CA2068398A1 - Multiple stage drag and dynamic turbine downhole motor - Google Patents
Multiple stage drag and dynamic turbine downhole motorInfo
- Publication number
- CA2068398A1 CA2068398A1 CA002068398A CA2068398A CA2068398A1 CA 2068398 A1 CA2068398 A1 CA 2068398A1 CA 002068398 A CA002068398 A CA 002068398A CA 2068398 A CA2068398 A CA 2068398A CA 2068398 A1 CA2068398 A1 CA 2068398A1
- Authority
- CA
- Canada
- Prior art keywords
- turbine
- flow
- turbine blades
- blades
- shaft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 239000012530 fluid Substances 0.000 claims abstract description 24
- 238000005553 drilling Methods 0.000 description 7
- 125000006850 spacer group Chemical group 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000000295 complement effect Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- BLFWHYXWBKKRHI-JYBILGDPSA-N plap Chemical compound N([C@@H](CC(C)C)C(=O)N[C@@H]([C@@H](C)CC)C(=O)N[C@@H](C)C(=O)N[C@@H](CCCCN)C(=O)N[C@@H](C(C)C)C(=O)N[C@@H](CC(C)C)C(=O)N[C@@H]([C@@H](C)O)C(=O)N[C@@H]([C@@H](C)O)C(=O)N[C@@H](CCC(O)=O)C(=O)N1[C@@H](CCC1)C(=O)N1[C@@H](CCC1)C(=O)N[C@@H]([C@@H](C)CC)C(=O)N[C@@H]([C@@H](C)CC)C(=O)N[C@@H]([C@@H](C)O)C(=O)N1[C@@H](CCC1)C(=O)N[C@@H](C(C)C)C(=O)N[C@@H](CCCNC(N)=N)C(=O)N[C@@H](CCCNC(N)=N)C(O)=O)C(=O)[C@@H]1CCCN1C(=O)[C@H](CO)NC(=O)[C@@H](N)CCC(O)=O BLFWHYXWBKKRHI-JYBILGDPSA-N 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Classifications
-
- E—FIXED CONSTRUCTIONS
- E21—EARTH OR ROCK DRILLING; MINING
- E21B—EARTH OR ROCK DRILLING; OBTAINING OIL, GAS, WATER, SOLUBLE OR MELTABLE MATERIALS OR A SLURRY OF MINERALS FROM WELLS
- E21B4/00—Drives for drilling, used in the borehole
- E21B4/02—Fluid rotary type drives
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B13/00—Adaptations of machines or engines for special use; Combinations of machines or engines with driving or driven apparatus; Power stations or aggregates
- F03B13/02—Adaptations for drilling wells
Landscapes
- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Mechanical Engineering (AREA)
- Geology (AREA)
- Mining & Mineral Resources (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Environmental & Geological Engineering (AREA)
- Fluid Mechanics (AREA)
- General Life Sciences & Earth Sciences (AREA)
- Geochemistry & Mineralogy (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE
A multistage turbine is provided for driving a downhole motor (1), which is driven by the flow of a fluid therethrough. The turbine comprises a housing (3) and a shaft (5) positioned in the housing, the shaft rotating about the longitudinal axis thereof. A plurality of turbine stages (9) are mounted on the shaft for rotation therewith, each turbine stage including a rim (15) coaxial with the shaft and a plurality of turbine blades (13) fixed to the rim. A plurality of flow directing stators (11) are positioned between adjacent turbine stages, each of the stators having a wall portion and diverter portion (17, 19), wherein the wall portions are perpendicular to the axis of the shaft and the diverter portions are at an angle of less than 90° with respect to the axis of the shaft. At least one of the turbine blades and the diverter portions form a seal for preventing the flow from passing therebetween, such that flow through a turbine stage is perpendicular to the axis of the shaft in the space between adjacent wall portions and wherein the diverter portions are positioned with respect to said wall means for diverting flow from the turbine stage to an adjacent turbine stage.
The turbine blades are positioned between adjacent stators such that flow between the wall portion of adjacent stators contacts the edges of the turbine blades, thereby imparting a drag force on the turbine blades and flow through adjacent diverter portions impinges upon the face surface of the turbine blades, thereby imparting a dynamic force on the turbine blades, whereby the turbine blades are rotated by the combination of the drag forces and dynamic forces thereon.
A multistage turbine is provided for driving a downhole motor (1), which is driven by the flow of a fluid therethrough. The turbine comprises a housing (3) and a shaft (5) positioned in the housing, the shaft rotating about the longitudinal axis thereof. A plurality of turbine stages (9) are mounted on the shaft for rotation therewith, each turbine stage including a rim (15) coaxial with the shaft and a plurality of turbine blades (13) fixed to the rim. A plurality of flow directing stators (11) are positioned between adjacent turbine stages, each of the stators having a wall portion and diverter portion (17, 19), wherein the wall portions are perpendicular to the axis of the shaft and the diverter portions are at an angle of less than 90° with respect to the axis of the shaft. At least one of the turbine blades and the diverter portions form a seal for preventing the flow from passing therebetween, such that flow through a turbine stage is perpendicular to the axis of the shaft in the space between adjacent wall portions and wherein the diverter portions are positioned with respect to said wall means for diverting flow from the turbine stage to an adjacent turbine stage.
The turbine blades are positioned between adjacent stators such that flow between the wall portion of adjacent stators contacts the edges of the turbine blades, thereby imparting a drag force on the turbine blades and flow through adjacent diverter portions impinges upon the face surface of the turbine blades, thereby imparting a dynamic force on the turbine blades, whereby the turbine blades are rotated by the combination of the drag forces and dynamic forces thereon.
Description
r , . . ~ . ' r A f ~ !
20~8398 .. . .
MULTIPLE STAGE DRAG AND DYNAMIC TURBIN~ DOWNHOLE MOTOR
BACKGROUND OF THE INVENTION
Field of the Invention The present invention is directed to a multiple stage turbine for use as a downhole motor on a drilling string, and more particularly, to a multiple stage turbine downhole motor which is driven by the drag or shear stress force alone or in combination with the dynamic or impulse force of the fluid flowing through the turbine.
De~oription of the Prior Art Prior art downhole motors for use on drilling strings convert the kineti¢ energy of a mass of a fluid against the face surface of turbine blades into power for turning a drill string and thereby a drill bit attached to the bottom of the drill string. The turbines rely solely on the dynamic or impulse force. Prior art downhole motors of this type are generally required to be relatively long in order to have 6ufficient turbine blade surface area for generating enough power to turn the bit at the proper speed with sufficient torque. However, because the downhole motor itself i5 quite long, it i8 difficult for the drill string to move through curves and thus it i5 much more difficult to control the direction of drilling.
Another disadvantage of the dynamic force type downhole motors, is that maximum power and efficiency occur at rather high rotational speed ; higher than the range of operational speed for most mechanical drill bits, like tricone bits. The reason for this characteristic is that the functions of power and efficiency, in terms of the velocity of the flow is proportional to the square of the velocity. The function i5 a parabola in which the apex i~ approximately midway between zero and runaway or no load speed. -~ "~
~ ,"~",,,,~.~.,a?,". ~ ~
~., Still another disadvantage of prior a~t downhole turbine motors is that the turbine blades are internal with respect to the drilling shaft. In order to drive the turbine, fluid must flow through the internal structure of the drill string and can cause damage to the bearings, seals and other internal parts of the downhole motor.
SUMMARY OF THE INVENTION
A helical multiple impulse hydraulic downhole motor i~ described in my prior U. S. patent application Serial No.
045,822, filed May 4, 1987, now abandoned. This appllcation is incorporated herein by reference.
It is the primary ob;ect of the present invention to provide a multiple stage turbine which operates by using the shear force o~ the ~luid on the edges of the blades of the turbine either alone or in combination with the impulse force of the fluid on the surface of the blades.
It i8 another ob~ect of the present invention to provide a downhole motor for use in turning a drilling string, and thereby a drill bit on the end of the drill string, which operates at a relatively 810w speed of 300 - 500 rpm and produces high torque, with no torque on the plpe of the drill string itself.
It i8 another object of the present invention to provide a multiple stage turbine in which the xotor having the turbine blades, is external to the drilling sha~t and thus the moviny parts are external to the drilling shaft. Further, because the blades are attached to an external movable part, the generated ~orces are farther away from the axis of the turbine, giving more leverage and hence more torque.
The present invention ~s directed to a multistage turbine for driving a downhole motor, which is driven by the flow of a fluid therethrough. The turbine comprises a housing with a plurality of rims and a shaft positioned in the housing, ~,~"",, ~,s`,.~'~'~,`',;,.,.,,.`."" "''' .~
the housing and rims rotating about the longitudinal axis thereof. A plurality of turbine stages are mounted on the housing for rotation therewith, each turbine stage including a rim coaxial with the shaft and a plurality of turbine blades fixed to each rim. A plurality of flow directing stator~ are positioned between ad~acent turblne stages, each of the stators having a wall portion and diverter portion, wherein the wall portions are perpendicular to the axis of the shaft and the diverter portions are at an angle of less than 90- with respect to the axis of the ihaft. At lea3t three of the turbine blades and the diverter portions form a ~ieal for preventing the flow from passing therebetween, such that flow through a turbine stage i8 perpendicular to the axis of the shaft in the space between adjacent wall portions and wherein the diverter portions are positioned with respect to said wall means for diverting flow from the turbine stage to an ad~acent turbine stage.
The turbine blades are positioned between adjacent stators such that flow between the wall portion of adjacent sta~ors contacts the edges of the turbine blades, thereby imparting a drag force on the turbine blades and flow through ad~acent diverter portions impinges upon the face surface of the turbine blades, thereby imparting a dynamic force on the turbine blades ! whereby the turbine blades are rotated by the combination of the drag forces and dynamia forces thereon.
B~ DESCRT~ION OF TH~ PRAWIN~
Figure l is a sectional view of a downhole motor of the present invention.
Figure la is an expanded view of a portion of Figure l.
Figure lb is a sectional view through Section lb-lb in Figures 1 and la.
Figure 2 i6 a perspective view of the flow through a turbine of the present invention.
.` ~. .
Figures 3a and 3b are diagrams for analyzing the flow and forces in a turbine of the present invention.
Figure 4 is a partial sectional view of a turbine of a first embodlment of the present invention.
Figure 5 i~ a perspective view of a rotor stage of the present invention.
Figure 6 is a front view of the rotor stage of Figure 5.
Figure 7 is a perspective view of a stator of the fir~t embodiment of the present invention.
Figure 8 is a perspective view of an alternate embodiment of a stator of the pre~ent invention.
Figure 9 is a partial layout illustrating the flow of fluld through a first embodiment of the turblne of the present invention.
Figure 10 i3 a partial layout illustratlng the flow of fluid through a second embodiment of the turbine of the present invention.
Figure 11 is a partial sectional view of a turblne of a second embodiment of the pres~nt invention.
Figure 12 is a perspective view of the stator of the ~econd embodiment of the present invantion.
Figure 13 i8 a front view of the stator of Figure 12.
Figure 14 is a bottom view of the stator of Figure 12.
Figure 15 is a partia~ layout illustrating the flow o~ fluid through a third embodiment of the turbine of the pre~ent invention.
Figure 16 is a partlal layout illustrating the flow of ~luid through a fourth embodiment of the turblne of the present inventlon.
Figure 17a iB a partial sectional view of a fifth embodiment of the turbine of the present invention.
Figure 17b is a partial sectional view of Section 17A-17A' of Figure 17a.
.
~; 206~398 ,. .` .
Figure 17c i8 a sectional view of Section 17B-17~' of Figure 17b.
Figure 17d is a perspective view of the turbine rotor of the fifth embodiment of the present invention.
Figures 18a and 18b are partial layouts illustrating the intermediate seal for the drag and dynamic embodiment of the present invention.
The present invention is directed to a multiple stage turbine which comprises a plurality of single stages, each of which operates on the principle of the shear stre~s of fluid flowing in passages or spaces in the stage against the edges of the turbine blades which generate drag forces either alone or in combination with impulse forces of the fluid against the surface of the blades. The volume of ~low is not a factor as to the drag force or the shear forces on the edges o~ the turbine blades. The power produced by the drag force i8 a function of the relative velocity and drag surface, the drag surface being the edges of the turbine blades, and not the surface or face of the blade itself. The use of the drag force results in a higher torque then a conventional turbine rotor of the same dimensions. This enables the motor of the present invention to generate sufficient torque using less stages, which ln turn enables it to be shorter in length than a conventional turbine motor.
Figure 1 i6 an elevational view o~ a downhole motor 1 which comprises an outer casing 3 and an inner shaft 5. The motor further includeR a bearing assembly 7 and a turbine a3sembly 9 having a plurality of stages, each stage having a stator and rotor assembly. Each stator assembly comprises a plurality of flow directing stators 11 and each rotor assembly comprises a plurality of turbine blades 13 which are fixed to a rotor rim 15.
.
~ 'A,,'G~
206~398 A plurallty of turbine rotors 13 are pre-loaded and held together by means o~ nuts 28 and 29 located at the ends of the downhole motor. A drill bit (not shown) may be connected to nut 28. These nuts also hold the bearing assembly 7 in place. The bearings 7 may be tapered journal bearings or other types of bearings such as ball bearings. If necessary, nuts for holding the assembly together can be used as intermediate portions of the motor. Block 31 provides separation between the bearlng assembly 7 and the turbine assembly 9 and forms a seal therebetween. Block 31 can also be used to house a pressure aompensator for the bearing lubrication system, should such pres3ure compensation be necessary.
Referring to Figures I, la and lb, fluid, the flow of which is illustrated by arrows Fl - F7, flows through the downhole motor 1 as shown. Flow starts at Fl - F3 axially through the center of shaft 5, between F3 and F4, the fluid flowe through a plurality of slots 33 in the shaft 5. ~etween F4 and F5, the fluid flows through the turbine as~embly 9, rotating the turbine blades 13 and the outer casing 3. End piece 28 is screw-threaded into outer casing 3 and tightened against blades 13 to thereby cause the blade 13 to rotate with the outer casing 3. At F5 - F6, the fluid then flows out of the turbine assembly 9 and into the Rhaft 5 through additional slots 35, which are the same as slots 33, and then exits from the downhole motor into the bore hole. As can be seen, the turbine as~embly is mounted on the outside of the shaft 5, thus, the moving parts are external to the drill shaft.
Figure 2 shows the flat helical flow path through a turbine assembly 9. The turbine assembly i8 mounted on a shaft 5. The turbine assembly includes a plurality of flow dire¢ting stators 11 fixed to the shaft 5, with a plurality of turbine blades 13 being fixed to the corresponding rotor rim 15 being positioned to rotate between ad~acent stators 11 ~See Figure 1).
A seal is formed between flow directing portions l9b and l9a and æ~
the turbine blades 13 so that the flow F is circular in the channel or space formed between ad~acent stators 11 and then flows through the channel or space between the flow diverters 17a and 17b and l9a and lsb into an adjacent turbine stage between the next adjacent stators 11. Thus as can be seen, the flow follows a ~lat circular path through almost an entire 360-and then a somewhat helical path diagonally downward into the next turbine stage. The drag forces and impulse forces applied to the turbine blades by the flow through the turbine will depend upon the configuration of the turbine blades 13 and the stators 11 as will be explained in more detail below.
The turbine of the present invention is driven by the shear ~tress or drag force in combination with the dynamic or lmpulse force of the fluid flowing through the turbine. The drag force is generated by the flow of fluid against thc edges of the turbine blades. The dynamia for¢e is generated by the impa¢t of the flow against the surface of the face of the turbine blades as its flows through the rotor blades at the entrance and the outlet of each turbine stage.`
The total force acting on the rotor i8:
FT = Fdr ~ Fdy . . . (1) where:
Fdr = shear force or drag force Fdy = impulse or dynamic force The drag force i9 ag follOW8:
Fdr 2 ~ Adr adru(C - u)2/2g . . . (2) where:
= specific weight of the fluid (Kgf/m3).
Adr = drag coefficient (dimensionless) ~rom rotor blades and channels geometrical configuration.
C = mean velocity of the flow through the drag channels (m/sec).
u = peripheral velocity o~ the rotor (m/sec).
~' .,~
.....
adr = drag area upon which the shear stress acts (m).
The dynamic force can be calculated with reference to Figure 3a which is a section of the rotor blades, transverse to the axis of rotation wherein: ;
u = tangential velocity of the rotor (m/sec).
wl - relative velooity o~ the flow (m/sec).
~1 = angle of w1 with the direation u (degrees).
C1 - absolute velocity, vectorial addition of of u and W1.
~1 = angle of c, with the direction of u.
wx1 - component o~ w1 in the direction of movement The ~ubscript "1" corresponds to the inlet of the flow for every change of direction through the blade assembly.
20 l~ The subscripts "2" are used to denote the aorresponding values of the flow at the outlet of every change of direction, generating a hydraulic impulse.
In order to deduce or obtain the equation for the dynamic force, referring to Figure 3b, shows the composition of the triangles of velocities at the inlet and outlet o~ the flow at every impul~e or change of direction.
According to Newton's Secon~ Law:
Fdy - p Q ~Wxl ~ Wx2) wherelns wx1 and WX2 are the components of the relative veloaltie~ in the direction of the movement.
p - specific mass = y g Then:
WX1 = C1 C08~rl u Wx2 = Cm2 ~ tanP,2 = Cm1 ~ tanfl2. ...
= C1 sin~1 ~ tan~2-` 206~398 .~
. .`. . .
and Fdy ~ m p Q[(Clcosal - u) + C1sinul/tan~2] . . (3) wherein:
m = number of changes of direction or impulses in each stage.
Referring to Figures 4 - ~, it can be seen that the blades 13 are fixed to rotor rims 15. Although only four blades are ~hown, the remaining blades are positioned around the entire rim 15. When a plurality of rotor assemblies are used as shown in Figure 1, the rim 15 can have a width equal to the width o~
the turbine blades 13 and a spacer 151 can be positioned ad~acent to the rim 15. Alternatively, the rim 15 can be made wider than the blade 13 so that the spacer ~5' is an integral portion thereof. Figure 6 is an elevation view taken in plane 6-6 of Figure 5 showing the orientation of blades 13 with respect to rim 15 and the center of rim 15. Although the blades 13 are ~hown in a V-shape cros~-se¢tion, other cross-sectlons aan be used suoh as a rounded V, offcenter V, a combination of round and offaentered Vs, etc.
Figure 7 ls a perspective view of a flow directing stator 11. Stator 11 has wall portions 25 and flow diverting portions 17a and 17b and l9a and l9b. Flow diverting portions 17a and l9a form seals with ad~acent turbine blades 13, as shown as ln Figure 2. Although the seal is not a perfect seal ~ince it is necessary for the turbine blades to rotate, the seal substantially stops the flow of fluid thereby maintaining the proper flow path through the turbine assembly as will be described below. The stator 11 further comprises a hub 21 having a keyway 23 for receiving the key 6 when the stator is mounted on the sha~t 5. The stator assembly further lncludes a wall portion 25 integrally formed with the flow directing portions. As shown in Figure 4, a ~pace 27 is formed between wall portion 25 and spacer 15'. The space 27 is made very ~mall ~`'~'' ` 2068398 .. ..
80 that the flow of fluid through the space i8 negligible, but the space is sufflcient to permit the rotation of rotor 13 with respect to stator 11.
Figure 8 is an alternative embodiment of the stator 11 in which the hub 21 has a reduced diameter port~on 21a. The length or angle of the reduced portion will depend upon the particular flow characteristics but generally will be les~ than 90'. The purpose of the reduced hub radius is to allow the fluid to flow under the blades 13c, thereby eliminating the impulse forces on blades 13c and to quickly equalize the flow on both sides of the blades 13d. If desired, the sharp corners between surfaces 17a and 17b, and l9a and l9b can be rounded in order to smooth the flow and reduce turbulence.
Figure 9 is a partial layout illustrating the flow of fluid through two blade assemblies 13 in a first embodiment of the turbine of the present invention. The arrows F show the flow and the arrows D and I illustrate the drag and dynamic foraes on the turbine blade~ 13. Starting from the right, the flow F aauses a drag force D on the edges of the turbine blades 13. When the flow reache~ surface 17b, it is diverted downward as shown, striking the blades 13a and applying a dynamic force I to the blades 13a. Flow then continues through flow diverters l9a and l9b into the ad~acent stage of turbine blades and again dynamic forces I are applied to blades 13a. Flow then continues towards the left where only drag forces are applied to the edges of the blades 13.
Figure 10 is a partial layout illustrating the flow oP fluid through a second embodiment of the turbine of the present invention in which three impulses are produced in each stage. The arrows F show the flow and the arrows D and I
illustrate the drag and dynamic on the turbine blades 13.
Starting from the right, the flow F causes a drag force D on only one edge of the turbine blades 13. In the embodiment of Figure 8, the turbine blades are configured 80 that the drag ~ ' .
force is on both edges of the blades. When the flow reaches surface 17b it is diverted downward, as shown, striking the blades 13a and applying a dynamic force I to the blades 13a.
The flow then continues through flow diverter~ l9a and l9b into the ad~acent stage of turbine blades 13 and again dynamic forces are applied to blades 13a.
In the embodiment of Figure 10, there are three changes of direction so three impulses are generated in every stage. In the equation (3), in this case the value of parameters "m" would be three.
Figures 11 - 15 illustrate a third embodiment of the turbine of the present invention. In Figure 11, flow directing stators 111 include diverter portions 117a, and 117b and ll9a and ll9b and wall portions 125. The turbine blade stages 113 are the same as those described in the embodiment of Figures 4 -6.
Figure 12 i8 a perspective view of the flow directing stator 111. The stator 111 comprises a hub 121 with a keyway 123 and a wall portion 125. The wall portion 125 has a plurality of sections 125a - 125k ~not shown in Figure 12) which can be seen in Figure 13 which is a full-layout of a plurality of flow directing stators and turbine blade stages. Figure 13 i8 an elevational view in plane 13-13 of Figure 12, and Figure 14 i3 a side view of Figure 13 in plane 14-14. The surfaces of diverter portions 117 and wall portions 125 in the correspondin~J
Figures 11 - 15, have been designated by letters A - G.
The flow through the turbine in the embodiment of Figures 11 - 15 is illustrated by the arrows F in Figure 15.
This flow causes impulse forces on the outer halves 113a of the turblne blades 113. The inner halves 113b of the turbine blades 113 do not have any significant forces acting thereon, but rather, act with corresponding diverter wall portions 125a, 125e and 125i to form a substantial seal therebetween. The seals ensurs that the flow i3 as indicated by arrows F, rather than ~¢`'~''}j~}f'Q~
206~398 . . .
through the space between the turbine blades and the wall portions 125a, 12se and 125i. ~he impulse fGrces on the turbine blades 113a are the same impulse forces described above with respect to the embodiment of Figures 4 - 9. As can be seen however, in this embodiment there are no substantial drag forces on the turbine blades. The lack of substantial drag forces occurs because centrifugal force on the flow moves the fluid towards the outside again~t wall portion~ 125c, 125k and 125g which are away from the edges of the turbine blade~. This embodiment i8 the limit for the dynamic force, because "m" has been increased to provide the maximum dynamic force.
Figure 16 shows a fourth embodiment of the turbine of the present invention. In this embodiment, the blades 213 are alternately attached to the outside rotor rim (not shown). A
sealing wall members form a seal with one side of blades 213, and the other side of blades 213 form a seal with stator 211.
Flow i9 in one direction around the annular space and is almost 360' at which point it flows through the outlet into the next stage. The sinuous path of the flow F produces drag forces D
on the tips or edges of the blades 213 and additionally produces impulses I on the surface~ of the blades. The drag and dynamic forces can be calculated in accordance with the equations set ~orth above. However, since the path is not very well defined, the equations have to be effected by coefficients determined experimentally.
Instead of blade~, planar or rounded bodies ¢an be used and attached to the rotor rim to eliminate eddy currents and turbulence and to enhance impulses on the slanted surfaces to produce the desired number of smooth changes of direction along the annular channels.
Figures 17a - 17d illustrate a fifth embodiment of the turbine of the present invention. In this embodiment, the turbine is substantially a pure drag turbine which i~ simple, versatile, has high torque and a comparatively high efficiency.
. . .`, .
... .
Additional turbine blades can be added to produce additional forces either drag forces or dynamic forces to modify the performance of the turbine, iP desired.
Referring to Figures 17a - 17d, the flow indicated the arrow F, flows through the turbine with the intermediate seal 315 at the diagonal entrance of the next stage. The turbine has blades 313 which contact seals 315. The seal 317a and the diagonal diverter divert the flow through opening 317 in the wall of stator 311. The flow channel i~ cylindrical and covers almost 360~ and is coaxial and parallel with the cylindrical space covered by the rotor and its blades. In other words, the flow i8 cylindrical and intermediate between the edges of the blades and the internal hub, a~ shown in Figure 17c.
The blade length, thickness, angle of inclination, as well as separation between blades, can be varied. All of these variables affect the drag coefficient ldr and thus the ultimate drag foroe, velo¢ity and efficiency.
The drag action in this embodiment of the present invention i8 generally better than in the other embodiments of the present invention.
In the fifth embodiment, since the flow through the ohannels is cylindrical and parallel to the rotor and blades, the blades do not cross or deviate from the direction of the flow, to produce an impulse, except in the change of stages.
~he ohange oP direction of the flow from one staqe to the next is produced by the seal and stator and hence friotion 1088, and oorrespondingly hydraulio head loss are small.
The following is an explanation of the manner in which the intermediate seals operate in the present invention.
Considering one stage of the turbine with the drag and dynamic actions, such as in Figure 18a and 18b, which shows sohematically a section of the channel with seven changes of direotion. The rotor i~ shown divided in two portions; one is 2~683~8 : .
::
the seal portion in the change of stage, and the other is the complement portion for the rest of the rotor.
The equilibrium equations for each one of the those portions are: ~
+ ~ ;
se~l = PlAp + P7Ap - -~Pl - P7)Ap (seal portion) P1 and P7 are the pressures at the inlet and outlet of the stage, and Ap is the area o~ the blades on which the pressures act.
Fc~ = PlAp-P7Ap + Fdr + Fdy = (Pl-P7)Ap + Fdr + Fdy (complement portion) The total force acting on the rotor will be:
FT = ~ Fseal + ~ FC~P
( ~ P7)Ap + (Pl - P7)Ap + Fdr + Fdy FT ' Fdr + Fdy Thus, the forces coming from pressure acting on the section cancel each other.
Although the present invention is shown as a turbine, the principles o~ the invention can also be used for a pump, blower or compressor.
The present invention may be embodied in other speci~ic ~orms without departing from the spirit or essential oharacteristics thereof. The presently disclosed embodiments are therefore to ~e considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims, rather than the foregolng description, and all changes which come within the meaning and range of equivalency of the claim3 are, there~ore, to be embraced therein.
20~8398 .. . .
MULTIPLE STAGE DRAG AND DYNAMIC TURBIN~ DOWNHOLE MOTOR
BACKGROUND OF THE INVENTION
Field of the Invention The present invention is directed to a multiple stage turbine for use as a downhole motor on a drilling string, and more particularly, to a multiple stage turbine downhole motor which is driven by the drag or shear stress force alone or in combination with the dynamic or impulse force of the fluid flowing through the turbine.
De~oription of the Prior Art Prior art downhole motors for use on drilling strings convert the kineti¢ energy of a mass of a fluid against the face surface of turbine blades into power for turning a drill string and thereby a drill bit attached to the bottom of the drill string. The turbines rely solely on the dynamic or impulse force. Prior art downhole motors of this type are generally required to be relatively long in order to have 6ufficient turbine blade surface area for generating enough power to turn the bit at the proper speed with sufficient torque. However, because the downhole motor itself i5 quite long, it i8 difficult for the drill string to move through curves and thus it i5 much more difficult to control the direction of drilling.
Another disadvantage of the dynamic force type downhole motors, is that maximum power and efficiency occur at rather high rotational speed ; higher than the range of operational speed for most mechanical drill bits, like tricone bits. The reason for this characteristic is that the functions of power and efficiency, in terms of the velocity of the flow is proportional to the square of the velocity. The function i5 a parabola in which the apex i~ approximately midway between zero and runaway or no load speed. -~ "~
~ ,"~",,,,~.~.,a?,". ~ ~
~., Still another disadvantage of prior a~t downhole turbine motors is that the turbine blades are internal with respect to the drilling shaft. In order to drive the turbine, fluid must flow through the internal structure of the drill string and can cause damage to the bearings, seals and other internal parts of the downhole motor.
SUMMARY OF THE INVENTION
A helical multiple impulse hydraulic downhole motor i~ described in my prior U. S. patent application Serial No.
045,822, filed May 4, 1987, now abandoned. This appllcation is incorporated herein by reference.
It is the primary ob;ect of the present invention to provide a multiple stage turbine which operates by using the shear force o~ the ~luid on the edges of the blades of the turbine either alone or in combination with the impulse force of the fluid on the surface of the blades.
It i8 another ob~ect of the present invention to provide a downhole motor for use in turning a drilling string, and thereby a drill bit on the end of the drill string, which operates at a relatively 810w speed of 300 - 500 rpm and produces high torque, with no torque on the plpe of the drill string itself.
It i8 another object of the present invention to provide a multiple stage turbine in which the xotor having the turbine blades, is external to the drilling sha~t and thus the moviny parts are external to the drilling shaft. Further, because the blades are attached to an external movable part, the generated ~orces are farther away from the axis of the turbine, giving more leverage and hence more torque.
The present invention ~s directed to a multistage turbine for driving a downhole motor, which is driven by the flow of a fluid therethrough. The turbine comprises a housing with a plurality of rims and a shaft positioned in the housing, ~,~"",, ~,s`,.~'~'~,`',;,.,.,,.`."" "''' .~
the housing and rims rotating about the longitudinal axis thereof. A plurality of turbine stages are mounted on the housing for rotation therewith, each turbine stage including a rim coaxial with the shaft and a plurality of turbine blades fixed to each rim. A plurality of flow directing stator~ are positioned between ad~acent turblne stages, each of the stators having a wall portion and diverter portion, wherein the wall portions are perpendicular to the axis of the shaft and the diverter portions are at an angle of less than 90- with respect to the axis of the ihaft. At lea3t three of the turbine blades and the diverter portions form a ~ieal for preventing the flow from passing therebetween, such that flow through a turbine stage i8 perpendicular to the axis of the shaft in the space between adjacent wall portions and wherein the diverter portions are positioned with respect to said wall means for diverting flow from the turbine stage to an ad~acent turbine stage.
The turbine blades are positioned between adjacent stators such that flow between the wall portion of adjacent sta~ors contacts the edges of the turbine blades, thereby imparting a drag force on the turbine blades and flow through ad~acent diverter portions impinges upon the face surface of the turbine blades, thereby imparting a dynamic force on the turbine blades ! whereby the turbine blades are rotated by the combination of the drag forces and dynamia forces thereon.
B~ DESCRT~ION OF TH~ PRAWIN~
Figure l is a sectional view of a downhole motor of the present invention.
Figure la is an expanded view of a portion of Figure l.
Figure lb is a sectional view through Section lb-lb in Figures 1 and la.
Figure 2 i6 a perspective view of the flow through a turbine of the present invention.
.` ~. .
Figures 3a and 3b are diagrams for analyzing the flow and forces in a turbine of the present invention.
Figure 4 is a partial sectional view of a turbine of a first embodlment of the present invention.
Figure 5 i~ a perspective view of a rotor stage of the present invention.
Figure 6 is a front view of the rotor stage of Figure 5.
Figure 7 is a perspective view of a stator of the fir~t embodiment of the present invention.
Figure 8 is a perspective view of an alternate embodiment of a stator of the pre~ent invention.
Figure 9 is a partial layout illustrating the flow of fluld through a first embodiment of the turblne of the present invention.
Figure 10 i3 a partial layout illustratlng the flow of fluid through a second embodiment of the turbine of the present invention.
Figure 11 is a partial sectional view of a turblne of a second embodiment of the pres~nt invention.
Figure 12 is a perspective view of the stator of the ~econd embodiment of the present invantion.
Figure 13 i8 a front view of the stator of Figure 12.
Figure 14 is a bottom view of the stator of Figure 12.
Figure 15 is a partia~ layout illustrating the flow o~ fluid through a third embodiment of the turbine of the pre~ent invention.
Figure 16 is a partlal layout illustrating the flow of ~luid through a fourth embodiment of the turblne of the present inventlon.
Figure 17a iB a partial sectional view of a fifth embodiment of the turbine of the present invention.
Figure 17b is a partial sectional view of Section 17A-17A' of Figure 17a.
.
~; 206~398 ,. .` .
Figure 17c i8 a sectional view of Section 17B-17~' of Figure 17b.
Figure 17d is a perspective view of the turbine rotor of the fifth embodiment of the present invention.
Figures 18a and 18b are partial layouts illustrating the intermediate seal for the drag and dynamic embodiment of the present invention.
The present invention is directed to a multiple stage turbine which comprises a plurality of single stages, each of which operates on the principle of the shear stre~s of fluid flowing in passages or spaces in the stage against the edges of the turbine blades which generate drag forces either alone or in combination with impulse forces of the fluid against the surface of the blades. The volume of ~low is not a factor as to the drag force or the shear forces on the edges o~ the turbine blades. The power produced by the drag force i8 a function of the relative velocity and drag surface, the drag surface being the edges of the turbine blades, and not the surface or face of the blade itself. The use of the drag force results in a higher torque then a conventional turbine rotor of the same dimensions. This enables the motor of the present invention to generate sufficient torque using less stages, which ln turn enables it to be shorter in length than a conventional turbine motor.
Figure 1 i6 an elevational view o~ a downhole motor 1 which comprises an outer casing 3 and an inner shaft 5. The motor further includeR a bearing assembly 7 and a turbine a3sembly 9 having a plurality of stages, each stage having a stator and rotor assembly. Each stator assembly comprises a plurality of flow directing stators 11 and each rotor assembly comprises a plurality of turbine blades 13 which are fixed to a rotor rim 15.
.
~ 'A,,'G~
206~398 A plurallty of turbine rotors 13 are pre-loaded and held together by means o~ nuts 28 and 29 located at the ends of the downhole motor. A drill bit (not shown) may be connected to nut 28. These nuts also hold the bearing assembly 7 in place. The bearings 7 may be tapered journal bearings or other types of bearings such as ball bearings. If necessary, nuts for holding the assembly together can be used as intermediate portions of the motor. Block 31 provides separation between the bearlng assembly 7 and the turbine assembly 9 and forms a seal therebetween. Block 31 can also be used to house a pressure aompensator for the bearing lubrication system, should such pres3ure compensation be necessary.
Referring to Figures I, la and lb, fluid, the flow of which is illustrated by arrows Fl - F7, flows through the downhole motor 1 as shown. Flow starts at Fl - F3 axially through the center of shaft 5, between F3 and F4, the fluid flowe through a plurality of slots 33 in the shaft 5. ~etween F4 and F5, the fluid flows through the turbine as~embly 9, rotating the turbine blades 13 and the outer casing 3. End piece 28 is screw-threaded into outer casing 3 and tightened against blades 13 to thereby cause the blade 13 to rotate with the outer casing 3. At F5 - F6, the fluid then flows out of the turbine assembly 9 and into the Rhaft 5 through additional slots 35, which are the same as slots 33, and then exits from the downhole motor into the bore hole. As can be seen, the turbine as~embly is mounted on the outside of the shaft 5, thus, the moving parts are external to the drill shaft.
Figure 2 shows the flat helical flow path through a turbine assembly 9. The turbine assembly i8 mounted on a shaft 5. The turbine assembly includes a plurality of flow dire¢ting stators 11 fixed to the shaft 5, with a plurality of turbine blades 13 being fixed to the corresponding rotor rim 15 being positioned to rotate between ad~acent stators 11 ~See Figure 1).
A seal is formed between flow directing portions l9b and l9a and æ~
the turbine blades 13 so that the flow F is circular in the channel or space formed between ad~acent stators 11 and then flows through the channel or space between the flow diverters 17a and 17b and l9a and lsb into an adjacent turbine stage between the next adjacent stators 11. Thus as can be seen, the flow follows a ~lat circular path through almost an entire 360-and then a somewhat helical path diagonally downward into the next turbine stage. The drag forces and impulse forces applied to the turbine blades by the flow through the turbine will depend upon the configuration of the turbine blades 13 and the stators 11 as will be explained in more detail below.
The turbine of the present invention is driven by the shear ~tress or drag force in combination with the dynamic or lmpulse force of the fluid flowing through the turbine. The drag force is generated by the flow of fluid against thc edges of the turbine blades. The dynamia for¢e is generated by the impa¢t of the flow against the surface of the face of the turbine blades as its flows through the rotor blades at the entrance and the outlet of each turbine stage.`
The total force acting on the rotor i8:
FT = Fdr ~ Fdy . . . (1) where:
Fdr = shear force or drag force Fdy = impulse or dynamic force The drag force i9 ag follOW8:
Fdr 2 ~ Adr adru(C - u)2/2g . . . (2) where:
= specific weight of the fluid (Kgf/m3).
Adr = drag coefficient (dimensionless) ~rom rotor blades and channels geometrical configuration.
C = mean velocity of the flow through the drag channels (m/sec).
u = peripheral velocity o~ the rotor (m/sec).
~' .,~
.....
adr = drag area upon which the shear stress acts (m).
The dynamic force can be calculated with reference to Figure 3a which is a section of the rotor blades, transverse to the axis of rotation wherein: ;
u = tangential velocity of the rotor (m/sec).
wl - relative velooity o~ the flow (m/sec).
~1 = angle of w1 with the direation u (degrees).
C1 - absolute velocity, vectorial addition of of u and W1.
~1 = angle of c, with the direction of u.
wx1 - component o~ w1 in the direction of movement The ~ubscript "1" corresponds to the inlet of the flow for every change of direction through the blade assembly.
20 l~ The subscripts "2" are used to denote the aorresponding values of the flow at the outlet of every change of direction, generating a hydraulic impulse.
In order to deduce or obtain the equation for the dynamic force, referring to Figure 3b, shows the composition of the triangles of velocities at the inlet and outlet o~ the flow at every impul~e or change of direction.
According to Newton's Secon~ Law:
Fdy - p Q ~Wxl ~ Wx2) wherelns wx1 and WX2 are the components of the relative veloaltie~ in the direction of the movement.
p - specific mass = y g Then:
WX1 = C1 C08~rl u Wx2 = Cm2 ~ tanP,2 = Cm1 ~ tanfl2. ...
= C1 sin~1 ~ tan~2-` 206~398 .~
. .`. . .
and Fdy ~ m p Q[(Clcosal - u) + C1sinul/tan~2] . . (3) wherein:
m = number of changes of direction or impulses in each stage.
Referring to Figures 4 - ~, it can be seen that the blades 13 are fixed to rotor rims 15. Although only four blades are ~hown, the remaining blades are positioned around the entire rim 15. When a plurality of rotor assemblies are used as shown in Figure 1, the rim 15 can have a width equal to the width o~
the turbine blades 13 and a spacer 151 can be positioned ad~acent to the rim 15. Alternatively, the rim 15 can be made wider than the blade 13 so that the spacer ~5' is an integral portion thereof. Figure 6 is an elevation view taken in plane 6-6 of Figure 5 showing the orientation of blades 13 with respect to rim 15 and the center of rim 15. Although the blades 13 are ~hown in a V-shape cros~-se¢tion, other cross-sectlons aan be used suoh as a rounded V, offcenter V, a combination of round and offaentered Vs, etc.
Figure 7 ls a perspective view of a flow directing stator 11. Stator 11 has wall portions 25 and flow diverting portions 17a and 17b and l9a and l9b. Flow diverting portions 17a and l9a form seals with ad~acent turbine blades 13, as shown as ln Figure 2. Although the seal is not a perfect seal ~ince it is necessary for the turbine blades to rotate, the seal substantially stops the flow of fluid thereby maintaining the proper flow path through the turbine assembly as will be described below. The stator 11 further comprises a hub 21 having a keyway 23 for receiving the key 6 when the stator is mounted on the sha~t 5. The stator assembly further lncludes a wall portion 25 integrally formed with the flow directing portions. As shown in Figure 4, a ~pace 27 is formed between wall portion 25 and spacer 15'. The space 27 is made very ~mall ~`'~'' ` 2068398 .. ..
80 that the flow of fluid through the space i8 negligible, but the space is sufflcient to permit the rotation of rotor 13 with respect to stator 11.
Figure 8 is an alternative embodiment of the stator 11 in which the hub 21 has a reduced diameter port~on 21a. The length or angle of the reduced portion will depend upon the particular flow characteristics but generally will be les~ than 90'. The purpose of the reduced hub radius is to allow the fluid to flow under the blades 13c, thereby eliminating the impulse forces on blades 13c and to quickly equalize the flow on both sides of the blades 13d. If desired, the sharp corners between surfaces 17a and 17b, and l9a and l9b can be rounded in order to smooth the flow and reduce turbulence.
Figure 9 is a partial layout illustrating the flow of fluid through two blade assemblies 13 in a first embodiment of the turbine of the present invention. The arrows F show the flow and the arrows D and I illustrate the drag and dynamic foraes on the turbine blade~ 13. Starting from the right, the flow F aauses a drag force D on the edges of the turbine blades 13. When the flow reache~ surface 17b, it is diverted downward as shown, striking the blades 13a and applying a dynamic force I to the blades 13a. Flow then continues through flow diverters l9a and l9b into the ad~acent stage of turbine blades and again dynamic forces I are applied to blades 13a. Flow then continues towards the left where only drag forces are applied to the edges of the blades 13.
Figure 10 is a partial layout illustrating the flow oP fluid through a second embodiment of the turbine of the present invention in which three impulses are produced in each stage. The arrows F show the flow and the arrows D and I
illustrate the drag and dynamic on the turbine blades 13.
Starting from the right, the flow F causes a drag force D on only one edge of the turbine blades 13. In the embodiment of Figure 8, the turbine blades are configured 80 that the drag ~ ' .
force is on both edges of the blades. When the flow reaches surface 17b it is diverted downward, as shown, striking the blades 13a and applying a dynamic force I to the blades 13a.
The flow then continues through flow diverter~ l9a and l9b into the ad~acent stage of turbine blades 13 and again dynamic forces are applied to blades 13a.
In the embodiment of Figure 10, there are three changes of direction so three impulses are generated in every stage. In the equation (3), in this case the value of parameters "m" would be three.
Figures 11 - 15 illustrate a third embodiment of the turbine of the present invention. In Figure 11, flow directing stators 111 include diverter portions 117a, and 117b and ll9a and ll9b and wall portions 125. The turbine blade stages 113 are the same as those described in the embodiment of Figures 4 -6.
Figure 12 i8 a perspective view of the flow directing stator 111. The stator 111 comprises a hub 121 with a keyway 123 and a wall portion 125. The wall portion 125 has a plurality of sections 125a - 125k ~not shown in Figure 12) which can be seen in Figure 13 which is a full-layout of a plurality of flow directing stators and turbine blade stages. Figure 13 i8 an elevational view in plane 13-13 of Figure 12, and Figure 14 i3 a side view of Figure 13 in plane 14-14. The surfaces of diverter portions 117 and wall portions 125 in the correspondin~J
Figures 11 - 15, have been designated by letters A - G.
The flow through the turbine in the embodiment of Figures 11 - 15 is illustrated by the arrows F in Figure 15.
This flow causes impulse forces on the outer halves 113a of the turblne blades 113. The inner halves 113b of the turbine blades 113 do not have any significant forces acting thereon, but rather, act with corresponding diverter wall portions 125a, 125e and 125i to form a substantial seal therebetween. The seals ensurs that the flow i3 as indicated by arrows F, rather than ~¢`'~''}j~}f'Q~
206~398 . . .
through the space between the turbine blades and the wall portions 125a, 12se and 125i. ~he impulse fGrces on the turbine blades 113a are the same impulse forces described above with respect to the embodiment of Figures 4 - 9. As can be seen however, in this embodiment there are no substantial drag forces on the turbine blades. The lack of substantial drag forces occurs because centrifugal force on the flow moves the fluid towards the outside again~t wall portion~ 125c, 125k and 125g which are away from the edges of the turbine blade~. This embodiment i8 the limit for the dynamic force, because "m" has been increased to provide the maximum dynamic force.
Figure 16 shows a fourth embodiment of the turbine of the present invention. In this embodiment, the blades 213 are alternately attached to the outside rotor rim (not shown). A
sealing wall members form a seal with one side of blades 213, and the other side of blades 213 form a seal with stator 211.
Flow i9 in one direction around the annular space and is almost 360' at which point it flows through the outlet into the next stage. The sinuous path of the flow F produces drag forces D
on the tips or edges of the blades 213 and additionally produces impulses I on the surface~ of the blades. The drag and dynamic forces can be calculated in accordance with the equations set ~orth above. However, since the path is not very well defined, the equations have to be effected by coefficients determined experimentally.
Instead of blade~, planar or rounded bodies ¢an be used and attached to the rotor rim to eliminate eddy currents and turbulence and to enhance impulses on the slanted surfaces to produce the desired number of smooth changes of direction along the annular channels.
Figures 17a - 17d illustrate a fifth embodiment of the turbine of the present invention. In this embodiment, the turbine is substantially a pure drag turbine which i~ simple, versatile, has high torque and a comparatively high efficiency.
. . .`, .
... .
Additional turbine blades can be added to produce additional forces either drag forces or dynamic forces to modify the performance of the turbine, iP desired.
Referring to Figures 17a - 17d, the flow indicated the arrow F, flows through the turbine with the intermediate seal 315 at the diagonal entrance of the next stage. The turbine has blades 313 which contact seals 315. The seal 317a and the diagonal diverter divert the flow through opening 317 in the wall of stator 311. The flow channel i~ cylindrical and covers almost 360~ and is coaxial and parallel with the cylindrical space covered by the rotor and its blades. In other words, the flow i8 cylindrical and intermediate between the edges of the blades and the internal hub, a~ shown in Figure 17c.
The blade length, thickness, angle of inclination, as well as separation between blades, can be varied. All of these variables affect the drag coefficient ldr and thus the ultimate drag foroe, velo¢ity and efficiency.
The drag action in this embodiment of the present invention i8 generally better than in the other embodiments of the present invention.
In the fifth embodiment, since the flow through the ohannels is cylindrical and parallel to the rotor and blades, the blades do not cross or deviate from the direction of the flow, to produce an impulse, except in the change of stages.
~he ohange oP direction of the flow from one staqe to the next is produced by the seal and stator and hence friotion 1088, and oorrespondingly hydraulio head loss are small.
The following is an explanation of the manner in which the intermediate seals operate in the present invention.
Considering one stage of the turbine with the drag and dynamic actions, such as in Figure 18a and 18b, which shows sohematically a section of the channel with seven changes of direotion. The rotor i~ shown divided in two portions; one is 2~683~8 : .
::
the seal portion in the change of stage, and the other is the complement portion for the rest of the rotor.
The equilibrium equations for each one of the those portions are: ~
+ ~ ;
se~l = PlAp + P7Ap - -~Pl - P7)Ap (seal portion) P1 and P7 are the pressures at the inlet and outlet of the stage, and Ap is the area o~ the blades on which the pressures act.
Fc~ = PlAp-P7Ap + Fdr + Fdy = (Pl-P7)Ap + Fdr + Fdy (complement portion) The total force acting on the rotor will be:
FT = ~ Fseal + ~ FC~P
( ~ P7)Ap + (Pl - P7)Ap + Fdr + Fdy FT ' Fdr + Fdy Thus, the forces coming from pressure acting on the section cancel each other.
Although the present invention is shown as a turbine, the principles o~ the invention can also be used for a pump, blower or compressor.
The present invention may be embodied in other speci~ic ~orms without departing from the spirit or essential oharacteristics thereof. The presently disclosed embodiments are therefore to ~e considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims, rather than the foregolng description, and all changes which come within the meaning and range of equivalency of the claim3 are, there~ore, to be embraced therein.
Claims (11)
1. A turbine for driving a downhole motor, said turbine being driven by the flow of a fluid therethrough said turbine comprising:
(a) a housing;
(b) a shaft positioned in said housing, said shaft rotating about the longitudinal axis thereof;
(c) a rotor assembly having a plurality of turbine stages mounted on said shaft for rotation therewith, each turbine stage including a rim means coaxial with said shaft and a plurality of turbine blades fixed to said rim means; and (d) a stator assembly having a plurality of flow directing stator means, each of said stator means being positioned between adjacent turbine stages, each of said stator means having a wall means and diverter means, wherein said wall means are perpendicular to the axis of said shaft and said diverter means are at an angle of less than 90° with respect to the axis of said shaft, wherein at least one of said turbine blades and said diverter means form a seal for preventing the flow from passing therebetween, such that flow through a turbine stage is perpendicular to the axis of said shaft in the space between adjacent wall means and wherein said diverter means are positioned with respect to said wall means for diverting flow from the turbine stage to an adjacent turbine stage.
(a) a housing;
(b) a shaft positioned in said housing, said shaft rotating about the longitudinal axis thereof;
(c) a rotor assembly having a plurality of turbine stages mounted on said shaft for rotation therewith, each turbine stage including a rim means coaxial with said shaft and a plurality of turbine blades fixed to said rim means; and (d) a stator assembly having a plurality of flow directing stator means, each of said stator means being positioned between adjacent turbine stages, each of said stator means having a wall means and diverter means, wherein said wall means are perpendicular to the axis of said shaft and said diverter means are at an angle of less than 90° with respect to the axis of said shaft, wherein at least one of said turbine blades and said diverter means form a seal for preventing the flow from passing therebetween, such that flow through a turbine stage is perpendicular to the axis of said shaft in the space between adjacent wall means and wherein said diverter means are positioned with respect to said wall means for diverting flow from the turbine stage to an adjacent turbine stage.
2. A turbine as set forth in Claim 1, wherein said turbine blades are positioned between adjacent stator means such that the flow between the wall means of the adjacent stator means contacts the edges of said turbine blades thereby imparting a drag force on said turbine blades whereby said turbine is rotated.
3. A turbine as set forth in Claim 1, wherein said turbine blades are positioned between adjacent stator means such that flow between adjacent diverter means impinges upon the face surface of said turbine blades thereby imparting a dynamic force on said turbine blades whereby said turbine is rotated.
4. A turbine as set forth in Claim 1, wherein said turbine blades are positioned between adjacent stator means such that flow between the wall means of adjacent stator means contacts the edges of said turbine blades, thereby imparting a drag force on said turbine blades and flow through adjacent diverter means impinges upon the face surface of said turbine blades, thereby imparting a dynamic force on said turbine blades, whereby said turbine blades are rotated by the combination of the drag forces and dynamic forces thereon.
5. A turbine as set forth in any one of Claim 1, 2 or 4, wherein each of said wall means are planar in single plane perpendicular to the axis of said shaft.
6. A turbine as set forth in any one of Claims 1, 2 and 4, wherein said turbine blades are mounted on said rim such that the flow through a turbine stage contacts at least one the side edges of said turbine blades.
7. A turbine as set forth in Claim 6, wherein said turbine blades are mounted on said rim such that the flow through a turbine stage contacts both side edges of said turbine blades.
8. A turbine as set forth in any one of Claims 1, 2 and 4, wherein said turbine blades are mounted on said rim such that the flow through a turbine stage contacts the front edges of said turbine blades.
9. A turbine as set forth in any one of Claims 1 -4, wherein each of said wall means comprises:
(a) a plurality of planar first sections perpendicular to the axis of said shaft, wherein at least one of said planar first sections is not coplanar with at least another of said planar first sections; and (b) a plurality of planar second sections positioned between and interconnecting said planar firs sections.
(a) a plurality of planar first sections perpendicular to the axis of said shaft, wherein at least one of said planar first sections is not coplanar with at least another of said planar first sections; and (b) a plurality of planar second sections positioned between and interconnecting said planar firs sections.
10. A turbine as set forth in any one of Claims 1, 2 and 4, further including center seal means for forming a seal with a side edge of at least two of said turbine blades, wherein when the seal is formed, the other side edge of said at least one turbine blades forms the seal with said stator means.
11. A turbine as set forth in Claim 1, wherein said at least one turbine blade which forms a seal with said diverter means is at least three turbine blades.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002068398A CA2068398A1 (en) | 1992-05-08 | 1992-05-08 | Multiple stage drag and dynamic turbine downhole motor |
| EP92107873A EP0568723A1 (en) | 1992-05-08 | 1992-05-08 | Multiple stage drag and dynamic turbine downhole motor |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002068398A CA2068398A1 (en) | 1992-05-08 | 1992-05-08 | Multiple stage drag and dynamic turbine downhole motor |
| EP92107873A EP0568723A1 (en) | 1992-05-08 | 1992-05-08 | Multiple stage drag and dynamic turbine downhole motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2068398A1 true CA2068398A1 (en) | 1993-11-09 |
Family
ID=25675130
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002068398A Abandoned CA2068398A1 (en) | 1992-05-08 | 1992-05-08 | Multiple stage drag and dynamic turbine downhole motor |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP0568723A1 (en) |
| CA (1) | CA2068398A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6441508B1 (en) * | 2000-12-12 | 2002-08-27 | Ebara International Corporation | Dual type multiple stage, hydraulic turbine power generator including reaction type turbine with adjustable blades |
| CN102155158B (en) * | 2011-02-21 | 2013-12-04 | 周林 | Jet rotor |
| EA022524B1 (en) * | 2012-09-10 | 2016-01-29 | Товарищество С Ограниченной Ответственностью "Научно-Внедренческий Центр Алмас" | Volumetric downhole motor |
| CN110017102A (en) * | 2019-05-24 | 2019-07-16 | 杰瑞能源服务有限公司 | A kind of fluid power pulsative oscillation tool |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5098258A (en) * | 1991-01-25 | 1992-03-24 | Barnetche Gonzalez Eduardo | Multiple stage drag turbine downhole motor |
-
1992
- 1992-05-08 EP EP92107873A patent/EP0568723A1/en not_active Ceased
- 1992-05-08 CA CA002068398A patent/CA2068398A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| EP0568723A1 (en) | 1993-11-10 |
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Legal Events
| Date | Code | Title | Description |
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| FZDE | Discontinued |