CN104074667A - Point projection blade turbine stator and rotor assembling unit and turbine motor - Google Patents
Point projection blade turbine stator and rotor assembling unit and turbine motor Download PDFInfo
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- CN104074667A CN104074667A CN201410315784.7A CN201410315784A CN104074667A CN 104074667 A CN104074667 A CN 104074667A CN 201410315784 A CN201410315784 A CN 201410315784A CN 104074667 A CN104074667 A CN 104074667A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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Abstract
The invention provides a point projection blade turbine stator and rotor assembling unit and a turbine motor. The point projection blade turbine stator and rotor assembling unit comprises a stator and a rotor which are arranged in a sleeve mode and coaxially, the axial height of every stator blade gradually increases in the radial direction of the stator from inside to outside and is in direct proportion to the radius of an equal-diameter cylindrical surface of the stator; the axial height of the rotor blade gradually increases in the radial direction of the rotor from inside to outside and is in direct proportion to the radius of an equal-diameter cylindrical surface of the rotor. The point projection blade turbine stator and rotor assembling unit and the turbine motor are small in hydraulic loss, large in torque, simple in structure, and applicable to well drilling of every size.
Description
Technical field
The slim-hole or the eyelet that the present invention relates to the fields such as the rotary drilling in the fields such as oil, rock gas, coal-seam gas, shale gas exploitation or geology, railway, electric power, communication creep into mud motor, especially rotor assembly parts and the turbine motor of high pulling torque turbodrill, belong to machinery manufacturing technology field.
Background technique
TURBODRILLING TECHNIQUE WITH TREMENDOUS TECHNICAL has good economy and social benefit, is a cutting edge technology of petroleum industry.Turbodrilling can reduce consumption, reduces costs.Turbodrill is commercial Application a kind of mud motor the earliest, turbine motor, cardan shaft and transmission shaft three parts, consists of, and its effect is to change the hydrodynamic pressure energy of working fluid into mechanical energy, drives drill bit to rotate with broken bottom rock.Historically, turbodrill is from being developed so far always as Russia and the conventional a kind of mud motor of western developed country oilfield.China the 1950's is from the former Soviet Union introduces turbodrill production technology, slower development, fail to obtain fine application at industrial and mineral scene, one of its major reason is: because turbodrill has the defects such as rotating speed is high, moment of torsion is little, model is single, operating life is short, incompatible with China's drilling equipment and instrument development level.
At present domesticly not can be used for the high pulling torque turbine motor that oil creeps into, and along with the reducing of turbine motor outside dimension, rotating speed increases, moment of torsion diminishes.Turbine motor is the power section of turbodrill, and the design of turbine stator and rotor is the core of turbine motor design.
Because the shortcoming that above-mentioned existing TURBODRILLING TECHNIQUE WITH TREMENDOUS TECHNICAL exists, the design people is based on being engaged in for a long time related scientific research and site test, to the positive improvement and bring new ideas in addition of prior art, to realizing a kind of high pulling torque, high efficiency turbine rotor assembly parts and turbine motor.
Summary of the invention
The object of this invention is to provide a kind of high pulling torque, high efficiency, be suitable for the spot projection blade turbine rotor assembly parts that needles of various sizes well is crept into.
For achieving the above object, the present invention proposes a kind of spot projection blade turbine rotor assembly parts, comprise stator and the rotor of coaxial package, the centerline collineation of described stator and described rotor; Described stator comprises cylindric stator body, several stator vanes and the circular stator integral shroud of coaxial setting, described rotor comprises cylindric rotor body, several rotor blades and the circular rotor integral shroud of coaxial setting, the inwall of described stator integral shroud and described rotor body outer wall coaxial package, the axial height of described stator vane radially increases from inside to outside gradually along described stator, and is directly proportional to the isometrical cylndrical surface radius of described stator; The axial height of described rotor blade radially increases from inside to outside gradually along described rotor, and is directly proportional to the isometrical cylndrical surface radius of described rotor.
Spot projection blade turbine rotor assembly parts as above, wherein, the pressure side of rotor blade and suction surface and through the equivalent meridian plane of this rotor blade, intersect and form two first-phases and pass through straight line described in each, described two first-phases pass through straight line and intersect, wherein, the intersection point being positioned in described rotor centerline is the first intersection point, described the first intersection point is at rotor blade leading edge peak between the vertical projection point in rotor centerline and the vertical projection point of rotor blade trailing edge minimum point in rotor centerline, and described the first intersection point is unique; The pressure side of stator vane and suction surface and through the equivalent meridian plane of this stator vane, intersect and form two second-phases and pass through straight line described in each, described two second-phases pass through straight line and intersect, wherein, the intersection point being positioned on described stator center line is the second intersection point, described the second intersection point is at stator vane leading edge peak between the vertical projection point on stator center line and the vertical projection point of stator vane trailing edge minimum point on stator center line, and described the second intersection point is unique.
Spot projection blade turbine rotor assembly parts as above, wherein, stator vane established angle and rotor blade established angle on same described isometrical cylndrical surface, opposite direction; Stator vane established angle on different described isometrical cylndrical surface, radially equates; Rotor blade established angle on different described isometrical cylndrical surface, radially equates.
Spot projection blade turbine rotor assembly parts as above, wherein: the circumferential thickness of described stator vane radially increases from inside to outside gradually along described stator, the circumferential thickness of described rotor blade radially increases from inside to outside gradually along described rotor.
Spot projection blade turbine rotor assembly parts as above, wherein, the equivalent meridian plane of described the first intersection point of process and the pressure side of described rotor blade or the intersecting line of suction surface intersect at described the first intersection point; The equivalent meridian plane of described the second intersection point of process and the pressure side of described stator vane or the intersecting line of suction surface intersect at described the second intersection point.
Spot projection blade turbine rotor assembly parts as above, wherein, intersect described stator vane and any two isometrical cylndrical surface, the leading edge of described stator vane is identical with the leading edge intersecting line shape that two stator vanes that form are intersected in described two isometrical cylndrical surface, and the trailing edge of described stator vane is also identical with the trailing edge intersecting line shape that two stator vanes that form are intersected in described two isometrical cylndrical surface; Intersect described rotor blade and any two isometrical cylndrical surface, the leading edge of described rotor blade is identical with two rotor blade leading edge intersecting line shapes that formation is intersected in described two isometrical cylndrical surface, and the trailing edge of described rotor blade is also identical with two rotor blade trailing edge intersecting line shapes that formation is intersected in described two isometrical cylndrical surface.
The present invention also provides a kind of turbine motor, and described turbine motor comprises turbine motor main shaft and turbine motor housing, is socketed with spot projection blade turbine rotor assembly parts as above on described turbine motor main shaft.
Turbine motor as above, wherein, described spot projection blade turbine rotor assembly parts is axially stacked with 50～300 along described turbine motor main shaft, forms the high pulling torque turbine motor with 50～300 grades of turbine rotors.
Spot projection blade turbine rotor assembly parts of the present invention, the rotor and the stator that comprise coaxial package, described rotor comprises rotor body cylindraceous, several rotor blades and circular rotor integral shroud, in described rotor body one end periphery, be provided with the boss radially protruding, described several rotor blades are evenly laid along the outer peripheral surface of described boss, and described rotor integral shroud is socketed on the leaf top of described rotor blade; Described stator comprises stator body cylindraceous, several stator vanes and circular stator integral shroud, described several stator vanes are evenly laid along the inner circumferential surface of described stator body, and the outer wall of described stator integral shroud is connected with at the bottom of the leaf of described stator vane; The inwall of described stator integral shroud and the coaxial fit of described rotor body outer wall; The blade profile of described stator vane and described rotor blade is spot projection and forms, thin at the bottom of blade inlet edge and leaf top thickness, trailing edge and leaf, be the stator vane blade three dimensional design curved surface projection of serving as reasons on the isometrical cylndrical surface of the specific S value of stator (0≤S≤1.0) to the formed infinite height solid conical of a specified point on axis stator, at the bottom of leaf, isometrical cylndrical surface (S=0) and leaf push up isometrical cylndrical surface (S=1) cutting and form; The blade three dimensional design curved surface projection that rotor blade is served as reasons on the isometrical cylndrical surface of the specific S value of rotor (0≤S≤1.0) is to the formed infinite height solid conical of a specified point on rotor axis, and at the bottom of leaf, isometrical cylndrical surface (S=0) and leaf push up isometrical cylndrical surface (S=1) cutting and form.This specified point is between the intersection point and axis and the intersection point of blade exit end face of axis and blade inlet end face.
The axial height of described stator or rotor blade, radially (from inside to outside) increase gradually, be directly proportional to isometrical cylndrical surface radius.Stator vane established angle on isometrical cylndrical surface and rotor blade established angle, and opposite direction (right-hand rule: stator vane dextrorotation, rotor blade is left-handed); Stator vane established angle on isometrical cylndrical surface, radially equates; Rotor blade established angle on isometrical cylndrical surface, radially equates.The circumferential thickness of described stator vane or rotor blade radially (from inside to outside) increases gradually.Described stator vane or rotor blade and arbitrary equivalent meridian plane intersect, and blade pressure surface and suction surface and meridian plane intersect two straight lines of formation, and the intersecting line of stator or rotor blade pressure side and suction surface and equivalent meridian plane is straight line; When meridian plane is when the specified point, two elongation lines that pass through mutually straight line intersect at same point with stator or rotor axis, and sensing radial direction.
Compared with prior art, the present invention has following characteristics and advantage:
1, patent turbine rotor assembly parts hydraulic efficiency of the present invention is high.
2, patent turbine motor of the present invention is simple in structure, moment of torsion is large, and applicable needles of various sizes well is crept into.
Accompanying drawing explanation
Accompanying drawing described here is only for task of explanation, and is not intended to limit by any way scope disclosed by the invention.In addition, in figure, the shape of each parts and proportional sizes etc. are only schematically, for helping the understanding of the present invention, are not shape and the proportional sizes that specifically limits each parts of the present invention.Those skilled in the art, under instruction of the present invention, can select various possible shapes and proportional sizes to implement the present invention as the case may be.
Fig. 1 is spot projection blade turbine rotor assembly parts embodiment's of the present invention (equivalent meridian plane when specified point is I=0.5 and the intersection point of stator or rotor axis) two-dimension plane structure schematic diagram;
Fig. 2 is the stator cross-sectional view of the embodiment of the present invention;
Fig. 3 is the stator perspective view of the embodiment of the present invention;
Fig. 4 is that the stator vane of the embodiment of the present invention pushes up isometrical cylndrical surface S=1.0 expansion schematic diagram along leaf;
Fig. 5 is that the stator of the embodiment of the present invention is along the equivalent meridian plane cut-away illustration of I=0.5;
Fig. 6 is the rotor profiles structural representation of the embodiment of the present invention;
Fig. 7 is the rotor perspective view of the embodiment of the present invention;
Fig. 8 is that the rotor blade of the embodiment of the present invention pushes up isometrical cylndrical surface S=1.0 expansion schematic diagram along leaf;
Fig. 9 is that the rotor of the embodiment of the present invention is along the equivalent meridian plane cut-away illustration of I=0.5;
Figure 10 is spot projection blade turbine rotor assembly parts embodiment's of the present invention 3-D solid structure schematic diagram;
Figure 11 is the cross-sectional view of turbine motor of the present invention.
Description of reference numerals:
1-rotor; 101-rotor body; 102-rotor blade; 103-rotor integral shroud; 104-boss; 105-rotor blade suction surface; 106-rotor blade pressure side; 107-rotor leaf top; At the bottom of 108-rotor leaf; 109-rotor blade leading edge; 110-rotor blade trailing edge; 111-first-phase transversal; 112-the first intersection point; 113-rotor centerline;
2-stator; 201-stator body; 202-stator vane; 203-stator integral shroud; 204-stator vane pressure side; 205-stator vane suction surface; 207-stator leaf top; At the bottom of 208-stator leaf; 209-stator vane leading edge; 210-stator vane trailing edge; 211-second-phase transversal; 212-the second intersection point; 213-stator center line;
31-turbine motor main shaft; 41-turbine motor housing.
Embodiment
With the description of the specific embodiment of the invention, can more be well understood to details of the present invention by reference to the accompanying drawings.But the specific embodiment of the present invention described here,, for explaining object of the present invention, is only limitation of the present invention and can not be understood as by any way.Under instruction of the present invention, technician can conceive based on possible distortion arbitrarily of the present invention, and these all should be regarded as belonging to scope of the present invention.
Please refer to Fig. 1 to Figure 10, Fig. 1 is spot projection blade turbine rotor assembly parts embodiment's of the present invention (equivalent meridian plane when specified point is I=0.5 and the intersection point of stator or rotor axis) two-dimension plane structure schematic diagram; Fig. 2 is the stator cross-sectional view of the embodiment of the present invention; Fig. 3 is the stator perspective view of the embodiment of the present invention; Fig. 4 is that the stator vane of the embodiment of the present invention pushes up isometrical cylndrical surface S=1.0 expansion schematic diagram along leaf; Fig. 5 is that the stator of the embodiment of the present invention is along the equivalent meridian plane cut-away illustration of I=0.5; Fig. 6 is the rotor profiles structural representation of the embodiment of the present invention; Fig. 7 is the rotor perspective view of the embodiment of the present invention; Fig. 8 is that the rotor blade of the embodiment of the present invention pushes up isometrical cylndrical surface S=1.0 expansion schematic diagram along leaf; Fig. 9 is that the rotor of the embodiment of the present invention is along the equivalent meridian plane cut-away illustration of I=0.5; Figure 10 is spot projection blade turbine rotor assembly parts embodiment's of the present invention 3-D solid structure schematic diagram.
As shown in Figures 1 to 10, spot projection blade turbine rotor assembly parts of the present invention, comprises stator 2 and the rotor 1 of coaxial package, the centerline collineation of stator 2 and rotor 1, stator 2 comprises the cylindric stator body 201 of coaxial setting, several stator vanes 202 and circular stator integral shroud 203, rotor 1 comprises the cylindric rotor body 101 of coaxial setting, several rotor blades 102 and circular rotor integral shroud 103, in one end of rotor body 101 periphery, be provided with the boss 104 radially protruding, several rotor blades 102 are evenly laid along boss 104 external peripheral surfaces of rotor body 101, rotor integral shroud 103 is socketed on the leaf top of rotor blade 102, make rotor body 101, blade 102, rotor integral shroud 103 forms the rotor 1 of integrative-structure.
As shown in Figures 2 to 5, stator 2 comprises stator body 201 cylindraceous, several stator vanes 202 and circular stator integral shroud 203, several stator vanes 202 are evenly laid along the inner circumferential surface of stator body 201, at the bottom of the leaf of the outer wall of stator integral shroud 203 and stator vane 202, be connected, make stator body 201, several stator vanes 202 and stator integral shroud 203 form the stator 2 of integrative-structures.As shown in Figure 1, the inwall of stator integral shroud 203 and rotor body 101 outer wall phase fits, and stator body 201 center lines 213 are coaxial with rotor body 101 center lines 113, and the inwall of stator integral shroud 203 and the coaxial fit of rotor body 101 outer wall, make stator 2 coordinate installation with rotor 1.
In the present invention, stator vane 202 and rotor blade 102 are the blade that spot projection forms.As shown in Figure 3, stator vane 202 is stator leaf top 207 in abutting connection with a side of stator body 201, and its side in abutting connection with stator integral shroud 203 is at the bottom of stator leaf 208.At the bottom of stator leaf top 207 and stator leaf, between 208, have cylndrical surface any number of and stator body 201 and stator integral shroud 203 common central axis, each cylndrical surface is referred to as isometrical cylndrical surface.208 relative position S value representation at the bottom of arbitrary isometrical cylndrical surface at the bottom of stator leaf top 207 and stator leaf between 208 and stator leaf top 207 and stator leaf, 0≤S≤1.0: as isometrical cylndrical surface S=0.0 when 208 cylndrical surface, place overlap at the bottom of stator leaf, push up 207 cylndrical surface, place S=1.0 while overlapping when isometrical cylndrical surface with stator leaf.Accordingly, as shown in Figure 7, rotor blade 102 is at the bottom of rotor leaf 108 in abutting connection with a side of rotor body 101, and its side in abutting connection with rotor integral shroud 103 is rotor leaf top 107, at the bottom of rotor leaf top 107 and rotor leaf, between 108, have cylndrical surface any number of and rotor body 101 and rotor integral shroud 103 common central axis, each cylndrical surface is also referred to as isometrical cylndrical surface.108 relative position S value representation at the bottom of arbitrary isometrical cylndrical surface at the bottom of rotor leaf top 107 and rotor leaf between 108 and rotor leaf top 107 and rotor leaf, 0≤S≤1.0: as isometrical cylndrical surface S=0.0 when 108 cylndrical surface, place overlap at the bottom of rotor leaf, push up 107 cylndrical surface, place S=1.0 while overlapping when isometrical cylndrical surface with rotor leaf.Because stator 2 and rotor 1 are total to central axis up and down, being set with superimposed setting, is therefore same isometrical cylndrical surface waiting isometrical cylndrical surface and the isometrical cylndrical surface on rotor 1 on the stator 2 of S value.
In the present invention, the plane intersecting vertically with the center line (axis) of stator 2 and rotor 1 is referred to as meridian plane.As shown in Figure 5, the meridian plane between the upper end of stator vane 202 (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: I=0.0 when the upper end of equivalent meridian plane and stator vane 202 is tangent, I=1.0 when the lower end of equivalent meridian plane and stator vane 202 is tangent.Accordingly, as shown in Figure 9, the meridian plane between the upper end of rotor blade 102 (entrance) and lower end (outlet) and the relative position I value representation of upper end and lower end, 0.0≤I≤1.0.Wherein, the meridian plane that waits I value is also referred to as equivalent meridian plane: I=0.0 when the upper end of equivalent meridian plane and rotor blade 102 is tangent, I=1.0 when the lower end of equivalent meridian plane and rotor blade 102 is tangent.
In the present invention, as shown in Figure 2 and Figure 6, the axial height of stator vane 202 radially increases from inside to outside gradually along stator 2, and the axial height of stator vane 202 is directly proportional to isometrical cylndrical surface radius.The axial height of rotor blade 102 radially increases from inside to outside gradually along rotor 1, and the axial height of rotor blade 102 is directly proportional to isometrical cylndrical surface radius.
As Fig. 1, shown in Fig. 5 and Fig. 9, stator vane 202 and rotor blade 102 are the blade that spot projection forms, described in each, the pressure side 106 of rotor blade and suction surface 105 intersects and forms two first-phases with equivalent meridian plane through this rotor blade and pass through straight line 111, described two first-phases pass through straight line 111 and intersect, wherein, the intersection point being positioned in described rotor centerline 113 is the first intersection point 112, described the first intersection point 112 is at rotor blade leading edge peak between the vertical projection point in rotor centerline and the vertical projection point of rotor blade trailing edge minimum point in rotor centerline, and the first intersection point 112 is unique, described in each, the pressure side 204 of stator vane and suction surface 205 intersects and forms two second-phases with equivalent meridian plane through this stator vane and pass through straight line 211, described two second-phases pass through straight line 211 and intersect, wherein, the intersection point being positioned on described stator center line 213 is the second intersection point 212, described the second intersection point 212 is at stator vane leading edge peak between the vertical projection point on stator center line and the vertical projection point of stator vane trailing edge minimum point on stator center line, and the second intersection point 212 is unique.
Further, as shown in Fig. 5 and Fig. 9, through two intersecting lines 111 of the equivalent meridian plane of the first intersection point 112 and the pressure side 104 of rotor blade 102 or suction surface 105, intersect at the first intersection point 112; Two intersecting lines 211 through the equivalent meridian plane of the second intersection point 212 and the pressure side 206 of stator vane 202 or suction surface 205 intersect at the second intersection point 212.
Further, as shown in Figure 4 and Figure 8, rotor blade 102 and the inclined setting of stator vane 202 with respect to rotor 1 and stator 2, and rotor blade 102 is contrary with the true dip direction of stator vane 202, i.e. stator vane established angle on same isometrical cylndrical surface and rotor blade established angle, opposite direction; Stator vane established angle on different isometrical cylndrical surface, radially equates; Rotor blade established angle on different described isometrical cylndrical surface, radially equates.
Further, as shown in Figure 3 and Figure 7, the circumferential thickness of stator vane 202 radially increases from inside to outside gradually along stator 2, and the circumferential thickness of rotor blade 102 radially increases from inside to outside gradually along rotor 1.
Further, as shown in Figure 1, Figure 2 with shown in Fig. 6, the axial height of stator and rotor is L=20～60mm, and stator outer diameter is D
se=50～300mm, rotor internal diameter is D
ri=20～200mm.
Further, as shown in Figure 1, Figure 2 with shown in Fig. 6, the axial height L of rotor integral shroud 103
1=7～20mm, stator integral shroud 203 axial height L
2=7～20mm; The axial height H of rotor blade 102
1=5～20mm, the axial height H of stator vane 202
2=5～20mm.
Further, as shown in Figure 1, Figure 2 with shown in Fig. 6, the inner circumference diameter of rotor integral shroud 103 is D
r1, the inner circumference diameter of stator body 201 is D
s1, the runner outer diameter D that this rotor combines
1=D
r1=D
s1=40～280mm; The boss 104 excircle diameters of rotor body 101 are D
r2, the excircle diameter of stator integral shroud 203 is D
s2, i.e. the runner inside diameter D of this rotor assemblying body
2=D
r2=D
s2=30～220mm; Runner outer diameter D
1with runner inside diameter D
2arithmetic mean value be average Flow diameter D, D=(D
1+ D
2)/2=35～250mm; Runner outer diameter D
1with runner inside diameter D
2half of difference be width of flow path h=h
r=h
s, h=(D
1-D
2)/2=5～100mm.(note: as required, D
r1with D
s1, D
r2with D
s2desirable different value.)
Further, as shown in Figure 3 and Figure 7, the blade number n of stator vane 202
2blade number n with rotor blade 102
1be respectively n
1=10～60, n
2=10～60, thus meet different operating mode demands.
Further, stator vane 202 is tangent with any two isometrical cylndrical surface, the leading edge 209 of stator vane is identical with the leading edge intersecting line shape that two stator vanes 202 that form are intersected in two isometrical cylndrical surface, and the trailing edge 210 of stator vane is also identical with the trailing edge intersecting line shape that two stator vanes 202 that form are intersected in two isometrical cylndrical surface; Rotor blade 102 is tangent with any two isometrical cylndrical surface, the leading edge of rotor blade 102 is identical with two rotor blade leading edge intersecting line shapes that formation is intersected in two isometrical cylndrical surface, and the trailing edge of rotor blade 102 is also identical with two rotor blade trailing edge intersecting line shapes that formation is intersected in two isometrical cylndrical surface.As shown in Figure 4 and Figure 8, the pitch between stator vane 202 is t
2, t
2=5.0～15.0mm; Pitch between rotor blade 102 is t
1, t
1=5.0～15.0mm.The inlet angle of stator vane 202 is α
2k, α
2k=30 °～150 °; The inlet angle of rotor blade 102 is β
1k, β
1k=30 °～150 °.The exit angle of stator vane 202 is α
1k, α
1k=5 °～85 °; The exit angle of rotor blade 102 is β
2k, β
2k=5 °～85 °.The leading-edge radius of stator vane 202 is r
21, r
21=0.1～3.0mm; Trailing edge radius is r
22, r
22=0.1～3.0mm.The leading-edge radius of rotor blade 102 is r
11, r
11=0.1～3.0mm; Trailing edge radius is r
12, r
12=0.1～3.0mm.The leading edge cone angle of stator vane 202 is
the leading edge cone angle of rotor blade 102 is
the trailing edge cone angle of stator vane 202 is
the trailing edge cone angle of rotor blade 102 is
the established angle of stator vane 202 is β
l2, β
l2=20 °～90 °; The established angle of rotor blade 102 is β
l1, β
l1=20 °～90 °.
Further, as shown in Fig. 5 and Fig. 9, the equivalent meridian plane of described stator vane or rotor blade and I=0.5 intersects, two of stator or rotor blade pressure side and suction surface and equivalent meridian plane pass through mutually straight line and all point to radial direction, and the circumferential thickness of stator vane and the circumferential thickness of rotor blade radially (from inside to outside) increase gradually.
It is worthy of note, the inlet angle of aforementioned turbine stator blade and rotor blade, exit angle, leading-edge radius, trailing edge radius, leading edge cone angle, trailing edge cone angle, blade angle, isometrical cylndrical surface, equivalent meridian plane are defined as the known technology of related domain, at this, no longer describe.
In sum, the present invention is by above-mentioned structural design, and that Novel turbine rotor assembly parts has advantages of is simple in structure, pressure drop is low, moment of torsion is large, hydraulic efficiency is high.
As shown in figure 11, be turbine motor embodiment's of the present invention cross-sectional view.The invention provides a kind of turbine motor, this turbine motor comprises turbine motor main shaft 31 and turbine motor housing 41, on turbine motor main shaft 31, be socketed with 50～300 grades of spot projection blade turbine rotor assembly parties as above, form the high pulling torque turbine motor with 50～300 grades of turbine rotors.Turbine motor, is applicable to diameter of phi 60～Φ 600mm well or eyelet and creeps into by turbodrill and Bottom Hole Assembly (BHA).
The foregoing is only the schematic embodiment of the present invention, not in order to limit scope of the present invention.Any those skilled in the art, not departing from equivalent variations and the modification of having done under the prerequisite of design of the present invention and principle, all should belong to the scope of protection of the invention.
Claims (8)
1. a spot projection blade turbine rotor assembly parts, comprises stator and the rotor of coaxial package, the centerline collineation of described stator and described rotor; Described stator comprises cylindric stator body, several stator vanes and the circular stator integral shroud of coaxial setting, described rotor comprises cylindric rotor body, several rotor blades and the circular rotor integral shroud of coaxial setting, the inwall of described stator integral shroud and described rotor body outer wall coaxial package, it is characterized in that: the axial height of described stator vane radially increases from inside to outside gradually along described stator, and is directly proportional to the isometrical cylndrical surface radius of described stator; The axial height of described rotor blade radially increases from inside to outside gradually along described rotor, and is directly proportional to the isometrical cylndrical surface radius of described rotor.
2. spot projection blade turbine rotor assembly parts as claimed in claim 1, it is characterized in that: the pressure side of rotor blade and suction surface and through the equivalent meridian plane of this rotor blade, intersect and form two first-phases and pass through straight line described in each, described two first-phases pass through straight line and intersect, wherein, the intersection point being positioned in described rotor centerline is the first intersection point, described the first intersection point is at rotor blade leading edge peak between the vertical projection point in rotor centerline and the vertical projection point of rotor blade trailing edge minimum point in rotor centerline, and described the first intersection point is unique, the pressure side of stator vane and suction surface and through the equivalent meridian plane of this stator vane, intersect and form two second-phases and pass through straight line described in each, described two second-phases pass through straight line and intersect, wherein, the intersection point being positioned on described stator center line is the second intersection point, described the second intersection point is at stator vane leading edge peak between the vertical projection point on stator center line and the vertical projection point of stator vane trailing edge minimum point on stator center line, and described the second intersection point is unique.
3. spot projection blade turbine rotor assembly parts as claimed in claim 1 or 2, is characterized in that: stator vane established angle and rotor blade established angle on same described isometrical cylndrical surface, opposite direction; Stator vane established angle on different described isometrical cylndrical surface, radially equates; Rotor blade established angle on different described isometrical cylndrical surface, radially equates.
4. spot projection blade turbine rotor assembly parts as claimed in claim 1 or 2, it is characterized in that: the circumferential thickness of described stator vane radially increases from inside to outside gradually along described stator, the circumferential thickness of described rotor blade radially increases from inside to outside gradually along described rotor.
5. spot projection blade turbine rotor assembly parts as claimed in claim 2, is characterized in that: the equivalent meridian plane of described the first intersection point of process and the pressure side of described rotor blade or the intersecting line of suction surface intersect at described the first intersection point; The equivalent meridian plane of described the second intersection point of process and the pressure side of described stator vane or the intersecting line of suction surface intersect at described the second intersection point.
6. spot projection blade turbine rotor assembly parts as claimed in claim 1 or 2, it is characterized in that: intersect described stator vane and any two isometrical cylndrical surface, the leading edge of described stator vane is identical with the leading edge intersecting line shape that two stator vanes that form are intersected in described two isometrical cylndrical surface, and the trailing edge of described stator vane is also identical with the trailing edge intersecting line shape that two stator vanes that form are intersected in described two isometrical cylndrical surface; Intersect described rotor blade and any two isometrical cylndrical surface, the leading edge of described rotor blade is identical with two rotor blade leading edge intersecting line shapes that formation is intersected in described two isometrical cylndrical surface, and the trailing edge of described rotor blade is also identical with two rotor blade trailing edge intersecting line shapes that formation is intersected in described two isometrical cylndrical surface.
7. a turbine motor, is characterized in that: described turbine motor comprises turbine motor main shaft and turbine motor housing, is socketed with the spot projection blade turbine rotor assembly parts as described in any one in claim 1 to 6 on described turbine motor main shaft.
8. turbine motor as claimed in claim 7, is characterized in that: described spot projection blade turbine rotor assembly parts is axially stacked with 50～300 along described turbine motor main shaft, forms the high pulling torque turbine motor with 50～300 grades of turbine rotors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| CN110145225A (en) * | 2019-05-17 | 2019-08-20 | 西南石油大学 | A kind of turbodrill worm gear pair with tandem cascade |
| CN113297710A (en) * | 2021-07-12 | 2021-08-24 | 中国地质大学（北京） | Twisted turbine blade, forming method, turbine and underground turbine drilling tool |
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