Stage pressure turbine of the turbo-drill

 

(57) Abstract:

The invention relates to turbine drilling of deep wells, in particular to the implementation of the turbine of the turbo-drill. Stage pressure turbine of the turbo-drill consists of a hub of the stator is pressed into it, the stator blade of the crown having an inner rim, and the chord of the blades of the stator crown is inclined to the plane perpendicular to the axis of the pressure stage of the turbine, at an angle not exceeding 50. The inner surface of the larger diameter stator blade rounded crown radius R, whose center is the axis of the pressure stage of the turbine. Inside the hub of the stator and pressed into her shoulder crown freely inserted the rotor hub with pressed on her the rotor blade tip. Thus the chord of the rotor blades of the crown is inclined to the plane perpendicular to the axis of the pressure stage of the turbine, at an angle not less than 70. The rotor blades of the crown have a guaranteed gap Z relative to the hub of the stator within the range of values from 0.1 to 0.2 from the radial height h3the rotor blades of the crown. The invention provides increased service life of the axial bearings of the turbo-drill and in General, increasing the turnaround is rednaznachena for drilling oil and gas wells and in a narrower division of these funds - for constructive nodes downhole motors - turbodrills, through which are driven drill bits.

Analogue of the invention is the stage pressure turbine, described on page 18, Fig. 2 (see Turbine oil drilling. PP Shumilov, part I, lecture notes.Heavy industry. USSR, Moscow 1936, Leningrad).

In the source describes the degree of pressure turbine having conoidal surface of the restricting blade crown of the stator, while the rotor crown made without the outer rim.

This design pressure stage of the turbine has two major drawbacks: a large axial hydraulic load on the turbine rotor and the impossibility of drilling a turbodrill for drilling fluids containing an inert PlayReady filler type melkorublenyh cord fiber or plate-fish scales, which, falling in the narrow gap between the rotor blades rims and corresponding stator hub pressure stages of the turbine, one shaft of the turbo-drill.

The closest analogue of the invention is a turbine is performed according to the claims of the patent of Russian Federation N 2032063 (see PP. 18 and 19). This patent describes the degree dawni pressure turbine stator of a turbo-drill. But in the mentioned patent is not resolved and is not described none of the design features that reduce to a minimum axial hydraulic load on the rotor of the mud motor and avoid zaklinsky ends of the blades of the rotor crowns inert filler. Therefore, turbodrills so far not drill into the geological sections prone to mud loss.

The invention allows to drill a turbodrill in all geological formations, including those prone to partial or full acquisitions of mud, while allowing for increasing trouble-free service life of the axial bearings of the turbo-drill to significantly increase its overhaul life.

The essence of our invention is to provide recolorations turbine, bezobidnoy blade crown pressure stage rotor which has a large radial clearance relative to the hub of the stator. This gap is so large that it can't wedge themselves flakes filler, washed out of him by the flow of drilling mud.

All the designs of pressure turbine turbodrills increase the radial clearance blade row of the rotor relative to the ACC is of the efficiency of the turbine of the turbo-drill. In the construction of turbines with bezobidnymi blade rims rotary pressure (see nearest equivalent) under the action of centrifugal force to the slurry and the filler are displaced towards the ends of the blades get jammed and break them. When the rotor of the mud motor or jams in the stator or broken blades, falling into the lower pressure stage, break their blades, then all turbodrill turbine turns into scrap metal.

In the invention the blades of the rotor crowns are profiling and installed so that the operating frequencies of the rotation shaft of the rotor of the turbo-drill the main part of the differential pressure in the turbine is implemented in the stator blade rows. Thus to the possible minimum reduced hydraulic axial load on the rotor of the turbo-drill and reduced leakage of the drilling fluid in the gaps of the rotary crowns. This fact is especially important for designs turbodrills with independent spindle axial bearing heel in each section.

The invention is illustrated in three figures.

In Fig. 1 shows the General layout of the pressure stage of the turbine.

In Fig. 2 shows a detail of the upper crown pressure stage stator of the turbine.

Inside the hub of the stator 1 and the shoulder of the crown of the stator 2 is freely inserted the rotor hub 4, which is pressed (or secured in any other appropriate way) blade crown of the rotor 5. In Fig. 1, the rotor hub 4 is based on the ring 6 (in the Assembly of the turbodrill it is not used), with which the rotor hub 4 is the actual position in which it is assembled turbodrill. The upper axial clearance is a value from 2 to 4 mm, the Lower axial clearance b is always greater than the clearance a and has a value of from 8 to 12 mm stator Vanes 7 of the crown 2 is performed in such a way that their radial height h1measured on the input side is always greater than their radial height h2measured on the output edge. The inner surface of the larger diameter of the shoulder of the crown 2 of the stator rounded with a radius "R", Zentai section of the shoulder of the crown 2 output edges of his shoulder blades. The inner rim 3 has a mainly rectangular cross-section, which in its upper part may have a smooth radius fillet.

Blade crown of the rotor 5 has a radial height h3blades 8, or equal to 1 to 3 mm greater than the radial height h2the stator blades of the crown 2. Radial clearance Z of the rotor blades of the crown 5 relative to the hub 1 is well within the range of values from 0.1 to 0.2 from the radial height h3blades 8 rotary crown 5.

The turbodrills relatively large diameter on the hub of the rotor 4 may be the groove 9, into which is inserted a rubber or rubber-to-metal seal 10, which may be of round, rectangular or elliptical shape.

The seal 10 overlaps the gap between the rim 3 of the shoulder of the crown 2 of the stator and the rotor hub 4.

The turbodrills small diameter on the hub 4, it is impossible to perform the groove 9, so on the outer surface of the hub 4 is cut fine metric thread (right screw).

The stator vanes 7 of the crown 2 is performed so that the slope of the L chord 11 to the plane perpendicular to the axis of the pressure stage of the turbine, does not exceed the values in the 50o, ornago crown 5 are thus their chord 12 coincides with the target plane of the inner surface of the blades 8. When this chord 12 is inclined at an angle to a plane perpendicular to the axis of the pressure stage of the turbine, at an angle of not less than 70o. Thus the slope of the chord 11 of stator blades 7 is different from the slope of the chord 12 of the blades 8 of the rotor angle of more than 20o.

The minimum gap dpbetween two adjacent blades 8 rotary crown should be not less than 11 mm, the performance blade rims 2 of the stator and 5 of the rotor allows the operating frequency range of rotation of the mud motor to actuate the main part of the pressure drop in the stator of a turbo-drill simultaneously raising to the highest possible overall efficiency of the turbine and reducing to a minimum the amount of hydraulic axial load on the axial bearings of the turbo-drill. At the same time such a performance pressure stages of the turbine allows the turbodrill properly working on solutions containing fibrous or lamellar fillers.

WORKING PRESSURE STAGE OF THE TURBINE OF THE TURBO-DRILL

The flow of drilling fluid up through the stator vanes 7 of the crown 2, generates kinetic energy. When seal 10 is liquidated leak part of the solution flow rate in kolawole leakage is eliminated and the effect of "zataskivanija" filler specified in the annular channel, that is liquidated and the reason that causes Salenko rotating hub 4 rotary pressure stage of the turbine of the turbo-drill.

In the absence of the hub 4, the seal 10 is trapped in the annular gap filler with a thread cut on the outer surface of the hub 4, being pushed in the axial upper interfering with a gap.

The flow of drilling fluid passing through the stator blades 7 of the crown 2, flowing down over the surface formed by the radius R, deviates from the ends of the blades 8 of the rotary crown 5. At the end a sharp edge (pair of radius R and output edges of the blades 7) blade of the crown 2 is formed vortex circulation, the rotation of which is directed against clockwise movement. This vortex escapes the gap Z between the ends of the blades 8 and the corresponding wheel hub 1 stator pressure stage of the turbine). If individual particles or flakes filler and fall into the gap under the action of centrifugal force from the rotating blades 8, unlike bezobidnyh turbines with a low value of this gap, they do not get jammed rotary stage pressure turbine in the hub of the stator 1 stage pressure and flow of the solution are carried at the lower axial clearance b.

M is th crown 5 (designation dpsubstantially greater than that of the turbines other structural types. This allows you to "skip" over the shoulder crowns viscous drilling fluids with a high concentration playlouder filler (filler mud to fight acquisitions drilling fluid in the wellbore).

1. Stage pressure turbine of the turbo-drill, consisting of a stator hub pressure with fixed inside the stator blade ring having an inner rim, and a rotary pressure, consisting of a hub of a rotary pressure attached to it a rotary blade crown, characterized in that the radial clearance between the ends of the rotor blades of the crown and the stator hub is well within the range of values from 0.1 to 0.2 from the radial height of the vane rotor crown.

2. Stage pressure turbine of the turbo-drill performed on p. 1, characterized in that the stator blade, the crown has an inner surface with a larger diameter, described by a radius, the center of which is located from the axis of the pressure stage of the turbine.

3. Stage pressure turbine of the turbo-drill performed on p. 1, characterized in that the slope of the chord of the blades of the stator crown of the NCA to the same plane at an angle of more than 20, thus the chord of the blades of the stator crown tilted to the specified plane at an angle of not more than 50, and the chord of the rotor blades of the crown at an angle of not less than 70.

4. Stage pressure turbine of the turbo-drill performed on p. 1, characterized in that the hub of the rotary pressure stage of the turbine has an elastic sealing contact with the inner surface of the rim of the stator blade and the crown.

5. The degree of pressure of the turbo-drill performed on p. 1, characterized in that on the outer surface of the rotor hub pressure stage of the turbine is running, the screw thread.

 

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