。Abstract: The nozzle is the core component of a hydraulic horizontal drilling equipment, and optimizing its structure is crucial for helping to improve the construction efficiency of exploiting low permeability oil and gas resources.Based on the computational fluid dynamics (CFD) approach, we studied the effects of the structural parameters of the tail flow (evenly distributed on the end of the nozzle) on the jet flow field.The results show that:when the number of the tail flow (N) is 6, with an angle (α) between 15° and 30° and a diameter (D) of 1.4mm, the nozzle exhibits good performance on the rock fragmentation and discharge; the reasonable design of N and D contributes to implementing the nozzle propulsion and the rock destruction by jet; the reasonable design of the jet nozzle angle α contributes to effectively reducing the abrasion of the jet nozzle and extending its service life.
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Key words:
- computational fluid dynamics /
- hydraulic jet drilling /
- tail flow /
- nozzle /
- numerical simulation
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图 6 不同N下井底压力径向分布曲线
Figure 6. Radial distribution of the bottom holepressure with different N
图 7 N=4时轴截面速度分布云图
Figure 7. Velocity distribution nephogram inthe axial section when N=4
图 9 不同α下井底压力径向分布曲线
Figure 9. Radial distribution of the bottom holepressure with different α
图 14 不同d下井底压力径向分布曲线
Figure 14. Radial distribution of bottom holepressure with different d
表 1 喷嘴几何参数
Table 1. Geometric parameters of the nozzle
D1/(mm) L1/(mm) D2/(mm) L/(mm) d/(mm) N S α/(°) β/(°) 6 5 4 30 2 6 0.75 15 60 
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表 2 分析方案
Table 2. Analysis scheme
Scheme N d/(mm) α/(°) 1 3 2.0 0 2 4 2.0 0 3 5 2.0 0 4 6 2.0 0 5 7 2.0 0 6 8 2.0 0 7 6 2.0 15 8 6 2.0 30 9 6 2.0 45 10 6 2.0 60 11 6 1.0 15 12 6 1.2 15 13 6 1.4 15 14 6 1.6 15 15 6 1.8 15
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表 3 喷嘴轴向推进力
Table 3. The axial thrust of the nozzle
N Wall stress/(N) Recoilforce/(N) Propulsion/(N) Bottomstress/(N) 3 1190 -574 616 1923 4 1342 -467 875 1713 5 1369 -158 1211 1453 6 1525 -130 1395 1436 7 1760 -97 1663 1425 8 1737 87 1824 1280
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