Vortex stage pressure turbine of the turbo-drill

 

The invention relates to turbine drilling deep wells. Vortex stage pressure turbine consists of a hub of the stator, in which zapressovyvajutsja blade crown stator, which has an internal rim. The blades of the stator blade of the crown have the chord of the profile of the blades, which is inclined to the plane perpendicular to the longitudinal axis of the pressure stage of the turbine at an anglenot exceeding 50. Inside the stator hub and the rim is inserted into the rotary stage pressure turbine, which has a hub, which blade pressed in a reduced state, the crown having an outer rim. The rotor blades of the crown have the rear alignment angledefined inclined to the plane perpendicular to the longitudinal axis of the pressure stage of the turbine, the line. Angleis within the range from 40 to 80. External front surface of the blade is convex and shaped by one or more radii, smoothly connecting the output edges of the blades with their input rounded edges. The centers of these radii are located on the side of the line that defines the rear mounting angle lopa load on its rotor. 6 Il.

The present invention relates to means used for drilling oil and gas wells, and in particular to a turbine drilling of deep wells, and to fulfill the master node of the turbo-drill - parts of the turbine.

Distant analogue of the invention is the stage pressure turbine, described in the source: "fundamentals of theory techniques turbine drilling", ed. R. A. Ioannesjan, Costoptimized, Moscow-Leningrad, 1953, pages 50-51, Fig.33, option "a".

The closest analogue of the invention is the stage pressure turbine of the turbo-drill, performed according to the description of the invention under the patent of R. F. No. 2174584 "Stage pressure turbine of the turbo-drill", bull. No. 28 dated 10.10.2001,

This patent describes the degree of pressure turbine, 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 attached to it a rotary blade crown, while the slope of the chord of the profile of the stator blades of the crown to the plane perpendicular to the axis of the pressure stage of the turbine, does not exceed 50and the chord of the blades of the rotor blade crown tilted to the same plane for the majority of the pressure drop in the turbine of the turbo-drill in its stator unit and not only to a certain extent, relieve excessive hydraulic loads axial abutment of the turbodrill, but to increase the efficiency of the turbodrill as the mechanism as a whole.

However, as with all (unregulated flow of drilling mud) turbine blade apparatus, this turbine has a functional relationship between the magnitude of torque on its rotor and the frequency of its rotation, which is expressed by the linear relationship:

where Mi- torque on the turbine rotor when the rotational speed of ni;

Mt- maximum (ultimate joint) the torque on the turbine rotor ati=0, i.e. when the rotor is braked;

nx- idling speed of the turbine rotor when no torque load on it.

This means that when any sudden change in torque load on the rotor of the turbine (for example, the transition bit under the specified driller axial load on it from solid, nmomenteel the formation in viscous momentumsi) in cases wherethe turbine rotor is now.

M2is required on the bit torque at the entrance to the viscous interlayer;

M1- torque on the bit when drilling hard nmomenteel interlayer.

Every stop of the turbine rotor (i.e. the shaft of the turbo-drill, nye, re-run the turbodrill and slowly, working through the previously drilled interval, to come to the old slaughter and begin the process of drilling at a new reduced load on the bit. The extra time reduce drilling efficiency and make it difficult to extremes to automate the submission of a chisel. Therefore, the increase relationswhere MN- torque at peak power output of the turbine of the turbo-drill, while maintaining maximum efficiency is the goal that you are trying to solve for more than 60 years.

The invention allows to increase this ratio to values of 2.4 to 2.6 (versus 2, which are characterized by the turbine commercially available turbodrills). It also provided the maximum possible (in a given diametral dimensions of the turbine), the value of efficiency and the smallest (among all possible variants) axial height of the pressure stage of the turbine. It also provides the lowest possible hydraulic load on the turbine rotor, i.e. in axial abutment of the turbodrill.

The invention consists in creating pressure stage turbine, comprising a stator pressure stage having a hub and a stator vane crown with an inner rim; rotomatic stator crown to the plane, perpendicular to the axis of the pressure stage of the turbine, does not exceed 50and the line that defines the rear of the installation angle of the blades of the rotor blade crown, inclined to the plane perpendicular to the axis of the pressure stage of the turbine, at an angle from 40up to 80. The external front surface of the blades of the rotor blade of the crown is convex.

This surface is shaped by one or more radii that smoothly match the front clipped output edges of the blades with their input rounded edges.

The centers of these radii are located on the side of the line that defines the rear of the installation angle of the blades of the rotor blade and the crown.

With such design pressure stage of the turbine to 2.4 to 2.6 (in some cases up to 3) increases the ratio of maximum (ultimate joint) torque to the moments that have characterized the zone of maximum power. They are the same modes maximum efficiency of the turbines, designed on the basis of this description.

This invention allows the use of turbodrills pressure stage turbine with axial height of 38-42 mm, that is an opportunity to increase and absolute anisoptera illustrated by figures.

In Fig.1 shows the General layout of the vortex pressure stage of the turbine cross-section.

In Fig.2 is a cross section and pulling on the shoulder of the crown of the stator pressure stage of the turbine.

In Fig.3 is a cross section and pulling on the shoulder of the crown rotary vortex pressure stage of the turbine.

In Fig.4 shows unstressed irrotational flow mud vane rotary vane crown vortex pressure stage of the turbine during turbine operation in the zone of maximum values of efficiency.

In Fig.5 shows the vortex flow mud vane rotary vane crown when operating in modes overload its rotor torque.

In Fig.6 in dimensionless form is given of the energy performance of the vortex pressure stage of the turbine.

Vortex stage pressure turbine of the turbo-drill (in the three turbodrills them set up 420-450 pieces) consists of a hub of the stator 1, in which zapressovyvajutsja (glued) blade crown of the stator 2, which has an inner rim 3. Blade crown 2 with vanes 4 can be cast from steel, plastic and aluminum.

Inside the stator hub 1 and rim 3 is inserted into the rotary stage pressure turbine, which has a hub 5 of the rotor, which is on the shoulder of the crown.

In Fig.1, the hub 5 of the rotor based on the auxiliary ring 9, which is set to the correct position, which takes each vortex stage pressure rotor relative to the corresponding pressure stage stator in the casing of the turbine section. The blades 4 of the stator blade of the crown have the chord 10 of the profile, which is inclined to the plane perpendicular to the axis of pressure turbine at an angle ""not exceeding the value of 50.

Weekends thin edges 11 of the blades 4 are cut flush with the inner rim 3 by line 12. The blades 8 of the rotor blade crown 6 have the rear alignment angledefined inclined to the plane perpendicular to the axis of the turbine, line 13. The optimum anglefits in the range from 40up to 80. External front surface 14 of the blades 8 is convex and shaped by one or more radii, smoothly connecting the front clipped output edges 15 of the blades 8 with their input rounded edges 16. The centers of these radii are the line-side 13 that defines the rear mustache is ogotai or flat, or you can run two planes intersecting at an acute angle (on the energy characteristics of the vortex pressure stage turbine configuration of the back surface 17 of the influence it has little).

The performance of the vortex pressure stage turbine provides the maximum possible from now achieved within the specified diameters and axial dimensions height pressure stage) efficiency in the widest range of operating frequencies of rotation of its rotor; minimizes axial thrust on the heel of the turbodrill; a significant increase torque in the rotational speed range, located to the left of the maximum power mode, i.e., increases low-speed stability of the turbine.

The work of the vortex pressure stage of the turbine of the turbo-drill.

Vortex pressure stage turbine mounted in the turbine sections of the turbodrill with spindles having axial abutment rolling.

The bit with the mud motor to drill pipe is brought to the position "on-bottom" drilled wells, and then incorporated in the work of mud pumps. At idle considering the wellbore.

However due to the form and mode of wrapping mud blades rotor blade of the crown (Fig.4) tour and axial load when running at speeds within the range of the maximum values of efficiency, is a smooth increase in pressure drop at the turbine by increasing creativesage it effective pressure.

The increase in pressure difference balances by increasing the hydraulic load on the turbine rotor axial load on the bit, which greatly relieves from axial loads heel turbodrill.

From the idle rotation speed to the rotation speed, which is located to the left (but near) the frequency corresponding to the maximum power (Fig.6) wrap mud blades 8 of the rotary blade of the crown is almost without the formation of vortices (Fig.4) on their front surfaces 14 and occipital surfaces 17, so the line torque turbine 18 presents (like all turbines with unregulated flow of mud on the shoulder crowns) - direct. Driller, by loading the bit axial load on kilometre, while watching the pressure gauge on the riser so that the discharge pressure of the drilling fluid was unchanged (see line pressure drop 19, Fig.6), i.e., carries out drilling within the maximum power (line 20) on the turbine rotor. The increasing torque on the bit (the sign bit soft and sticky clay proplof work. If this changes dramatically in line with mud blades 8 of the rotary blade of the crown (Fig.5). On the occipital surface 17 of the blades 8 is formed a zone of intensive vortex that "clog" interscapular channels that, in turn, leads to the fact that dramatically increases the speed of flow of the drilling fluid on the front surfaces 14 of the blades 8. This, in turn, leads to a nonlinear sharp increase in torque on the turbine rotor and to a less intense growth pressure drop on it.

Driller, tracking unstable mode of operation of the turbine the pressure gauge, stops the feeding of the tool; the turbodrill, due to increased stock torque on the turbine rotor, fulfills the excess axial load, and the turbine is again in the range of stable rotation speed that is tracked by the driller pressure on the discharge lines of pumps.

After the pressure pump is normal, the driller can again start smooth feeding of the tool and the loading of the bit.

In most cases all operating modes of the turbine drilling are located to the right of point 21 - extreme power - on very gently sloping in the zone of maximum line 20, characterized the ins bit. Accordingly to this circumstance, the most preferred design is a turbine stage pressure which has maximum efficiency (line 22) in the real range of sustainable modes of its rotor.

Claims

Vortex stage pressure turbine of the turbo-drill, consisting of a stator hub pressure stage and the stator blade of the crown having an inner rim, and the slope of the chord of the profile of the stator blades of the crown to the plane perpendicular to the axis of the pressure stage of the turbine, does not exceed 50, and a rotary pressure, consisting of a hub and a rotor blade of a crown having an outer rim, characterized in that the line that defines the rear of the installation angle of the blades of the rotor blade crown is inclined to the plane perpendicular to the axis of the pressure stage of the turbine, at an angle from 40 to 80while external obverse surface of the blades of the rotor blade of the crown is convex and shaped by one or more radii, smoothly connecting the front clipped output edges of the blades with their input rounded edges, the centers of these radii are from the

 

Same patents:

The invention relates to gyratory hydraulic motors and pumps including multi-stage screw mechanisms, in particular to devices for drilling directional wells

The invention relates to the drilling of directional wells, in particular to a hydraulic downhole motors with turbine diverters

The invention relates to the drilling technique, namely downhole motors for drilling wells

Downhole motor // 2232244
The invention relates to the drilling technique, namely, downhole motors, designed for drilling and maintenance of oil and gas wells

The invention relates to the field of drilling, in particular, to a downhole motors

The invention relates to the field of drilling, in particular, to a downhole motors

The invention relates to hinge devices downhole motors designed for drilling of oil and gas, inclined and horizontal wells

The invention relates to hinge devices screw gyratory hydraulic machines and can be used in downhole motors for drilling and screw pumps for pumping fluid from the inclined and horizontal wells

The invention relates to the field of engineering, and in particular to equipment for servicing hydraulic downhole motors (HDM), and is designed for running and testing HDM both new and after repair

Ball bearing // 2224867
The invention relates to equipment for drilling oil and gas wells, in particular to nodes downhole motors, resulting in a rotation of the bit, destroying the well bottom

FIELD: oil and gas extractive industry.

SUBSTANCE: device has metallic hubs of stator and rotor, wherein crowns of stator and rotor are concentrically pressed. Crowns of stator and rotor are made of durable ceramics and are additionally equipped with connections, allowing to exclude non-controlled turning of crowns in hubs and spontaneous axial displacement thereof.

EFFECT: higher reliability and efficiency.

2 dwg

FIELD: mining industry.

SUBSTANCE: method includes physical-chemical treatment of metallic body parts, made in form of two half-cylinders, placement of puncheon within them, preparation of fresh rubber mixture, heating press-form up to 1502C, with following vulcanization of rubber mixture, detaching press-form, removing puncheon and controlling manufacture. Three compounds of rubber mixture are prepared, with following calendaring thereof on shafts and preparing fresh rubber strip of each compound, 0.5-0.6 mm thick, which prior to placement of puncheon in half-cylinders is wound in halving fashion onto the latter. Of rubber strip of compound, providing for durability, inner layer of rubber winding is made, of compound strip, providing for auto-compensation of wear - middle layer, and of strip, providing for hardness of connection between resin and half-cylinders - outer layer. Each layer of rubber winding is made of thickness, determined from relation khw, where h - thickness of each winding layer, mm; k - coefficient, determined empirically, equal to 30-0.35 for inner layer, 0.50-0.60 for middle layer, 0.10-0.15 for outer layer; hw - total thickness of rubber mixture winding, mm. glue covering is applied to each layer and rolled under pressure. After heating of press-form, the latter is placed into one of half-cylinders. Puncheon with rubber winding is deployed and connected to second half-cylinder. After vulcanization and removal of puncheon, rubber-metallic portion of stator is fixed in body pipe.

EFFECT: higher durability and simplified maintenance.

4 cl, 2 dwg, 5 ex

Face engine // 2248436

FIELD: oil and gas industry.

SUBSTANCE: device has turbine module, screw gear couple, including stator and rotor, assembly for connection of rotor of screw gear couple to turbine module and spindle, according to invention, rotor of screw gear couple has pass channel, into which a valve is mounted, including locking element and saddle, while locking element is mounted on resilient element with space to saddle surface and with possible contact with saddle surface. When engine is launched whole flow of drilling mud skirts screw gear couple through pass channel in rotor and open valve, i.e. through space between locking element and saddle surface and is directed into turbine module. In face engine loads on elements of gear couple are decreased during its launch due to redistribution of flows of working liquid between screw gear couple and turbine.

EFFECT: higher reliability, higher durability.

2 cl, 3 dwg

Gear mechanism // 2250340

FIELD: mechanical engineering.

SUBSTANCE: rotor axis of gear mechanism, performing a planetary movement, is displaced relatively to stator axis for distance of engagement eccentricity. As source auxiliary contour ellipse is used, while proportional coefficient k, determining radius of guiding circle, is taken equal to half necessary number of teeth z of wheel (k = z/2), optimal shape of its teeth is provided by rational combination of ellipse shape coefficient λ, equal to relation of lengths of its semi-axes and eccentricity coefficient of auxiliary contour, in form of relation of length of greater ellipse semi-axis to rolling circle radius, while inner and outer profiles are made in form of elliptic profiles from common ellipse contour.

EFFECT: simplified manufacture.

3 cl, 11 dwg

FIELD: oil and gas industry.

SUBSTANCE: roller tracks at edge inner and outer rings are made on same side, roller tracks at inner and outer rings are made with possible contact of balls with roller tracks of inner and outer rings at angle, greater than 45°, angle being formed by line, passing through points of contact of balls with roller tracks of inner and outer rings and line, perpendicular to longitudinal axis of bearing, profile of roller tracks on inner and outer rings is made from inequality condition D1 > (Din + Dout)/2, where D1 - diameter of circle passing through centers of balls in assembled bearing, Din - inner diameter of inner ring, Dout - outer diameter of outer ring, hardness of inner and outer rings being greater than 48 HRC, application point of radius of roller tracks profile on inner rings is placed in plane of stopping end of inner ring.

EFFECT: higher durability and reliability.

4 dwg

Boring rig // 2255194

FIELD: oil and gas well boring equipment.

SUBSTANCE: boring rig comprises turbodrill, drill bit and reducer including several planetary mechanisms and installed in-between. Sun gears of both planetary mechanisms are secured to turbodrill rotor shaft. Carrier with plane pinion axes of upper planetary mechanism is connected to boring rig body. Ring gear is attached to upper link of drill bit. Ring gear of lower planetary mechanism is linked with plane pinion axes of upper planetary mechanism, carrier thereof is connected with lower link of drill bit.

EFFECT: increased efficiency due to increase in turbodrill rotor speed up to optimal value, reduced number of turbodrill steps and hydraulic resistance thereof, increased flushing liquid flow velocity, reduced reactive moment on turbodrill stator and pipe string.

1 dwg

FIELD: oil and gas well drilling equipment, particularly hydraulic downhole motors.

SUBSTANCE: device has screw bottomhole motor comprising sub and body for arranging operating tool sections. Tool sections are mating rotor and stator surfaces made in the form of multistart screw pair. Tangential current-speed and inlet drilling mud direction transducer is installed above screw pair. The transducer comprises body, retaining ring and sealing collar. Blades of the transducer are right-handed (in opposition to helical teeth of the rotor and the stator).

EFFECT: increased mechanical penetration rate due to increased load applied to drilling bit without reduction in power and shaft torque indexes.

3 dwg

FIELD: drilling equipment, particularly for directional drilling, namely control devices adapted to control angle and reactive moment.

SUBSTANCE: control device has hollow central member and three hollow tubular noncoaxial members connected to hollow central member. Inner member is disposed in center between the first and the second members. The first and the second members are connected with inner members by threaded connection. The first member is connected to spindle by threaded coupling, the second member is attached to engine body by threaded coupling and central member is connected to inner member by spline. Each of central member and the first member are provided with sectional contact seats located from spindle connection side, wherein a pair of sectional contact seats arranged from either sides of meridional spindle plane in drilling string curvature plane are defined between central and the first members. Sectional contact seats defined between central and the first members are spaced a distance L from the nearest edges of sectional contact seats of central and the first members along central axis of the first member. The distance L is more or equal to spindle diameter D. Angular deviation of the sectional contact seat formed in the first member from meridian spindle plane in drilling string curvature plane is oppositely directed relative reactive drilling bit moment.

EFFECT: increased stability and angle of gerotor engine deflection and increased accuracy of non-uniform well bottom zone penetration.

2 cl, 10 dwg

FIELD: well drilling equipment, particularly bearings adapted to work in abrasive medium.

SUBSTANCE: radial bearing has body and shaft, as well as thrust collars secured in the body and spring-loaded holders arranged between the shaft and the body. Inserts with conical outer surfaces are located between the holders and the shaft so that inserts cooperate with the shaft and with inner surfaces of the holders. Radial bearing is made as two oppositely arranged blocks and as compression spring inserted in-between. Each block has stop member secured in the body and made as slotted bush. Inserts are arranged in the bush and may perform displacement in radial direction. Thrust collars have conical surfaces cooperating with outer surfaces of the inserts. Angles α at apexes of the cones defined by interacted conical surfaces of bearing support inserts, thrust collars and holders are correlated with friction coefficient μ of interacted surfaces as tg(α/2)≈μ. Insert surfaces cooperating with shaft surface may have coating of elastomeric or hard-alloy material. In accordance with the second embodiment surfaces of inserts, thrust collars and holders interacting one with another may have flat contact zones, which are inclined at (α/2) angle to longitudinal shaft axis.

EFFECT: increased operational reliability of radial bearing.

6 cl, 3 dwg

FIELD: oil and gas well drilling equipment with the use of hydraulic downhole motors.

SUBSTANCE: support-and-centering member is made as metal hub with blades connected to spindle connector. Spindle connector has support cone formed on outer surface thereof and adapted to provide rigid connection with metal hub from inner surface thereof. Support cone of the connector is formed from side of conical thread connecting spindle body with connector. Spindle connector has splines to connect thereof with metal hub. Metal hub is pressed with pressing cone, retaining washer and nut from another side thereof. Metal hub may be installed concentrically or eccentrically to spindle connector axis or outer surface thereof may be differently shaped and arranged eccentrically, concentrically or obliquely with respect to spindle connector axis.

EFFECT: reduced costs of spindle usage.

5 dwg

Up!