CN203867766U - Telescopic blade turbine stator and rotor assembly and turbine motor - Google Patents
Telescopic blade turbine stator and rotor assembly and turbine motor Download PDFInfo
- Publication number
- CN203867766U CN203867766U CN201420269282.0U CN201420269282U CN203867766U CN 203867766 U CN203867766 U CN 203867766U CN 201420269282 U CN201420269282 U CN 201420269282U CN 203867766 U CN203867766 U CN 203867766U
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- Prior art keywords
- rotor
- stator
- blade
- turbine
- stator vane
- Prior art date
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- Expired - Fee Related
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Classifications
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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
Abstract
The utility model provides a telescopic blade turbine stator and rotor assembly. The telescopic blade turbine stator and rotor assembly comprises a stator and a rotor which are coaxially arranged in a sleeved mode. The central axis of the stator and the central axis of the rotor are collinear. The stator comprises a cylindrical stator body, a plurality of stator blades and an annular stator blade crown which are coaxially arranged. The rotor comprises a cylindrical rotor body, a plurality of rotor blades and an annular rotor blade crown which are coaxially arranged. The inner wall of the stator blade crown and the outer wall of the rotor body are coaxially arranged in a sleeved mode. The multiple stator blades are circumferentially and obliquely arranged between the outer wall of the stator blade crown and the inner wall of the stator body. The multiple rotor blades are circumferentially and obliquely arranged between the outer wall of the rotor body and the inner wall of the rotor blade crown. The tilt direction of the stator blades is opposite to the tilt direction of the rotor blades. The telescopic blade turbine stator and rotor assembly is simple in structure, easy to machine and high in hydraulic efficiency. The utility model further provides a turbine motor with the telescopic blade turbine stator and rotor assembly, wherein the turbine motor is large in torque and suitable for drilling boreholes with various sizes.
Description
Technical field
The utility model relates to the field mud motors 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, 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, is made up of turbine motor, cardan shaft and transmission shaft three parts, 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, so far fail to obtain fine application at industrial and mineral scene, one of its major reason is due to defects such as existing turbodrill rotating speed are 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 the above-mentioned existing TURBODRILLING TECHNIQUE WITH TREMENDOUS TECHNICAL of China exists, the design people is based on being engaged in for a long time related scientific research and site test, to actively improvement and bring new ideas in addition of prior art, to realizing a kind of turbine rotor assembly parts and turbine motor of high pulling torque.
Model utility content
The purpose of this utility model is to provide a kind of high pulling torque, high efficiency, is applicable to turbine rotor assembly parts and turbine motor that needles of various sizes well is crept into.
For achieving the above object, the utility model proposes a kind of stretching blade turbine rotor assembly parts, comprise stator and the rotor of coaxial package, the central axis conllinear of described stator and described rotor, described stator comprises the cylindric stator body of coaxial setting, several stator vanes and circular stator integral shroud, described rotor comprises the cylindric rotor body of coaxial setting, several rotor blades and circular rotor integral shroud, the inwall of described stator integral shroud and described rotor body outer wall coaxial package, described in several, stator vane is arranged at described stator integral shroud outer wall between described stator body inwall along peripheral, oblique, described in several, rotor blade is arranged at described rotor body outer wall between described rotor integral shroud inwall along peripheral, oblique, and the tilt angle opposite direction of the tilt angle of described stator vane and described rotor blade.
As mentioned above stretching blade turbine rotor assembly parts, wherein, the stretching cross section of described stator vane and rotor blade respectively has one, and the stretching cross section of described stator vane is at the bottom of described stator leaf or the cross section of stator Ye Ding cylndrical surface isometrical with it; The stretching cross section of described rotor blade is at the bottom of described rotor leaf or the cross section of rotor Ye Ding cylndrical surface isometrical with it.
Stretching blade turbine rotor assembly parts as mentioned above, wherein, the stretching guide line of described stator vane and rotor blade respectively has one, the stretching guide line of described stator vane be along described stator body radially perpendicular to the straight line of the trailing edge mid point of described stator vane; The stretching guide line of described rotor blade be along described rotor body radially perpendicular to the straight line of the leading edge mid point of described rotor blade.
Stretching blade turbine rotor assembly parts as mentioned above, wherein, the tilt angle of each described stator vane or the tilt angle of each described rotor blade are along radial dimension is equal separately, direction is identical.
Stretching blade turbine rotor assembly parts as mentioned above, wherein, the circumferential thickness of each described stator vane or each described rotor blade is along radial dimension is equal separately.
Stretching blade turbine rotor assembly parts as mentioned above, wherein, the axial height of each described stator vane or each described rotor blade is along radial dimension is equal separately.
The utility model also provides a kind of turbine motor, comprises turbine motor main shaft and motor casing, is socketed with stretching blade turbine rotor assembly parts as above on described turbine motor main shaft.
Turbine motor as mentioned above, wherein, described stretching 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.
The utility model stretching blade turbine rotor assembly parts, comprise rotor and the stator of coaxial package, described rotor comprises rotor body cylindraceous, several rotor blades and circular rotor integral shroud, be provided with the boss radially protruding in described rotor body one end periphery, 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.Described stator vane and described rotor blade are to stretch and form, blade inlet edge is thick, trailing edge is thin, be the stator vane blade three dimensional design curved surface of serving as reasons on isometrical cylndrical surface at the bottom of stator leaf along trailing edge mid point spoon of blade radially vertical line be stretched to leaf and push up isometrical cylndrical surface and form, or the stator vane isometrical cylndrical surface at the bottom of stator leaf pushes up blade three dimensional design curved surface on isometrical cylndrical surface radially vertical line is stretched to leaf along trailing edge mid point spoon of blade of serving as reasons forms; The blade three dimensional design curved surface that rotor blade is served as reasons on isometrical cylndrical surface at the bottom of rotor leaf along leading edge mid point spoon of blade radially vertical line be stretched to leaf and push up isometrical cylndrical surface and form, or the rotor blade isometrical cylndrical surface at the bottom of rotor leaf pushes up blade three dimensional design curved surface on isometrical cylndrical surface radially vertical line is stretched to leaf along leading edge mid point spoon of blade of serving as reasons forms.The stretching cross section of described stator vane and rotor blade respectively has one, be respectively at the bottom of stator leaf or leaf push up blade three dimensional design curved surface on isometrical cylndrical surface, at the bottom of rotor leaf or leaf push up the blade three dimensional design curved surface on isometrical cylndrical surface; The stretching guide line of described stator vane and rotor blade also respectively has one, is respectively the radially radially vertical line of spoon of blade of vertical line, process rotor blade leading edge mid point of spoon of blade through stator vane trailing edge mid point.The circumferential thickness of described stator vane or rotor blade is constant along stretching guide line, axial height radially equates, the tilt angle of described stator vane on an isometrical cylndrical surface in office and the tilt angle opposite direction of described rotor blade (right-hand rule: stator vane dextrorotation, rotor blade is left-handed), the tilt angle of each described stator vane or tilt angle equal and opposite in direction, the direction of each described rotor blade on an isometrical cylndrical surface in office are identical.Described stator vane trailing edge stretching guide line, rotor blade leading edge stretching guide line all point to radial direction.Described stator or rotor blade pressure side and suction surface with etc. I value (I value is the relative position of arbitrary plane vertical with stator or rotor axis and leading edge and trailing edge between turbine stage rotor blade inlet edge and trailing edge; As this plane and leading edge peak I=0 during in same position, when this plane with trailing edge peak I=1.0 during in same position) to pass through mutually straight line parallel with stator or rotor radius direction for two of meridian plane.
The stretching guide line of described stator vane and rotor blade except the aforementioned spoon of blade through stator vane trailing edge mid point radially vertical line, radially vertical line, respectively have another through the spoon of blade of rotor blade leading edge mid point: they be respectively through the spoon of blade of other any point except trailing edge mid point on stator vane trailing edge radially vertical line, through the radially vertical line of spoon of blade of other any point except leading edge mid point in rotor blade leading edge.
Compared with prior art, the utlity model has following characteristics and advantage:
1, the utility model turbine rotor assembly parts hydraulic efficiency is high.
2, the utility model turbine motor is simple in structure, moment of torsion is large, is suitable for needles of various sizes well and creeps into.
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 the utility model instruction, can select various possible shapes and proportional sizes to implement the utility model as the case may be.
Fig. 1 is the utility model stretching blade turbine rotor assembly parts embodiment's biopsy cavity marker devices perspective view;
Fig. 2 is the utility model embodiment's stator cross-sectional view;
Fig. 3 is the utility model embodiment's stator stereochemical structure part cut-away illustration;
Fig. 4 is that the utility model embodiment's stator vane pushes up isometrical cylndrical surface (S=1) expansion schematic diagram along leaf;
Fig. 5 is that the utility model embodiment's stator is along equivalent meridian plane (I=0.5) cut-away illustration;
Fig. 6 is the utility model embodiment's rotor profiles structural representation;
Fig. 7 is the utility model embodiment's rotor stereochemical structure part cut-away illustration;
Fig. 8 is that the utility model embodiment's rotor blade pushes up isometrical cylndrical surface (S=1) expansion schematic diagram along leaf;
Fig. 9 is that the utility model embodiment's rotor is along equivalent meridian plane (I=0.5) cut-away illustration;
Figure 10 is the utility model embodiment turbine motor cross-sectional view.
Description of reference numerals:
1-rotor; 101-rotor body; 102-rotor blade; 103-rotor integral shroud; 104-boss; 105-rotor blade pressure side; 106-rotor blade suction surface; 107-rotor leaf top; At the bottom of 108-rotor leaf; 109-rotor blade leading edge; 110-rotor blade trailing edge.
2-stator; 201-stator body; 202-stator vane; 203-stator integral shroud; 204-stator vane suction surface; 205-stator vane pressure side; 207-stator leaf top; At the bottom of 208-stator leaf; 209-stator vane leading edge; 210-stator vane trailing edge.
Embodiment
With the description of the utility model embodiment, can more be well understood to details of the present utility model by reference to the accompanying drawings.But embodiment 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 the utility model instruction, 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 utility model stretching blade turbine rotor assembly parts embodiment's biopsy cavity marker devices perspective view; Fig. 2 is the utility model embodiment's stator cross-sectional view; Fig. 3 is the utility model embodiment's stator stereochemical structure part cut-away illustration; Fig. 4 is that the utility model embodiment's stator vane pushes up isometrical cylndrical surface (S=1) expansion schematic diagram along leaf; Fig. 5 is that the utility model embodiment's stator is along equivalent meridian plane (I=0.5) cut-away illustration; Fig. 6 is the utility model embodiment's rotor profiles structural representation; Fig. 7 is the utility model embodiment's rotor stereochemical structure part cut-away illustration; Fig. 8 is that the utility model embodiment's rotor blade pushes up isometrical cylndrical surface (S=1.0) expansion schematic diagram along leaf; Fig. 9 is that the utility model embodiment's rotor is along equivalent meridian plane (I=0.5) cut-away illustration; Figure 10 is the utility model embodiment turbine motor cross-sectional view.
As shown in Figures 1 to 10, the stretching blade turbine rotor assembly parts the utility model proposes, comprises stator 2 and the rotor 1 of coaxial package, the central axis conllinear of stator 2 and rotor 1; As shown in Figures 2 to 5, stator 2 comprises cylindric stator body 201, several stator vanes 202 and the circular stator integral shroud 203 of coaxial setting.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-structure.Several stator vanes 202 are arranged at described stator integral shroud 203 outer walls between stator body 201 inwalls along stator body 201 peripheral, oblique.As shown in Figures 6 to 9, rotor 1 comprises cylindric rotor body 101, several rotor blades 102 and the circular rotor integral shroud 103 of coaxial setting, be provided with the boss 104 radially protruding in one end of rotor body 101 periphery, several rotor blades 102 are laid along boss 104 surface uniforms of the excircle of rotor body 101, rotor integral shroud 103 is socketed on the leaf top of rotor blade 102, makes rotor body 101, blade 102, rotor integral shroud 103 form the rotor 1 of integrative-structure.As shown in Figure 1, the inwall of stator integral shroud 203 and rotor body 101 outer wall coaxial packages, and stator body 201 is coaxial with the axis of rotor body 101, 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 utility model, the blade profile of stator vane 202 and rotor blade 102 is to stretch and 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 any number of and stator body 201 and stator integral shroud 203 cylndrical surface of central axis altogether, each cylndrical surface is referred to as an isometrical cylndrical surface.Stator leaf top 207 and the arbitrary isometrical cylndrical surface between 208 and stator leaf at the bottom of stator leaf push up 207 and stator leaf at the bottom of 208 relative position S value representation, 0≤S≤1.0: as isometrical cylndrical surface S=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 any number of and rotor body 101 and rotor integral shroud 103 cylndrical surface of central axis altogether, 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 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.Be set with superimposed setting because stator 2 and rotor 1 are total to central axis up and down, therefore the isometrical cylndrical surface on isometrical cylndrical surface and the rotor 1 on the stator 2 that waits S value is same isometrical cylndrical surface.
In the utility model, the plane intersecting vertically with the central 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, 0.0≤I≤1.0.Wherein, wait the meridian plane of I value to be called equivalent meridian plane: I=0.0 in the time that the upper end of equivalent meridian plane and stator vane 202 is tangent, I=1.0 in the time that 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 in the time that the upper end of equivalent meridian plane and rotor blade 102 is tangent, I=1.0 in the time that the lower end of equivalent meridian plane and rotor blade 102 is tangent.
As shown in Fig. 4, Fig. 8, stator vane 202 and rotor blade 102 are the blade that stretches and form, and the line between 2, the line between 2, the leading edge 209 circular arc centers of circle of stator vane 202 and the trailing edge 210 circular arc center of circle, the leading edge 109 circular arc centers of circle of rotor blade 102 and the trailing edge 110 circular arc center of circle forms a tilt angle (claiming again established angle) with equivalent meridian plane separately respectively, and stator vane angle of inclination beta on same isometrical cylndrical surface
l2with rotor blade angle of inclination beta
l1opposite direction.The tilt angle of each described stator vane or tilt angle equal and opposite in direction, the direction of each described rotor blade on an isometrical cylndrical surface in office are identical.
Further, as shown in Fig. 4, Fig. 8, the blade inlet edge 209 of stator vane 202 is thick, trailing edge 210 is thin, forms sickleshaped; Same, the blade inlet edge 109 of rotor blade 102 is thick, trailing edge 110 is thin, also forms sickleshaped.On an isometrical cylndrical surface in office, (the leading edge radius of arc pushing up on isometrical cylndrical surface at leaf is r for the leading edge 209 of stator vane 202 and trailing edge 210
21, trailing edge radius of arc is r
22, and r
21>=r
22) tangent with the profile line of pressure side 205, suction surface 204 respectively; The leading edge 109 of rotor blade 102 and trailing edge 110 (push up the leading edge radius of arc r on isometrical cylndrical surface at leaf
11, trailing edge radius of arc is r
12, and r
11>=r
12) tangent with the profile line of pressure side 105, suction surface 106 respectively.Can greatly reduce like this hydraulic loss.
Further, the outer contour of stator vane 202 comprise at the bottom of stator leaf top 207, stator leaf 208, stator vane pressure side 205 and stator vane suction surface 204; The outer contour of rotor blade 102 comprises at the bottom of rotor leaf top 107, rotor leaf 108, rotor blade pressure side 105 and rotor blade suction surface 106.The stretching cross section of stator vane 202 and rotor blade 102 respectively has one, and the stretching cross section of stator vane 202 is at the bottom of stator leaf 208 or the cross section of 207 cylndrical surface isometrical with it, stator leaf top; The stretching cross section of rotor blade 102 is at the bottom of rotor leaf 108 or the cross section of 107 cylndrical surface isometrical with it, rotor leaf top.
Further, the stretching guide line of stator vane 202 and rotor blade 102 respectively has one, the stretching guide line of stator vane 202 be along stator body 201 radially perpendicular to the straight line of the trailing edge mid point of stator vane 202; The stretching guide line of rotor blade 102 be along rotor body 101 radially perpendicular to the straight line of the leading edge mid point of rotor blade 102.
Further, on an isometrical cylndrical surface in office, the circumferential thickness of each stator vane 202 or each rotor blade 102 or axial height equate.
Further, as shown in Figure 2 and Figure 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, Figure 6 shows, 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=7～20mm, the axial height H of stator vane 202
2=7～20mm.
Further, as shown in Figure 1, Figure 2, Figure 6 shows, the inner circumference diameter of rotor integral shroud 103 is D
r1, the inner circumference diameter of stator body 201 is D
s1, i.e. the runner outer diameter D of this rotor combination
1=D
r1=D
s1=40～280mm; The excircle diameter of the boss 104 of rotor body 101 is D
r2, the excircle diameter of stator integral shroud 203 is D
s2, i.e. the runner inner diameter D of this rotor assemblying body
2=D
r2=D
s2=30～220mm; Runner outer diameter D
1with runner inner diameter D
2arithmetic mean value be average Flow diameter D, D=(D
1+ D
2)/2=35～250mm; 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=5～100mm.(note: as required, D
r1with D
s1, D
r2with D
s2desirable different value.)
Further, as shown in Figure 3 and Figure 7, described stator vane trailing edge 210 mid point guide lines, rotor blade leading edge 209 mid point guide lines point to radial direction; 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, to meet different operating mode demands.
Further, as shown in Figure 4 and Figure 8, the pitch between each stator vane 202 is t
2, t
2=5.0～15.0mm; Pitch between each 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, it is parallel with stator or rotor radius direction that described stator or rotor blade pressure side and suction surface and equivalent meridian plane two are passed through straight line mutually.
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 are defined as the known technology of related domain, no longer describe at this.
In sum, the utility model 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.
Figure 10 shows that the utility model turbine embodiment one motor cross-sectional view.The utility model provides a kind of turbine motor, and this turbine motor comprises turbine motor main shaft 31 and turbine motor housing 41, is socketed with 50～300 grades of turbine rotor assembly parties as above on turbine motor main shaft 31.It is that Φ 50～Φ 600mm well or eyelet creep into by turbodrill and Bottom Hole Assembly (BHA) that above-mentioned turbine motor is applicable to diameter.
For the each detailed explanation of above-mentioned mode of execution, its object is only the utility model to make an explanation, to 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, also combination in any mutually of each feature of describing in different mode of executions, thus form other mode of execution.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 mode of execution.
Claims (7)
1. a stretching blade turbine rotor assembly parts, comprise stator and the rotor of coaxial package: the central axis conllinear of described stator and described rotor, described stator comprises the cylindric stator body of coaxial setting, several stator vanes and circular stator integral shroud, described rotor comprises the cylindric rotor body of coaxial setting, several rotor blades and circular rotor integral shroud, the inwall of described stator integral shroud and described rotor body outer wall coaxial package, it is characterized in that: described in several, stator vane is arranged at described stator integral shroud outer wall between described stator body inwall along peripheral, oblique, described in several, rotor blade is arranged at described rotor body outer wall between described rotor integral shroud inwall along peripheral, oblique, and the tilt angle opposite direction of the tilt angle of described stator vane and described rotor blade, the stretching cross section of described stator vane and rotor blade respectively has one, the stretching cross section of described stator vane is at the bottom of described stator leaf or the cross section of stator Ye Ding cylndrical surface isometrical with it, and the stretching cross section of described rotor blade is at the bottom of described rotor leaf or the cross section of rotor Ye Ding cylndrical surface isometrical with it.
2. blade turbine rotor assembly parts as claimed in claim 1 stretches, it is characterized in that: the stretching guide line of described stator vane and rotor blade respectively has one, the stretching guide line of described stator vane be along described stator body radially perpendicular to the straight line of the trailing edge mid point of described stator vane, the stretching guide line of described rotor blade be along described rotor body radially perpendicular to the straight line of the leading edge mid point of described rotor blade.
3. the blade turbine rotor assembly parts that stretches as claimed in claim 2, is characterized in that: the tilt angle of each described stator vane or the tilt angle of each described rotor blade along radial dimension separately equate, direction is identical.
4. the blade turbine rotor assembly parts that stretches as claimed in claim 2, is characterized in that: the circumferential thickness of each described stator vane or each described rotor blade equates along radial dimension separately.
5. the blade turbine rotor assembly parts that stretches as claimed in claim 2, is characterized in that: the axial height of each described stator vane or each described rotor blade equates along radial dimension separately.
6. a turbine motor, is characterized in that: described turbine motor comprises turbine motor main shaft and motor casing, is socketed with the stretching blade turbine rotor assembly parts as described in any one in claim 1 to 5 on described turbine motor main shaft.
7. turbine motor as claimed in claim 6, is characterized in that: described stretching 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 |
|---|---|---|---|
| CN201420269282.0U CN203867766U (en) | 2014-05-23 | 2014-05-23 | Telescopic blade turbine stator and rotor assembly and turbine motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420269282.0U CN203867766U (en) | 2014-05-23 | 2014-05-23 | Telescopic blade turbine stator and rotor assembly and turbine motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203867766U true CN203867766U (en) | 2014-10-08 |
Family
ID=51648730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420269282.0U Expired - Fee Related CN203867766U (en) | 2014-05-23 | 2014-05-23 | Telescopic blade turbine stator and rotor assembly and turbine motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203867766U (en) |
-
2014
- 2014-05-23 CN CN201420269282.0U patent/CN203867766U/en not_active Expired - Fee Related
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
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Granted publication date: 20141008 |