CN109025804B - Turbine type axial impactor - Google Patents

Abstract

The invention relates to a turbine type axial impactor, wherein the upper end of a main short circuit of the turbine type axial impactor is connected with a double female joint, the lower end of the main short circuit is connected with an impact joint through a hexagonal sleeve, a hollow cavity of the impact joint is positioned in the main short circuit, an overflowing cover head of an overflowing cover plate is seated at the upper port of the hollow cavity of the impact joint, an overflowing channel of the overflowing cover plate is inserted into the hollow cavity, a piston hammer is of a three-section type hollow cylindrical structure and positioned in an annular space between the hollow cavity and the overflowing channel, a transmission cylinder of a turbine rotor is inserted into the overflowing channel, an annular table in the turbine rotor is seated on the overflowing cover head of the overflowing cover plate, the upper end of the turbine rotor is connected with a jet stator, and the jet stator is pressed at the lower port of the double female joint; the inside of the jet flow stator is provided with oblique perforation holes, and when fluid passes through the oblique perforation holes, the jet flow hits turbine blades of the turbine rotor, so that the turbine rotor rotates. The invention can generate good longitudinal vibration on the drill bit, and the speed-up effect is very obvious.

Description

Turbine Axial Impactor

Technical field:

The invention relates to a downhole hydraulic impact tool used in the drilling of oil and natural gas, in particular to a turbine-type axial impactor.

Background technique:

With the advancement of exploration and development technology, the depth of oil and gas wells continues to increase, and the number of deep and ultra-deep wells also increases. The high hardness of the deep formation rock and the high drillability value are the main reasons for the increase of drilling difficulty, the slowdown of ROP and the increase of drilling cost. The difficulty of drilling in hard formations has become more and more prominent, and high-efficiency rock-breaking technology is more important. The efficiency of rock-breaking will directly determine the speed and cost of drilling, and further determine the economic benefits of drilling projects. Through laboratory experiments and field practice, it can be seen that when a certain periodic impact force acts on the drill bit, the rock breaking efficiency of the drill bit will be significantly increased, thereby increasing the ROP.

Axial impactor, as a power tool for downhole auxiliary rock breaking, has received more and more attention in the industry because it does not need to provide additional energy, and has gradually become an indispensable technical means for speed-up of deep wells. Although various types of impactors have been proven to improve drilling efficiency in field tests, they have shortcomings such as short life and easy to be affected by drilling fluid properties, so that they have not been widely used in drilling rig operations.

Invention content:

The purpose of the present invention is to provide a turbine-type axial impactor, which is used to solve the problems of slower drilling speed and lower tool impact efficiency as the depth of the oil well increases.

The technical scheme adopted by the present invention to solve the technical problem is as follows: the turbine-type axial impactor includes a double female joint, a main body short-circuit, a hexagonal sleeve, an impact joint, a jet stator, a turbine rotor, Overcurrent cover plate, piston hammer, the upper end of the main body short-circuit is connected to the double female joint, and the lower end is connected to the impact joint through a hexagonal sleeve. The upper port of the cavity, the overflow channel of the overflow cover plate is inserted into the hollow cavity, the piston hammer is a three-section hollow cylindrical structure, the piston hammer is located in the annular space between the hollow cavity and the overflow channel, and the transmission cylinder of the turbine rotor is inserted through the cavity. In the flow channel, the annular stage in the turbine rotor sits on the flow cover head of the flow cover plate, the upper end of the turbine rotor is connected to the jet stator, and the jet stator is pressed at the lower port of the double female joint; there are oblique perforations inside the jet stator. When the fluid passes through the oblique perforation, the jet hits the turbine blades of the turbine rotor, causing the turbine rotor to rotate;

The transmission cylinder is hollow, the transmission cylinder above the annular table has an inflow hole, the transmission cylinder under the annular table is provided with a first circulation hole and a second circulation hole, and the flow passage is correspondingly provided with a first flow hole and a second flow hole. The hollow cavity is correspondingly provided with a first liquid outlet hole and a second liquid outlet hole.

In the above scheme, the jet stator is stuck at the female buckle of the main body short-circuit, and an annular elastic body is arranged between the jet stator and the double female joint, in order to slow down the impact of the reverse force formed by the jet on the double female joint; the oblique direction of the jet stator The outlet end of the perforation has an oblique groove with an inclined outer contour, which matches the turbine blades of the turbine rotor; there is a limit slot in the center of the jet stator, and the limit post at the upper end of the turbine rotor is inserted into the limit slot, so that the turbine The rotor does not move radially and axially.

In the above solution, there is a protection ring on the lower edge of the limiting column of the turbine rotor, and the function of the protection ring is to reduce the friction between the turbine rotor and the jet stator during the rotation process.

In the above scheme, the impact joint has a decompression hole at the bottom of the hollow cavity, from which the fluid can flow out of the hollow cavity, thereby reducing the pressure in the hollow cavity; There is a confluence channel on the flushing joint, from which the fluid from the first liquid outlet hole and the second liquid outlet hole can flow into the confluence channel; there is a steady flow channel between the decompression hole and the liquid outlet channel, in order to make the fluid flow A stable state is formed; there is a section of hexagonal joint outside the impact joint, the hexagonal joint matches the inside of the hexagonal sleeve, the impact joint is fixed, and the sharp part of the hexagonal joint has a chamfer, in order to reduce the wear during the vibration process.

In the above scheme, there is a snap ring groove on the outside of the impact joint, which is used to place the half ring to achieve the function of fixing the impact joint; a T-shaped step is set at the lower end of the snap ring groove to install the elastic body and buffer the movement of the impact joint.

In the above scheme, the jet stator has 1-7 oblique perforations.

In the above scheme, the turbine rotor has 1-17 turbine blades and 1-4 inflow holes.

In the above scheme, the impact joint has 1-8 liquid outlet channels, 1-6 first liquid outlet holes, and 1-6 second liquid outlet holes.

The present invention has the following beneficial effects:

1. The cooperation between the turbine rotor and the overflow cover plate of the present invention has a strong interference effect on the drilling fluid flow, can generate a pulse impact load, and generate a good longitudinal vibration on the drill bit, and the speed-up effect is very obvious.

2. The present invention mainly opens different chambers through the rotation of the turbine rotor, causing the piston hammer to move, so there is no such high requirement on sealing.

3. The longitudinal vibration frequency and amplitude of the present invention are controlled by the size, number and inclination angle of the oblique perforations, which are easy to adjust.

4. The present invention has no buffer reset device such as a spring, which reduces energy loss, improves the utilization efficiency of hydraulic impact power, and solves the problem of low impact efficiency.

5. The present invention has a simple structure, is easy to implement, has a low cost, and is convenient for popularization and application in oilfields.

4. Description of the attached drawings:

Fig. 1 is the structural representation of the present invention;

Fig. 2 is the outline drawing of the impact joint in the present invention;

Fig. 3 is the sectional view of A-A in Fig. 2;

Fig. 4 is the outline drawing of the overflow cover plate in the present invention;

Fig. 5 is the sectional view of overflow cover plate in the present invention;

Fig. 6 is the structural representation of hexagonal sleeve in the present invention;

Fig. 7 is the structural representation of movable hammer in the present invention;

Fig. 8 is the sectional view of the jet stator in the present invention;

Fig. 9 is the top view of the jet stator in the present invention;

Fig. 10 is the outline drawing of the turbine rotor in the present invention;

Fig. 11 is F-F sectional view in Fig. 10;

Fig. 12 is the upward movement state diagram of the movable hammer in the present invention;

Figure 13 is a sectional view of A-A in Figure 12;

Figure 14 is a sectional view of B-B in Figure 12;

Fig. 15 is the state diagram that the movable hammer keeps going up in the present invention;

Figure 16 is a sectional view of A-A in Figure 15;

Figure 17 is a sectional view of B-B in Figure 16;

Fig. 18 is the downward movement state diagram of the movable hammer in the present invention;

Figure 19 is a sectional view of A-A in Figure 18;

Figure 20 is a sectional view of B-B in Figure 18;

Fig. 21 is the state diagram that the movable hammer keeps descending in the present invention;

Figure 22 is a sectional view of A-A in Figure 21;

FIG. 23 is a cross-sectional view taken along line B-B of FIG. 21 .

In the figure, 1. double female joint, 2. main body short connection, 3. hexagonal sleeve, 4. impact joint, 5. jet stator, 6. turbine rotor, 7. overflow cover, 8. piston hammer, 9. elasticity Body I, 10. Half ring, 11. Elastomer II, 12. Hexagonal joint, 13. T-shaped step, 14. Snap ring groove, 15. Liquid outlet channel, 16. Second liquid outlet hole, 17. First outlet Liquid hole, 18. Hollow cavity, 19. Decompression hole, 20. Confluence channel, 21. Steady flow channel, 22. Overflow cover, 23. Overflow channel, 24. First flow hole, 25. Second flow hole Orifice, 26. Oblique perforation, 27 Limit slot, 28 Slant slot, 29. Limit column, 30. Protection ring, 31. Inflow hole, 32. Ring stage, 33. Transmission cylinder, 34. Section A circulation hole, 35. Second circulation hole, 36. Turbine blade, 37. Rotor channel, 38. First chamber, 39. Second chamber.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings:

As shown in Figure 1, this turbine type axial impactor includes a double female joint 1, a main body short-circuit 2, a hexagonal sleeve 3, an impact joint 4, a jet stator 5, a turbine rotor 6, The flow cover plate 7, the piston hammer 8, the upper end of the main body short circuit 2 is connected to the double female joint 1, the lower end is connected to the impact joint 4 through the hexagonal sleeve 3, and the hollow cavity 18 of the impact joint 4 is located in the main body short circuit 2. The overflow cover head 22 sits on the upper port of the hollow cavity 18 of the impact joint 4, and the flow passage 23 of the overflow cover plate 7 is inserted into the hollow cavity 18, so that the piston hammer 8 only moves inside the hollow cavity 18; the piston hammer 8 is located in the hollow cavity In the annular space between 18 and the overflow channel 23, the transmission cylinder 33 of the turbine rotor 6 is inserted into the overflow channel 23, the annular stage 32 in the turbine rotor 6 sits on the overflow cover head 22 of the overflow cover plate 7, and the turbine The upper end of the rotor 6 is connected to the jet stator 5 .

The jet stator 5 is stuck at the female buckle of the main body short-circuit 2, and an annular elastic body is installed between the jet stator 5 and the double female joint 1, in order to slow down the impact of the reverse force formed by the jet on the double female joint 1; As shown in FIGS. 8 and 9 , the outlet end of the oblique perforation 26 of the jet stator 5 has an oblique groove 28 with an inclined outer contour, which is convenient for matching with the turbine blades 36 of the turbine rotor 6; There is a limit slot 27 in the table, so that the turbine rotor 6 does not move radially and axially.

4 and 5, there is a flow passage 23 inside the flow cover plate 7, and the inner diameter of the flow passage 23 matches the outer diameter of the transmission cylinder 33 of the turbine rotor 6, so that the transmission cylinder 33 can pass through the flow. Rotating in the channel 23, the annular stage 32 in the turbine rotor 6 sits on the overflow cover head 22 of the overflow cover plate 7 to limit the axial movement of the overflow cover plate 7; there are seven oblique perforations 26 inside the jet stator 5 , when the fluid passes through the oblique perforations 26 , the jet will hit the turbine blades 36 of the turbine rotor 6 , causing the turbine rotor 6 to rotate.

The transmission cylinder 33 of the turbine rotor 6 is hollow, forming a rotor channel, which is the flow channel of the fluid; and the transmission cylinder 33 is divided into three sections, and there is an inflow hole 31 at the upper end of the transmission cylinder 33 to allow the fluid passing through the turbine blades 36. Flow into the rotor channel 37 of the turbine rotor 6; the transmission cylinder 33 has two sets of symmetrical circulation holes (the first circulation hole 34 and the second circulation hole 35), and there are also two sets of corresponding flow holes on the flow cover plate 7 (The first flow hole 24 and the second flow hole 25 ), they match each other, so that the piston hammer 8 moves repeatedly to impact the impact joint 4 .

The impact joint 4 has a decompression hole 19 at the bottom of the hollow cavity 18, from which the fluid can flow out of the hollow cavity 18, thereby reducing the pressure in the hollow cavity 18; in the middle of the impact joint 4, there is a set of outlet The liquid channel 15, from which the fluid from the first liquid outlet hole 17 and the second liquid outlet hole 16 can flow into the confluence channel 20; and there is a steady flow channel between the decompression hole 19 and the liquid outlet channel 15 21, in order to make the fluid form a stable state. There is a section of hexagonal joint 12 outside the impact joint 4, which is used to match the interior of the hexagonal sleeve 3 and fix the impact joint 4, and the sharp parts of the hexagonal joint have chamfers, in order to reduce the wear during vibration.

When the present invention is installed: the hexagonal sleeve 3 is sleeved on the impact joint 4, and the interior of the hexagonal sleeve 3 is matched with the six-ring joint 12 of the impact joint 4; On the groove 14 and the T-shaped step 13, the hexagonal sleeve 3 and the main body short-circuit 2 are screwed together to fix the impact joint 4; the piston hammer 8 is installed into the hollow cavity 18 of the impact joint 4, and the overflow The cover plate 7 and the turbine rotor 6 are inserted into the hollow cavity 18. At this time, the piston hammer 8 will only move axially inside the hollow cavity 18; To match, install the elastic body I9 on the turbine rotor 6, and finally tighten the double female joint 1 and the main body short-circuit 2 with threads, and the installation is completed.

As shown in FIGS. 2 and 3 , when the fluid in the hollow cavity 18 cannot flow out from the first liquid outlet hole 17 or the second liquid outlet hole 16 , a closed space will be formed inside the hollow cavity 18 , and as the fluid flows Inflow, the internal pressure of the hollow cavity 18 will gradually increase, causing the tool to be easily damaged. Therefore, a decompression hole 19 is punched at the bottom of the hollow cavity 18 to reduce the pressure in the hollow cavity. The snap ring groove 14 is used to install the half ring 10 so as to fix the impact joint 4 . The T-shaped step 13 is for installing the elastic body II 11 to relieve the position movement of the impact joint 4 caused by the periodic impact force of the piston hammer 8 .

As shown in FIG. 6 , the hexagonal sleeve 3 has a regular hexagon inside, which just matches the hexagon of the hexagonal joint 12 of the impact joint 4 , and is used to fix the impact joint 4 . The outside of the hexagonal sleeve 3 is a set of threads, which are matched with the internal threads of the main body short connection 2, so that the hexagonal sleeve 3 and the main body short connection 2 are connected together.

The overflow cover plate 7 in Fig. 4 and Fig. 5 is installed inside the piston hammer 8 in Fig. 7, and the transmission cylinder 33 of the turbine rotor 6 is also installed inside the flow passage 23 of the overflow cover plate 7. A ring of successive installations. Due to the rotation of the turbine rotor 6, the two circulation holes of the turbine rotor 6 and the corresponding two flow holes of the flow cover plate 7 will form a communication or closed channel at the same time, but because there is a layer of piston hammer 8 on the outside, just enough The passage is blocked, so the communication condition of the two passages is also closely related to the movement condition of the piston hammer 8 .

The piston hammer 8 shown in FIG. 7 is a three-section hollow cylindrical structure. The inner and outer diameters and lengths of the first and last sections are the same. The outer diameter of the middle section is large and the inner diameter is small. The piston hammer 8 is installed in the hollow cavity 18 of the impact joint 4. , can move axially, the middle section of the piston hammer 8 has a large outer diameter and a small inner diameter, in order to reduce the piston hammer 8 and the inside of the outer hollow cavity 18 and the inner overflow cover when the piston hammer 8 moves axially. friction on the outside of the plate 7, thereby reducing energy losses.

For ease of understanding, the working process of the present invention is described below:

1. When the turbine rotor 6 rotates, the first circulation hole 34 of the turbine rotor 6 is staggered from the first flow hole 24 of the flow cover plate 7 , as shown in FIGS. 12 , 13 and 14 . The first chamber 38 composed of the movable hammer 8, the overflow cover plate 7 and the impact joint 4 forms a negative pressure area, the movable hammer 8 moves upward, and the fluid in the first chamber 38 flows out from the first liquid outlet hole 17;

2. When the turbine rotor 6 continues to rotate and the first circulation hole 34 communicates with the first flow hole 24, the piston hammer 8 blocks their passage again, but at this time the second circulation hole 35 and the second flow hole 25 Connected, the fluid flows out from the second liquid outlet hole 16, and the piston hammer 8 maintains the upward state, as shown in Figures 15, 16, and 17;

3. When the turbine rotor 6 rotates again, the second circulation hole 35 and the second flow hole 25 are staggered, forming a negative pressure area in the second chamber shape 39, as shown in Figures 18, 19, 20, the piston hammer 8 moves downward, the fluid in the second chamber 39 flows out from the second liquid outlet hole 16;

4. When the turbine rotor 6 rotates again, the second circulation hole 35 communicates with the second flow hole 25, and the piston hammer 8 blocks their passage, but at this time the first circulation hole 34 and the first flow hole 24 Connected, the fluid flows out from the first liquid outlet hole 17, and the piston hammer 8 maintains the downward state, as shown in Figures 21, 22, and 23.

In this cycle, the piston hammer 8 will make a cyclic movement in the hollow cavity 18, repeatedly and periodically impact the impact joint 4.

Claims (8)

1. A turbine axial impactor, comprising: the turbine type axial impactor comprises a double female joint (1), a main body short circuit (2), a hexagonal sleeve (3), an impact joint (4), a jet flow stator (5), a turbine rotor (6), an overflowing cover plate (7) and a piston hammer (8), wherein the upper end of the main body short circuit (2) is connected with the double female joint (1), the lower end of the main body short circuit is connected with the impact joint (4) through the hexagonal sleeve (3), a hollow cavity (18) of the impact joint (4) is positioned in the main body short circuit (2), an overflowing cover head (22) of the overflowing cover plate (7) is seated at an upper port of the hollow cavity (18) of the impact joint (4), an overflowing channel (23) of the overflowing cover plate (7) is inserted into the hollow cavity (18), the piston hammer (8) is of a three-section hollow cylindrical structure, the piston hammer (8) is positioned in an annular space between the overflowing cavity (18) and the overflowing channel (23), a transmission cylinder (33) of the turbine rotor (6) is inserted into, an annular table (32) in the turbine rotor (6) is seated on an overflowing cover head (22) of the overflowing cover plate (7), the upper end of the turbine rotor (6) is connected with a jet flow stator (5), and the jet flow stator (5) is pressed at the lower port of the double female connector (1); the jet flow stator (5) is internally provided with oblique perforation holes (26), and when fluid passes through the oblique perforation holes (26), the jet flow hits turbine blades (36) of the turbine rotor (6), so that the turbine rotor (6) rotates;

the transmission cylinder (33) is hollow, the transmission cylinder above the annular table (32) is provided with an inflow hole (31), the transmission cylinder below the annular table (32) is provided with a first circulation hole (34) and a second circulation hole (35), the overflowing channel (23) is correspondingly provided with a first overflowing hole (24) and a second overflowing hole (25), and the hollow cavity (18) is correspondingly provided with a first liquid outlet hole (17) and a second liquid outlet hole (16).

2. The turbine axial impactor of claim 1, wherein: the jet flow stator (5) is clamped at a female buckle of the main body short circuit (2), and an annular elastic body is arranged between the jet flow stator (5) and the double female joint (1); an outlet end of an oblique perforation (26) of the jet flow stator (5) is provided with an oblique clamping groove (28) with an inclined outer profile, and the oblique clamping groove (28) is matched with a turbine blade (36) of the turbine rotor (6); a limiting groove (27) is formed in the center of the jet flow stator (5), and a limiting column (29) at the upper end of the turbine rotor (6) is inserted into the limiting groove (27).

3. The turbine axial impactor of claim 2, wherein: the lower edge of the limiting column (29) is provided with a protective ring (30).

4. The turbine axial impactor of claim 3, wherein: the bottom of the hollow cavity (18) of the impact joint (4) is provided with a pressure reducing hole (19), the middle part of the impact joint (4) is provided with a liquid outlet channel (15), and the impact joint below the liquid outlet channel (15) is provided with a confluence channel (20); a steady flow channel (21) is arranged between the pressure reducing hole (19) and the liquid outlet channel (15); a section of hexagonal joint (12) is arranged outside the impact joint (4), the hexagonal joint (12) is matched with the inside of the hexagonal sleeve (3), the impact joint (4) is fixed, and a sharp part of the hexagonal joint (12) is provided with a chamfer.

5. The turbine axial impactor of claim 4, wherein: the outside of the impact joint (4) is provided with a clamping ring groove (14), and the lower end of the clamping ring groove (14) is provided with a T-shaped step (13).

6. The turbine axial impactor of claim 5, wherein: the jet flow stator (5) is provided with 1-7 oblique perforation holes (26).

7. The turbine axial impactor of claim 6, wherein: the turbine rotor (6) is provided with 1-17 turbine blades (36) and 1-4 inflow holes (31).

8. The turbine axial impactor of claim 7, wherein: the impact joint (4) is provided with 1-8 liquid outlet channels (15), 1-6 first liquid outlet holes (17) and 1-6 second liquid outlet holes (16).