CN203769645U - Line projection blade braking stator and rotor composite member - Google Patents
Line projection blade braking stator and rotor composite member Download PDFInfo
- Publication number
- CN203769645U CN203769645U CN201420161393.XU CN201420161393U CN203769645U CN 203769645 U CN203769645 U CN 203769645U CN 201420161393 U CN201420161393 U CN 201420161393U CN 203769645 U CN203769645 U CN 203769645U
- Authority
- CN
- China
- Prior art keywords
- rotor
- stator
- blade
- stator vane
- rotor blade
- 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.)
- Withdrawn - After Issue
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a line projection blade braking stator and rotor composite member which comprises a stator and a rotor, wherein the stator and the rotor are sleeved together coaxially, the stator and the rotor are respectively provided with a body, a blade and an integral shroud, the inner wall of the integral shroud of the stator and the outer wall of the body of the rotor are sleeved together coaxially, and the stator blade and the rotor blade are both formed in a line projection mode; a stator blade inclination angle and a rotor blade inclination angle on a isometrical cylindrical surface are identical in direction and size and both become smaller gradually in the radial direction, the circumferential thickness of the stator blade or the rotor blade becomes larger gradually in the radial direction, and intersecting lines between the front end, the back edge, the pressure surface and the suction surface of the stator blade or the rotor blade and an equivalent meridian surface all point to the radius direction. According to the line projection blade braking stator and rotor composite member, braking torque is high, hydraulic loss is small, a certain number of line projection torsion wedge-shaped blade braking stators and rotors and a certain number of turbine stators and rotors are assembled together, the working time, overload capacity and low-rotation-speed working stability of a turbo-drill can be improved remarkably, and turbo-drilling footage can be improved remarkably.
Description
Technical field
The utility model patent relates to the creeping into of field such as the probing in the fields such as oil, natural gas, coal bed gas, shale gas exploitation or geology, railway, electric power, communication and uses down-hole turbodrill, especially a Wedge-shaped blade retrostage rotor composite member reverses in line projection, belongs to machinery manufacturing technology field.
Background technology
Turbodrill is commercial Application a kind of down-hole fluid motor the earliest, and its effect is to change the fluid pressure energy of working solution into output shaft rotating machinery energy, drives drill bit to rotate with broken bottom rock.Turbodrill is a kind of mud motor that oilfield is conventional.Because the turbodrill rotating speed being made up of existing multistage turbine level rotor composite member is too high, bit bearing or tooth wear excessive velocities, the drilling depth and the drilling time that bore for one time are more much lower than rotary drilling.
In view of the shortcoming of above-mentioned existing turbodrill existence, the design people is based on being engaged in for a long time related scientific research and field trial, to actively improvement and bring new ideas in addition of prior art, to realizing, a kind of pressure drop is low, idler revolutions and working speed is low, operation torque is moderate turbodrill.
Utility model content
The purpose of this utility model is to provide line projection's blade retrostage rotor composite member that a kind of braking torque is large, hydraulic loss is little.
For achieving the above object, the utility model proposes a kind of line projection blade retrostage rotor composite member, comprise stator and the rotor of coaxial package: the central axis conllinear of described stator and described rotor; Described stator comprises cylindric stator body, several stator vanes and the circular stator integral shroud of coaxial setting, and described in several, stator vane is along being circumferentially arranged between described stator body and described stator integral shroud; Described rotor comprises cylindric rotor body, several rotor blades and the circular rotor integral shroud of coaxial setting, and described in several, rotor blade is along being circumferentially arranged between described rotor body and described rotor integral shroud; Described stator integral shroud inwall and described rotor body outer wall coaxial package, on described stator vane outer contour, each point is first-phase transversal with the intersecting lens of its corresponding equivalent meridian plane, and this first-phase transversal intersects vertically with the first projection straight line in described stator integral shroud; On described rotor blade outer contour, each point is second-phase transversal with the intersecting lens of its corresponding equivalent meridian plane, and this second-phase transversal intersects vertically with the second projection straight line in described rotor body; The established angle of described stator vane is identical with the established angle direction of described rotor blade; Described stator vane established angle radially reduces from the inside to the outside gradually along described stator, and described rotor blade established angle also reduces from the inside to the outside gradually along described rotor radial; The cotangent value of described stator vane established angle and described rotor blade established angle is directly proportional with the radius on the corresponding isometrical face of cylinder.
Line projection as above blade retrostage rotor composite member, wherein, the central axis that described the first projection straight line is described stator, the central axis that described the second projection straight line is described rotor.
Line projection as above blade retrostage rotor composite member, wherein, each described stator vane arranges and circumferentially uniformly-spaced arranges along described stator along described stator shaft orientation equal altitudes; Each described rotor blade uniformly-spaced arranges along the setting of described rotor axial equal altitudes and along described periphery of rotor.
Line projection as above blade retrostage rotor composite member, wherein, the thickness of described stator vane radially increases from inside to outside gradually along described stator, and is directly proportional with the radius on the corresponding isometrical face of cylinder; The thickness of described rotor blade also increases from inside to outside gradually along described rotor radial, and is directly proportional with the radius on the corresponding isometrical face of cylinder.
Line projection as above blade retrostage rotor composite member, wherein, described stator vane comprises stator vane leading edge, stator vane trailing edge, stator vane pressure face and stator vane suction surface along the expanding wheel profile on the isometrical face of cylinder, the intersection of the equivalent meridian plane of described stator vane leading edge, stator vane trailing edge, stator vane pressure face and stator vane suction surface and described stator is straight line, and the intersection of described stator vane and described stator center intersect vertical axis; Described rotor blade comprises rotor blade leading edge, rotor blade trailing edge, rotor blade pressure face and rotor blade suction surface along the expanding wheel profile on the isometrical face of cylinder, the intersection of the equivalent meridian plane of described rotor blade leading edge, rotor blade trailing edge, rotor blade pressure face and rotor blade suction surface and described rotor is straight line, and the intersection of described rotor blade also intersects vertically with the central axis of described rotor.
Line projection as above blade retrostage rotor composite member, wherein, described stator vane and described rotor blade are along the expanding wheel profile on the isometrical face of cylinder separately the wedge shape that one end thickness is greater than other end thickness.
Line projection as above blade retrostage rotor composite member, wherein, the central axis of described the first projection straight line and described stator parallel lines each other, and described the first projection straight line and described stator center axis spacing are less than or equal to 50mm; The central axis of described the second projection straight line and described rotor parallel lines each other, and described the second projection straight line and described rotor center axis spacing are less than or equal to 50mm.
Axial height at stator described in the utility model or rotor blade is radially identical, not because axial distance (isometrical face of cylinder radius) changes.Described stator vane center line or rotor blade center line are straight line, this straight line with form an angle of slope (claiming again established angle) perpendicular to the plane of described stator or rotor axis; Described stator vane center line or the evolute of rotor blade center line on the isometrical face of cylinder are straight line, this straight line with form an angle of slope perpendicular to the plane of described stator or rotor axis; With stator vane angle of slope and the rotor blade angle of slope on the isometrical face of cylinder (face of cylinder that same axis, radius equate) of stator or the concentricity axis of rotor, direction is identical, equal and opposite in direction, and radially (from inside to outside) reduces gradually, the cotangent value of blade pitch angle is directly proportional to the isometrical face of cylinder radius of stator or the concentricity axis of rotor.The thickness of described stator vane or rotor blade radially (from inside to outside) increases gradually, is directly proportional to the isometrical face of cylinder radius of stator or the concentricity axis of rotor.(I value is the relative position of arbitrary plane vertical with stator or rotor axis and leading edge and trailing edge between turbo blade frontier and rear for described stator vane or rotor blade and certain I value, as this plane and leading edge peak I=0 during in same position, when this plane with trailing edge minimum point I=1.0 during in same position) equivalent meridian plane is crossing, blade inlet edge, pressure face, two straight lines of suction surface and trailing edge formation crossing with meridian plane, and two the extended line of straight line and stator or rotor axis intersect at same point, be stator or rotor blade leading edge, the intersection of trailing edge and pressure face and suction surface and equivalent meridian plane all points to radial direction.
Compared with prior art, the utlity model has following characteristics and advantage:
The utility model is simple in structure, braking torque is large, hydraulic loss is little, some line projections hydraulic brake level rotor and the combination of some stage of turbines rotor are assembled together, significantly reduce turbodrill idler revolutions and working speed, improved working time, overload capacity, the stability of working and the turbodrilling drilling depth of turbodrill under the slow-speed of revolution.
Brief description of the drawings
Accompanying drawing described here is only for task of explanation, and is not intended to limit by any way the utility model scope of disclosure.In addition, in figure, shape and the proportional sizes etc. of each parts are only schematically, for helping understanding of the present utility model, are not shape and the proportional sizes that specifically limits the each parts of the utility model.Those skilled in the art, under instruction of the present utility model, can select various possible shapes and proportional sizes to implement the utility model as the case may be.
Fig. 1 is the cross-sectional view of the utility model line projection blade retrostage rotor composite member;
Fig. 2 is the biopsy cavity marker devices structural representation of the utility model line projection blade retrostage rotor composite member;
Fig. 3 is stator cross-sectional view of the present utility model;
Fig. 4 is stator perspective view of the present utility model;
Fig. 5 is that stator vane of the present utility model pushes up the isometrical face of cylinder (S=1) expansion schematic diagram along leaf;
Fig. 6 is that stator of the present utility model is along equivalent meridian plane (I=0.5) cut-away illustration;
Fig. 7 is rotor profiles structural representation of the present utility model;
Fig. 8 is rotor perspective view of the present utility model;
Fig. 9 is that rotor blade of the present utility model pushes up the isometrical face of cylinder (S=1) expansion schematic diagram along leaf;
Figure 10 is that rotor of the present utility model is along equivalent meridian plane (I=0.5) cut-away illustration.
Description of reference numerals:
1-stator; 11-stator body; 12-stator vane; 121-stator leaf top; At the bottom of 122-stator leaf; 123-stator vane leading edge; 124-stator vane trailing edge; 125-stator vane suction surface; 126-stator vane pressure face; 13-stator integral shroud;
2-rotor; 21-rotor body; 22-rotor blade; 221-rotor leaf top; At the bottom of 222-rotor leaf; 223-rotor blade leading edge; 224-rotor blade trailing edge; 225-rotor blade pressure face; 226-rotor blade suction surface; 23-rotor integral shroud; 24-boss;
The isometrical face of cylinder of 3-; The equivalent meridian plane of 4-; 41-first-phase transversal; 42-second-phase transversal; 51-the first projection straight line; 52-the second projection straight line.
Detailed description of the invention
With the description of the utility model detailed description of the invention, can more be well understood to details of the present utility model by reference to the accompanying drawings.But detailed description of the invention of the present utility model described here,, for explaining the purpose of this utility model, is only to restriction of the present utility model and can not be understood as by any way.Under instruction of the present utility model, technician can conceive based on possible distortion arbitrarily of the present utility model, and these all should be regarded as belonging to scope of the present utility model.
Please refer to Fig. 1 to Figure 10, Fig. 1 is the cross-sectional view of the utility model line projection blade retrostage rotor composite member; Fig. 2 is the biopsy cavity marker devices structural representation of the utility model line projection blade retrostage rotor composite member; Fig. 3 is stator cross-sectional view of the present utility model; Fig. 4 is stator perspective view of the present utility model; Fig. 5 is that stator vane of the present utility model pushes up the isometrical face of cylinder (S=1) expansion schematic diagram along leaf; Fig. 6 is that stator of the present utility model is along equivalent meridian plane (I=0.5) cut-away illustration; Fig. 7 is rotor profiles structural representation of the present utility model; Fig. 8 is rotor perspective view of the present utility model; Fig. 9 is that rotor blade of the present utility model pushes up the isometrical face of cylinder (S=1) expansion schematic diagram along leaf; Figure 10 is that rotor of the present utility model is along equivalent meridian plane (I=0.5) cut-away illustration.
As shown in Figures 1 to 10, the utility model proposes a kind of line projection blade retrostage rotor composite member, comprise stator 1 and the rotor 2 of coaxial package, central axis OO ' the conllinear of stator 1 and rotor 2, stator 1 comprises stator body cylindraceous 11, several stator vanes 12 and the circular stator integral shroud 13 of coaxial setting, and several stator vanes 12 are along being circumferentially arranged between stator body 11 and stator integral shroud 13 (as shown in Figure 4).Several stator vanes 12 are evenly laid along the inner circumferential surface of stator body 11, and at the bottom of the leaf of the outer wall of stator integral shroud 13 and stator vane 12,122 are connected.Rotor 2 comprises rotor body cylindraceous 21, several rotor blades 22 and the circular rotor integral shroud 23 of coaxial setting, and several rotor blades 22 are along being circumferentially arranged between rotor body 21 and rotor integral shroud 23.As shown in Figure 8, be provided with the boss 24 radially protruding in rotor body 21 one end peripheries, several rotor blades 22 are evenly laid along the outer circumference surface of boss 24, rotor integral shroud 23 is socketed on the leaf top 221 of rotor blade 22, make rotor body 21, rotor blade 22, rotor integral shroud 23 form the rotor 2 of integrative-structure, can make turbine motor main shaft run through rotor body 21 and with rotor 2 synchronous rotaries.Stator integral shroud 13 inwalls and rotor body 21 outer wall coaxial packages, make stator 1 coordinate installation with rotor 2.
In the utility model, the blade profile of stator vane 12 and rotor blade 22 is line projection and forms.As shown in Figure 4, stator vane 12 is stator leaf top 121 in abutting connection with a side of stator body 11, and its side in abutting connection with stator integral shroud 13 is at the bottom of stator leaf 122.At the bottom of stator leaf top 121 and stator leaf, between 122, have any number of and stator body 11 and stator integral shroud 13 face of cylinder of central axis altogether, each face of cylinder is referred to as the isometrical face of cylinder 3.Stator leaf top 121 and the arbitrary isometrical face of cylinder 3 between 122 at the bottom of stator leaf and stator leaf push up 121 and stator leaf at the bottom of 122 relative position S value representation, 0≤S≤1.0: as the isometrical face of cylinder 3 S=0 when 122 faces of cylinder, place overlap at the bottom of stator leaf; Push up 121 faces of cylinder, place S=1.0 while overlapping when the isometrical face of cylinder 3 with stator leaf.Accordingly, as shown in Figure 8, rotor blade 22 is at the bottom of rotor leaf 222 in abutting connection with a side of the boss 24 of rotor body 21, and its side in abutting connection with rotor integral shroud 23 is rotor leaf top 221, at the bottom of rotor leaf top 221 and rotor leaf, between 222, have any number of and rotor body 21 and rotor integral shroud 23 face of cylinder of central axis altogether, each face of cylinder is also referred to as the isometrical face of cylinder 3.222 relative position S value representation at the bottom of the arbitrary isometrical face of cylinder 3 at the bottom of rotor leaf top 221 and rotor leaf between 222 and rotor leaf top 221 and rotor leaf, 0≤S≤1.0: as the isometrical face of cylinder 3 S=0 when 222 faces of cylinder, place overlap at the bottom of rotor leaf, push up 221 faces of cylinder, place S=1.0 while overlapping when the isometrical face of cylinder 3 with rotor leaf.Be set with superimposed setting because stator 1 and rotor 2 are total to central axis up and down, therefore the isometrical face of cylinder on the isometrical face of cylinder on the stator 1 that waits S value and rotor 2 is real is the same isometrical face of cylinder.
In the utility model, the plane intersecting vertically with the central axis of stator 1 and rotor 2 is referred to as meridian plane.As shown in Figure 5, Figure 6, the meridian plane between the upper end of stator vane 12 (entrance) and lower end (outlet) and the relative position I value representation of upper end and lower end, 0≤I≤1.0.Wherein, wait the meridian plane of I value to be called equivalent meridian plane 4: I=0 in the time that the upper end of equivalent meridian plane 4 and stator vane 12 is tangent, I=1 in the time that the lower end of equivalent meridian plane 4 and stator vane 12 is tangent.Accordingly, as shown in Figure 9, Figure 10, the meridian plane between the upper end of rotor blade 22 (entrance) and lower end (outlet) and the relative position I value representation of upper end and lower end, 0≤I≤1.0.Wherein, the meridian plane that waits I value is also referred to as equivalent meridian plane 4: I=0 in the time that the upper end of equivalent meridian plane 4 and rotor blade 22 is tangent, I=1 in the time that the lower end of equivalent meridian plane 4 and stator vane 12 is tangent.
In the utility model, as shown in Figure 6, the intersecting lens of the equivalent meridian plane 4 that on the outer contour of stator vane 12, each point is corresponding with it is first-phase transversal 41, and this first-phase transversal 41 and the first projection straight line 51(in stator integral shroud 13 are as shown in Figure 3) intersect vertically; And the intersecting lens of the equivalent meridian plane 4 that on the outer contour of rotor blade 22, each point is corresponding with it is second-phase transversal 42, this second-phase transversal 42 and the second projection straight line 52(in rotor body 21 are as shown in Figure 7) intersect vertically.In the utility model, the first projection straight line 51 and the second projection straight line 52 can be both the straight lines coinciding, also can be the straight line not coinciding, as long as ensure the cavity of the first projection straight line 51 through annular stator integral shroud 13, the second projection straight line is through cylindric rotor body 21 cavities.
As shown in Fig. 2, Fig. 5, Fig. 9, rotor blade 22 is obliquely installed face with stator vane 12 with respect to the central axis of rotor 2 and stator 1 and forms an angle of slope (claiming again established angle), and rotor blade 22 is identical with the incline direction of stator vane 12.Be the established angle β of stator vane 12
l1established angle β with rotor blade 22
l2direction is identical, equal and opposite in direction, stator vane 12 established angle β
l1radially reduce gradually from the inside to the outside rotor blade 22 established angle β along stator 1
l2radially also reduce gradually from the inside to the outside stator vane established angle β along rotor 2
l1cotangent value, rotor blade established angle β
l2cotangent value be directly proportional with the radius on the corresponding isometrical face of cylinder.The experiment proved that, the utility model moment of torsion is large, hydraulic efficiency is high, be suitable for needles of various sizes well creeps into.As shown in Figure 5, Figure 9, (the leading edge arc radius on the isometrical face of cylinder of certain specific S value is r for the leading edge of stator vane 12 and rotor blade 22 and trailing edge
11and r
21, trailing edge arc radius is r
12and r
22, and r
11≤ r
12, r
21≤ r
22) tangent with pressure face, suction surface outline line, can greatly reduce like this hydraulic loss of retrostage.
Further, as shown in Figure 5, Figure 9, stator vane 12 is along the expanding wheel profile on its isometrical face of cylinder 3 wedge shape that one end thickness is greater than other end thickness; Rotor blade 22 is also along the expanding wheel profile on its isometrical face of cylinder 3 wedge shape that one end thickness is greater than other end thickness.Wherein, the blade profile of stator vane 12 and rotor blade 22 is line projection and forms, thin at the bottom of blade inlet edge and leaf, trailing edge and leaf top thickness, be the solid conical (vertex of a cone is straight line) that blade three dimensional design curved surface upright projection that stator vane 12 is served as reasons on stator 1 certain isometrical face of cylinder of specific S value (0≤S≤1.0) forms to axis stator, at the bottom of leaf, the isometrical face of cylinder (S=0) and leaf push up the isometrical face of cylinder (S=1.0) cutting and form; The solid conical that the blade three dimensional design curved surface upright projection that rotor blade 22 is served as reasons on the rotor 2 isometrical faces of cylinder of certain particular value forms to rotor axis, at the bottom of leaf, the isometrical face of cylinder (S=0) and leaf push up the isometrical face of cylinder (S=1.0) cutting formation.The chock that each blade-shaped is reversed like one jiao and adjacent both sides.
In the present embodiment, preferred, the first projection straight line 51 is the central axis of stator 1, and the second projection straight line 52 is the central axis of rotor 2.
Further, as shown in Figure 5, Figure 9, each stator vane 12 is along the axial equal altitudes setting of stator 1 circumferentially uniformly-spaced arranging along stator 1; Each rotor blade 22 is along the axial equal altitudes setting of rotor 2 circumferentially uniformly-spaced arranging along rotor 2.
Further, as shown in Figure 5, Figure 9, the thickness of stator vane 12 radially increases from inside to outside gradually along stator 1, and is directly proportional with the radius on the corresponding isometrical face of cylinder 3; The thickness of rotor blade 22 radially also increases from inside to outside gradually along rotor 2, and is also directly proportional with the radius on the corresponding isometrical face of cylinder 3.
In the utility model, as shown in Fig. 5, Fig. 6, Fig. 9, Figure 10, stator vane 12 comprises stator vane leading edge 123, stator vane trailing edge 124, stator vane suction surface 125 and stator vane pressure face 126 along the expanding wheel profile on the isometrical face of cylinder 3; Stator vane leading edge 123, stator vane trailing edge 124, stator vane suction surface 125 and stator vane pressure face 126 are straight line with the intersection of the equivalent meridian plane 4 of stator 1, and the intersection of stator vane 12 and stator center axes O O ' intersect vertically.Rotor blade 22 comprises rotor blade leading edge 223, rotor blade trailing edge 224, rotor blade pressure face 225 and rotor blade suction surface 226 along the expanding wheel profile on the isometrical face of cylinder 3; Rotor blade leading edge 223, rotor blade trailing edge 224, rotor blade pressure face 225 and rotor blade suction surface 226 are also straight line with the intersection of the equivalent meridian plane 4 of rotor 2, and the central axis of the intersection of rotor blade 22 and rotor 2 also intersects vertically.
Further, the central axis parallel lines each other of the first projection straight line 51 and stator 1, and the first projection straight line 51 is less than or equal to 50mm with the central axis spacing of stator 1; The central axis parallel lines each other of the second projection straight line 52 and rotor 2, and the second projection straight line 52 is less than or equal to 50mm with the central axis spacing of rotor 2.
Further, as shown in Fig. 1, Fig. 3, Fig. 7, the axial height of stator 1 and rotor 2 is L=20～60mm, and stator 1 external diameter is D
se=50～300mm, rotor 2 internal diameters are D
ri=20～200mm.For ease of installing and using the outer diameter D of retrostage stator
seidentical with stage of turbine stator outer diameter, the inner diameter D of hydraulic brake level rotor
riidentical with stage of turbine rotor internal diameter.
Further, as shown in Fig. 1, Fig. 3, Fig. 7, stator integral shroud 13 axial height L
1=7～20mm, the axial height L of rotor integral shroud 23
2=7～20mm; The axial height H of stator vane 12
1=7～20mm, the axial height H of rotor blade 22
2=7～20mm.
Further, as shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 7, the outer wall of Wedge-shaped blade retrostage rotor body 21 reverses in line projection, inwall, the inwall of stator body 11 and the outer wall of stator integral shroud 13 of rotor integral shroud 23 forms circular fluid course.The inner periphery diameter D of rotor integral shroud 23
r1equal the inner periphery diameter D of stator body 11
s1, i.e. the runner outer diameter D of this rotor combination
1=D
r1=D
s1; The boss 24 excircle diameter D of rotor body 21
r2equal the excircle diameter D of stator integral shroud 13
s2, i.e. the runner inner diameter D of this rotor combination
2=D
r2=D
s2; Runner outer diameter D
1with runner inner diameter D
2arithmetic mean of instantaneous value be average flow diameter D; Runner outer diameter D
1with runner inner diameter D
2the half of difference be width of flow path h=h
r=h
s, h=(D
1-D
2)/2=5.0～100.0mm.(note: as required, D
r1with D
s1, D
r2with D
s2also desirable different value.)
Further, as shown in Figure 4 and Figure 8, the blade number n of stator vane 12
1blade number n with rotor blade 22
2be respectively n
1=10～60, n
2=10～60, thus meet different operating mode demands.
Further, as shown in Fig. 5 and Fig. 9, line projection reverses Wedge-shaped blade retrostage stator vane 12 and rotor blade 22 and all generates by line projection, and on the isometrical face of cylinder stator vane 12 established angle β
l1with rotor blade 22 established angle β
l2equate 10 °≤β of span
l1=β
l2≤ 90 °.The axial height L of rotor integral shroud 23
2with stator integral shroud 13 axial height L
1equate i.e. L
1=L
2=8～19mm; The axial height of rotor blade 22 is H
2, H
1the axial height of=8～19mm, stator vane 12 is, H
1=8～19mm; Angle between rotor blade 22 pressure faces and suction surface is
angle between stator vane 12 pressure faces and suction surface is
pitch t between adjacent two stator vanes 12
1or pitch t between adjacent two rotor blades 21
2be respectively t
1=3.0～10.0mm, t
2=3.0～10.0mm, pitch t
1with pitch t
2can get different value.
Further, as shown in Fig. 6 and Figure 10, the equivalent meridian plane that stator vane 12 or rotor blade 22 are 0.5 with value is crossing, two straight lines of blade inlet edge or pressure face or suction surface or trailing edge formation crossing with equivalent meridian plane, and two the extended line of straight line and stator 1 or rotor 2 axes intersect are in same point, and the intersection of stator vane or rotor blade ingress edge (leading edge), outlet edge (trailing edge) and pressure face and suction surface and equivalent meridian plane all points to radial direction.Stator vane 12 thickness and rotor blade 22 thickness radially increase gradually.It is worthy of note, the leading-edge radius of stator former blade 12 and rotor blade 22, trailing edge radius, blade angle, the isometrical face of cylinder, equivalent meridian plane are defined as the known technology of this area.
In use, the blade 12 that the blade 22 of line projection's torsion Wedge-shaped blade retrostage rotor 2 is equal to stator 1 is at axial rotation prolongation (stator vane established angle β
l1with rotor blade established angle β
l2identical), when hydraulic brake level rotor composite member and stage of turbine rotor composite member are arranged on same main shaft, when working solution is flowed through rotor composite member, stage of turbine rotor produces moment of torsion, and hydraulic brake level rotor is driven to rotate.Because the incline direction of retrostage stator vane is contrary with the incline direction of stage of turbine stator vane, therefore the working solution flowing out from retrostage stator is by inhibition to the rotation of retrostage rotor blade, that is not only can not produce operation torque to turbodrill main shaft, and will consume moment of torsion, thereby the rotating speed of main shaft is decreased.Meanwhile, when retrostage rotor rotates, just like axial flow pump runner, can assist borehole pump to pressurize to hydraulic fluid, play regulating system pressure, reduce the effect of overall presure drop.
In sum, the utility model patent designs by said structure, have advantages of simple in structure, pressure drop is low, moment of torsion is large, hydraulic efficiency is high.
For the detailed explanation of above-mentioned embodiment, its object is only the utility model to make an explanation, so that can understand better the utility model, but, it is to restriction of the present utility model that these descriptions can not be construed to any reason, particularly, each feature of describing in different embodiments also can be combined mutually, thereby forms other embodiments.Except there being clearly contrary description, these features should be understood to can be applied in any one embodiment, and are also not only confined to described embodiment.
Claims (7)
1. line projection's blade retrostage rotor composite member, comprises stator and the rotor of coaxial package, the central axis conllinear of described stator and described rotor; Described stator comprises cylindric stator body, several stator vanes and circular stator integral shroud, and described in several, stator vane is along being circumferentially arranged between described stator body and described stator integral shroud; Described rotor comprises cylindric rotor body, several rotor blades and circular rotor integral shroud, and described in several, rotor blade is along being circumferentially arranged between described rotor body and described rotor integral shroud; Described stator integral shroud inwall and described rotor body outer wall coaxial package, it is characterized in that: on described stator vane outer contour, each point is first-phase transversal with the intersecting lens of its corresponding equivalent meridian plane, this first-phase transversal intersects vertically with the first projection straight line in described stator integral shroud; On described rotor blade outer contour, each point is second-phase transversal with the intersecting lens of its corresponding equivalent meridian plane, and this second-phase transversal intersects vertically with the second projection straight line in described rotor body; The established angle of described stator vane is identical with the established angle direction of described rotor blade; Described stator vane established angle radially reduces from the inside to the outside gradually along described stator, and described rotor blade established angle also reduces from the inside to the outside gradually along described rotor radial; The cotangent value of described stator vane established angle and described rotor blade established angle is directly proportional with the radius on the corresponding isometrical face of cylinder.
2. line projection as claimed in claim 1 blade retrostage rotor composite member, is characterized in that: the central axis that described the first projection straight line is described stator, the central axis that described the second projection straight line is described rotor.
3. line projection as claimed in claim 1 or 2 blade retrostage rotor composite member, is characterized in that: each described stator vane arranges and circumferentially uniformly-spaced arranges along described stator along described stator shaft orientation equal altitudes; Each described rotor blade uniformly-spaced arranges along the setting of described rotor axial equal altitudes and along described periphery of rotor.
4. line projection as claimed in claim 1 or 2 blade retrostage rotor composite member, is characterized in that: the thickness of described stator vane radially increases from inside to outside gradually along described stator, and is directly proportional with the radius on the corresponding isometrical face of cylinder; The thickness of described rotor blade also increases from inside to outside gradually along described rotor radial, and is directly proportional with the radius on the corresponding isometrical face of cylinder.
5. line projection as claimed in claim 1 or 2 blade retrostage rotor composite member, it is characterized in that: described stator vane comprises stator vane leading edge, stator vane trailing edge, stator vane pressure face and stator vane suction surface along the expanding wheel profile on the isometrical face of cylinder, the intersection of the equivalent meridian plane of described stator vane leading edge, stator vane trailing edge, stator vane pressure face and stator vane suction surface and described stator is straight line, and the intersection of described stator vane and described stator center intersect vertical axis; Described rotor blade comprises rotor blade leading edge, rotor blade trailing edge, rotor blade pressure face and rotor blade suction surface along the expanding wheel profile on the isometrical face of cylinder, the intersection of the equivalent meridian plane of described rotor blade leading edge, rotor blade trailing edge, rotor blade pressure face and rotor blade suction surface and described rotor is straight line, and the intersection of described rotor blade also intersects vertically with the central axis of described rotor.
6. line projection as claimed in claim 5 blade retrostage rotor composite member, is characterized in that: described stator vane and described rotor blade are along the expanding wheel profile on the isometrical face of cylinder separately the wedge shape that one end thickness is greater than other end thickness.
7. line projection as claimed in claim 1 blade retrostage rotor composite member, it is characterized in that: the central axis of described the first projection straight line and described stator parallel lines each other, and described the first projection straight line and described stator center axis spacing are less than or equal to 50mm; The central axis of described the second projection straight line and described rotor parallel lines each other, and described the second projection straight line and described rotor center axis spacing are less than or equal to 50mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420161393.XU CN203769645U (en) | 2014-04-03 | 2014-04-03 | Line projection blade braking stator and rotor composite member |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420161393.XU CN203769645U (en) | 2014-04-03 | 2014-04-03 | Line projection blade braking stator and rotor composite member |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203769645U true CN203769645U (en) | 2014-08-13 |
Family
ID=51286846
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420161393.XU Withdrawn - After Issue CN203769645U (en) | 2014-04-03 | 2014-04-03 | Line projection blade braking stator and rotor composite member |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203769645U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103939008A (en) * | 2014-04-03 | 2014-07-23 | 中国石油大学(北京) | Linear projection blade braking stage stator and rotor assembly |
-
2014
- 2014-04-03 CN CN201420161393.XU patent/CN203769645U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103939008A (en) * | 2014-04-03 | 2014-07-23 | 中国石油大学(北京) | Linear projection blade braking stage stator and rotor assembly |
| CN103939008B (en) * | 2014-04-03 | 2016-03-16 | 中国石油大学(北京) | Line projection's blade activation level rotor composite member |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103711631B (en) | Line projection's blade turbine rotor assembly parts and turbine motor | |
| CN103939008B (en) | Line projection's blade activation level rotor composite member | |
| RU2647016C2 (en) | Stator and rotor assembly of the turbine and turbine engine | |
| CN104154043A (en) | Axial flow pump without blade top leakage vortex | |
| CN202520472U (en) | Stator and rotor combination piece of turbine, and turbine motor | |
| US7448455B2 (en) | Turbodrill with asymmetric stator and rotor vanes | |
| CN203769645U (en) | Line projection blade braking stator and rotor composite member | |
| CN203308640U (en) | Turbine stator and rotor assembly and turbine motor | |
| CN202039904U (en) | Turbine stator rotor assembled part and turbine drilling tool | |
| CN103334864A (en) | Turbine motor with hydraulic braking level stator and rotor components | |
| CN103925238A (en) | Epicycloid centrifugal pump impeller | |
| CN203321738U (en) | Hydraulic brake stator-rotor assembly | |
| CN102619779B (en) | Turbulence generator for medium-consistency paper pulp pump | |
| CN204140257U (en) | Spot projection Wedge-shaped blade activation level rotor assembly parts | |
| CN203962275U (en) | Scan Wedge-shaped blade retrostage rotor assembly parts | |
| CN204140259U (en) | Spot projection blade turbine rotor assembly parts and turbine motor | |
| CN104047795A (en) | Point-projection wedge-shaped blade brake-stage stator and rotor assembly | |
| CN203867763U (en) | Telescopic wedge-shaped blade brake-stage stator and rotor assembly | |
| CN203770008U (en) | Linear projection vane turbine stator and rotor assembly and turbine motor | |
| CN203308648U (en) | Turbine motor with hydraulic brake stage stator-rotor assembly | |
| CN104454024B (en) | A kind of multi-level centripetal turbine formula turbine section | |
| CN203962276U (en) | Scan shaping blade turbine rotor assembly parts and turbine motor | |
| CN104179622A (en) | Braking level stator-rotor assembly provided with sweeping wedge-shaped blades | |
| CN104074667A (en) | Point projection blade turbine stator and rotor assembling unit and turbine motor | |
| US20150060144A1 (en) | Turbine blade for turbodrills |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140813 Effective date of abandoning: 20160316 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |