CN110145225A - A kind of turbodrill worm gear pair with tandem cascade - Google Patents
A kind of turbodrill worm gear pair with tandem cascade Download PDFInfo
- Publication number
- CN110145225A CN110145225A CN201910412258.5A CN201910412258A CN110145225A CN 110145225 A CN110145225 A CN 110145225A CN 201910412258 A CN201910412258 A CN 201910412258A CN 110145225 A CN110145225 A CN 110145225A
- Authority
- CN
- China
- Prior art keywords
- rotor
- stator
- tandem
- blade
- aeroengine
- 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.)
- Pending
Links
- 239000012530 fluid Substances 0.000 claims abstract description 18
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 7
- 239000000411 inducer Substances 0.000 claims description 6
- 238000005553 drilling Methods 0.000 abstract description 8
- 238000004804 winding Methods 0.000 abstract description 3
- 239000007788 liquid Substances 0.000 description 10
- 238000010586 diagram Methods 0.000 description 5
- 210000001652 frontal lobe Anatomy 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000008719 thickening Effects 0.000 description 2
- 241001074085 Scophthalmus aquosus Species 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 230000005404 monopole Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
Classifications
-
- E—FIXED CONSTRUCTIONS
- E21—EARTH OR ROCK DRILLING; MINING
- E21B—EARTH OR ROCK DRILLING; OBTAINING OIL, GAS, WATER, SOLUBLE OR MELTABLE MATERIALS OR A SLURRY OF MINERALS FROM WELLS
- E21B4/00—Drives for drilling, used in the borehole
- E21B4/02—Fluid rotary type drives
-
- E—FIXED CONSTRUCTIONS
- E21—EARTH OR ROCK DRILLING; MINING
- E21B—EARTH OR ROCK DRILLING; OBTAINING OIL, GAS, WATER, SOLUBLE OR MELTABLE MATERIALS OR A SLURRY OF MINERALS FROM WELLS
- E21B7/00—Special methods or apparatus for drilling
- E21B7/04—Directional drilling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
- F03B3/12—Blades; Blade-carrying rotors
- F03B3/121—Blades, their form or construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
- F03B3/16—Stators
- F03B3/18—Stator blades; Guide conduits or vanes, e.g. adjustable
- F03B3/183—Adjustable vanes, e.g. wicket gates
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Geology (AREA)
- Life Sciences & Earth Sciences (AREA)
- Mining & Mineral Resources (AREA)
- Mechanical Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Environmental & Geological Engineering (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- General Life Sciences & Earth Sciences (AREA)
- Geochemistry & Mineralogy (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to the turbodrill worm gear pairs for one of oil/gas drilling with tandem cascade, are made of stator, rotor.The stator is made of stator tandem cascade, stator integral shroud, stator wheel hub, stator Tandem Blades To An Aeroengine in stator tandem cascade is made of stator front vane and stator rear blade, streamwise, stator front vane is located at upstream, stator rear blade is located at downstream, and stator vane gap is provided at the maximum camber of stator Tandem Blades To An Aeroengine.The rotor is made of rotor tandem cascade, rotor integral shroud, rotor hub, rotor Tandem Blades To An Aeroengine in rotor tandem cascade is made of rotor front vane and rotor rear blade, streamwise, rotor front vane is located at upstream, rotor rear blade is located at downstream, and rotor blade gap is provided at the maximum camber of rotor Tandem Blades To An Aeroengine.Because of the generation of gap stream when fluid winding flow rotor Tandem Blades To An Aeroengine, improve its boundary-layer distribution situation, is conducive to the torque and efficiency that improve single-stage turbine pair.
Description
Technical field
The present invention relates to the turbodrill worm gear pairs for one of oil/gas drilling engineering with tandem cascade, belong to
Oil and gas well drilling apparatus field.
Background technique
In oil gas and geological drilling engineering, turbodrill is widely used in the drilling of ultradeep well, high temperature well, directional well etc.
In the process.It by the core component that drilling fluid liquid can switch to turbine wheel shaft mechanical energy is exactly worm gear pair in turbodrill, a secondary turbine
Include the stator with annular cascade and the rotor with annular cascade in pair.In turbodrill used today, worm gear pair
Middle rotor leaf grating is single cascade, and turbodrill radial dimension is because of the constraint by borehole size, cascade blade length
It cannot design too long.To improve the torque of monopole turbine, often increase inlet and outlet liquid stream by increasing the bent angle of vane foil
Liquid stream turning angle mode come increase inlet and outlet speed variable quantity.Excessive blade profile bent angle and liquid stream turning angle will cause leaf
Grid efficiency reduces, and leaf grating hydraulic loss increases, and entire turbodrill pressure consumption increases, and the pump pressure of face-pumping requires higher over the ground.Especially
It is minor diameter turbodrill, because of the through-current capability of radial dimension limitation turbine, and the radius of gyration reduces, in order to improve its single-stage whirlpool
Wheel set output torque can only increase blade profile bent angle, therefore the blade profile bent angle of minor diameter turbodrill is bigger compared to conventional turbine drilling tool,
Its hydraulic efficiency is lower, and pressure consumption is bigger.In order to solve big bent angle and big liquid stream turning angle bring relevant issues, band string can be used
The worm gear pair of column leaf grating.
Summary of the invention
It is an object of the invention to the growth requirements to meet the prior art, provide a kind of turbine brill with tandem cascade
Has worm gear pair, to improve the output torque and efficiency of worm gear pair.
The technical scheme adopted by the invention is that:
A kind of turbodrill worm gear pair with tandem cascade of the present invention, is made of stator, rotor.The stator is by stator
Tandem cascade, stator integral shroud, stator wheel hub are constituted.Stator tandem cascade is made of several groups stator Tandem Blades To An Aeroengine, stator tandem
Blade is made of stator front vane and stator rear blade, streamwise, and stator front vane is located at upstream, and stator rear blade is located at
Downstream, and two blades head and the tail are sequentially connected, and connecting place is provided with stator vane gap.Stator front vane and stator rear blade
Geometric parameter constitutes the geometric parameter of entire stator Tandem Blades To An Aeroengine.The setting of stator vane gap is maximum in entire stator Tandem Blades To An Aeroengine
At camber, and the width streamwise in stator vane gap does not increase.At stator vane gap, the trailing edge of stator front vane
The leading edge of relative stator rear blade is in the downstream position of fluid flowing, the i.e. outlet section of stator front vane and stator rear blade
There are certain coincidence length for inducer, which ensure that fluid is successfully transitioned into stator rear blade from stator front vane, it is fixed to allow
Some in the fluid of sub- front vane pressure face outflow can reach the suction surface of stator rear blade by stator vane gap.
Due to the generation that gap is flowed in stator vane gap, the growth and thickening of stator front vane boundary-layer are terminated, and after stator
Blade inlet edge initially forms new boundary-layer, this greatly reduces the separation degree of the boundary-layer, reduces fluid winding flow leaf
Flowing hydraulic loss when piece.The respective blade profile bent angle of stator front vane, stator rear blade constitutes the leaf of stator Tandem Blades To An Aeroengine
Type bent angle, by adjusting stator front vane, stator rear blade positional relationship, it can be achieved that stator front vane, stator rear blade are each
The total biggish blade profile bent angle of entire stator Tandem Blades To An Aeroengine is realized from lesser blade profile bent angle, to realize that liquid stream is biggish
Liquid stream turning angle.
The rotor is made of rotor tandem cascade, rotor integral shroud, rotor hub.Rotor tandem cascade is by several group rotors
Tandem Blades To An Aeroengine composition, rotor Tandem Blades To An Aeroengine are made of rotor front vane and rotor rear blade, streamwise, rotor front vane position
In upstream, rotor rear blade is located at downstream, and two blades head and the tail are sequentially connected, and connecting place is provided with rotor blade gap.Turn
The geometric parameter of sub- front vane and rotor rear blade constitutes the geometric parameter of entire rotor Tandem Blades To An Aeroengine.The setting of rotor blade gap
At entire rotor Tandem Blades To An Aeroengine maximum camber, and the width streamwise in rotor blade gap does not increase.In rotor blade
At gap, the leading edge of the trailing edge relative rotor rear blade of rotor front vane is in the downstream position of fluid flowing, i.e. rotor frontal lobe
There are certain to be overlapped length with the inducer of rotor rear blade for the outlet section of piece, which ensure that fluid is successfully from rotor frontal lobe
Piece is transitioned into rotor rear blade, some in the fluid for allowing rotor front vane pressure face to flow out can be by rotor blade gap
Reach the suction surface of rotor rear blade.Due to the generation that gap is flowed in rotor blade gap, rotor front vane boundary-layer is terminated
Growth and thickening, and new boundary-layer is initially formed in rear blade leading edge, this greatly reduces the separation journey of the boundary-layer
Degree, reduces flowing hydraulic loss when fluid winding flow blade.The respective blade profile bent angle of rotor front vane, rotor rear blade is constituted
The blade profile bent angle of rotor Tandem Blades To An Aeroengine, by adjusting rotor front vane, rotor rear blade positional relationship, it can be achieved that before rotor
Blade, rotor rear blade respectively realize the total biggish blade profile bent angle of entire rotor Tandem Blades To An Aeroengine with lesser blade profile bent angle,
To realize the biggish liquid stream turning angle of liquid stream, so that the inlet and outlet speed difference of inlet and outlet liquid stream in the rotor increases, improve single
The output torque and efficiency of grade rotor.
Compared with prior art, the present invention the beneficial effect is that: 1. under identical size condition, can increase single-stage turbine
Secondary output torque and efficiency reduces the series of turbodrill worm gear pair, shortens turbodrill overall length, is conducive to Directional Drilling
Into；2. may make turbodrill that can export high torque, and there is greater efficiency, especially under minor diameter and small flow rate
It is suitable for feel ahead turbodrill.
Detailed description of the invention
Fig. 1 is a kind of partial cutaway structural schematic diagram of the turbodrill worm gear pair with tandem cascade of the present invention；
Fig. 2 is the partial cutaway structural schematic diagram of stator in Fig. 1；
Fig. 3 is stator Tandem Blades To An Aeroengine schematic diagram in Fig. 1；
Fig. 4 is the partial cutaway structural schematic diagram of rotor in Fig. 1；
Fig. 5 is the sub- Tandem Blades To An Aeroengine schematic diagram of Fig. 1 transfer.
In figure: 1. stator integral shrouds, 2. stator wheel hubs, 3. stator front vanes, 4. stator rear blades, 5. rotor hubs, 6. turns
Cotyledon hat, 7. rotor front vanes, 8. rotor rear blades, a. stator vane gap, b. rotor blade gap.
Specific embodiment
Embodiment of the present invention is illustrated with reference to the accompanying drawing.
As shown in figure 1, figure 2, figure 3, figure 4 and figure 5, a kind of turbodrill worm gear pair with tandem cascade of the present invention, by fixed
Son, rotor are constituted.As shown in Figure 1, Figure 2, Figure 3 shows, the stator is made of stator tandem cascade, stator integral shroud 1, stator wheel hub 2.
Stator tandem cascade is made of several groups stator Tandem Blades To An Aeroengine, and stator Tandem Blades To An Aeroengine is by stator front vane 3 and 4 groups of stator rear blade
At stator Tandem Blades To An Aeroengine is arranged on stator wheel hub 2, and has stator integral shroud 1.Streamwise, stator front vane 3 are located at upper
Trip, stator rear blade 4 is located at downstream, and two blades head and the tail are sequentially connected, and connecting place is provided with stator vane gap a.Stator
The geometric parameter of front vane 3 and stator rear blade 4 constitutes the geometric parameter of entire stator Tandem Blades To An Aeroengine.Stator vane gap a is set
It sets at entire stator Tandem Blades To An Aeroengine maximum camber, and the width streamwise of stator vane gap a does not increase.In stator leaf
At a of piece gap, the leading edge of the trailing edge relative stator rear blade 4 of stator front vane 3 is in the downstream position of fluid flowing, i.e. stator
There are certain to be overlapped length with the inducer of stator rear blade 4 for the outlet section of front vane 3, which ensure that fluid is successfully from fixed
Sub- front vane 3 is transitioned into stator rear blade 4, some in the fluid for allowing 3 pressure face of stator front vane to flow out can be by fixed
The suction surface of blades gap a arrival stator rear blade 4.Stator front vane 3, the respective blade profile bent angle of stator rear blade 4 are constituted
The blade profile bent angle of stator Tandem Blades To An Aeroengine, by adjusting stator front vane 3, stator rear blade 4 positional relationship, it can be achieved that entire
The total biggish blade profile bent angle of stator Tandem Blades To An Aeroengine.
The rotor is made of rotor tandem cascade, rotor integral shroud 6, rotor hub 5.Rotor tandem cascade is turned by several groups
Substring column blade composition, rotor Tandem Blades To An Aeroengine are made of rotor front vane 7 and rotor rear blade 8, and rotor Tandem Blades To An Aeroengine is arranged in
On rotor hub 5, and have rotor integral shroud 6.Streamwise, rotor front vane 7 is located at upstream, under rotor rear blade 8 is located at
Trip, and two blades head and the tail are sequentially connected, and connecting place is provided with rotor blade gap b.Rotor front vane 7 and rotor rear blade 8
Geometric parameter constitute the geometric parameter of entire rotor Tandem Blades To An Aeroengine.Rotor blade gap b is arranged in entire rotor Tandem Blades To An Aeroengine
At maximum camber, and the width streamwise of rotor blade gap b does not increase.At the b of rotor blade gap, rotor front vane
The leading edge of 7 trailing edge relative rotor rear blade 8 be in fluid flowing downstream position, i.e., the outlet section of rotor front vane 7 with turn
There are certain coincidence length for the inducer of sub- rear blade 8, which ensure that fluid is successfully transitioned into rotor from rotor front vane 7
Rear blade 8, allow 7 pressure face of rotor front vane flow out fluid in some can pass through rotor blade gap b reach rotor
The suction surface of rear blade 8.Rotor front vane 7, the respective blade profile bent angle of rotor rear blade 8 constitute the blade profile of rotor Tandem Blades To An Aeroengine
Bent angle, by adjusting rotor front vane 7, rotor rear blade 8 positional relationship, it can be achieved that total biggish of 8 rotor Tandem Blades To An Aeroengines
Blade profile bent angle.
The bending direction of rotor Tandem Blades To An Aeroengine and stator Tandem Blades To An Aeroengine is opposite.
Claims (1)
1. a kind of turbodrill worm gear pair with tandem cascade, is made of stator, rotor, it is characterised in that: the stator by
Stator tandem cascade, stator integral shroud (1), stator wheel hub (2) are constituted, and stator tandem cascade is by several groups stator Tandem Blades To An Aeroengine group
At stator Tandem Blades To An Aeroengine is made of stator front vane (3) and stator rear blade (4), streamwise, stator front vane (3) position
In upstream, stator rear blade (4) is located at downstream, is provided with stator vane gap at the maximum camber of entire stator Tandem Blades To An Aeroengine
(a), and the width streamwise in stator vane gap (a) does not increase, at stator vane gap (a), stator front vane (3)
The leading edge of trailing edge relative stator rear blade (4) be in the downstream position of fluid flowing, the outlet section of stator front vane (3) and fixed
For the inducer of sub- rear blade (4) there are certain coincidence length, stator front vane (3), stator rear blade (4) respective blade profile are curved
The blade profile bent angle of angle composition stator Tandem Blades To An Aeroengine；The rotor is by rotor tandem cascade, rotor integral shroud (6), rotor hub (5) structure
At rotor tandem cascade is made of several rotor Tandem Blades To An Aeroengines, and rotor Tandem Blades To An Aeroengine is by rotor front vane (7) and rotor rear blade
(8) it forms, streamwise, rotor front vane (7) is located at upstream, and rotor rear blade (8) is located at downstream, in entire rotor tandem
Rotor blade gap (b) is provided at the maximum camber of blade, and the width streamwise in rotor blade gap (b) does not increase
Greatly, at rotor blade gap (b), the leading edge of the trailing edge relative rotor rear blade (8) of rotor front vane (7) is in fluid flowing
Downstream position, there are certain to be overlapped length with the inducer of rotor rear blade (8) for the outlet section of rotor front vane (7), turn
Sub- front vane (7), the respective blade profile bent angle of rotor rear blade (8) constitute the blade profile bent angle of rotor Tandem Blades To An Aeroengine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910412258.5A CN110145225A (en) | 2019-05-17 | 2019-05-17 | A kind of turbodrill worm gear pair with tandem cascade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910412258.5A CN110145225A (en) | 2019-05-17 | 2019-05-17 | A kind of turbodrill worm gear pair with tandem cascade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110145225A true CN110145225A (en) | 2019-08-20 |
Family
ID=67595506
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910412258.5A Pending CN110145225A (en) | 2019-05-17 | 2019-05-17 | A kind of turbodrill worm gear pair with tandem cascade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110145225A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1122486A (en) * | 1997-06-30 | 1999-01-26 | Kawasaki Heavy Ind Ltd | Compressor structure using tandem blade |
| US20090229883A1 (en) * | 2005-11-21 | 2009-09-17 | Hall David R | Flow Guide Actuation |
| CN103711631A (en) * | 2014-01-16 | 2014-04-09 | 中国石油大学(北京) | Turbine stator and rotor combination piece for linear projection blade and turbine motor |
| CN104074667A (en) * | 2014-07-03 | 2014-10-01 | 中国石油大学(北京) | Point projection blade turbine stator and rotor assembling unit and turbine motor |
| CN105840551A (en) * | 2016-04-15 | 2016-08-10 | 上海交通大学 | Pneumatic implementation method for multi-operating-point high-load compressor blades |
-
2019
- 2019-05-17 CN CN201910412258.5A patent/CN110145225A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1122486A (en) * | 1997-06-30 | 1999-01-26 | Kawasaki Heavy Ind Ltd | Compressor structure using tandem blade |
| US20090229883A1 (en) * | 2005-11-21 | 2009-09-17 | Hall David R | Flow Guide Actuation |
| CN103711631A (en) * | 2014-01-16 | 2014-04-09 | 中国石油大学(北京) | Turbine stator and rotor combination piece for linear projection blade and turbine motor |
| CN104074667A (en) * | 2014-07-03 | 2014-10-01 | 中国石油大学(北京) | Point projection blade turbine stator and rotor assembling unit and turbine motor |
| CN105840551A (en) * | 2016-04-15 | 2016-08-10 | 上海交通大学 | Pneumatic implementation method for multi-operating-point high-load compressor blades |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102287398B (en) | Small-sized high-speed centrifugal pump suitable for flow regulation in wide range | |
| CN101223355A (en) | Water turbine with bi-symmetric airfoil | |
| CN101960094A (en) | Blade with non-axisymmetric platform | |
| CN101598138A (en) | Secondary splitter blade type centrifugal impeller | |
| CN106194821A (en) | Centrifugal hydraulic turbine impeller and design method thereof | |
| CN108223386A (en) | A kind of large-scale bulb through-flow pump installation | |
| CN108829970A (en) | Axial fan blade optimum design method and optimization system based on vortex dynamics | |
| CN102364083A (en) | Long-short blade rotating wheel for mixed flow pump turbine | |
| CN104632701A (en) | High-bypass-ratio turbo-fan engine fan long-short blade structure | |
| CN102472114A (en) | Multi-stage radial turbine | |
| CN106256993A (en) | A kind of final stage moving blade of feed pump industrial steam turbine | |
| CN106762824A (en) | Axial flow blower 3 d impeller with leaf vein texture and sea-gull type splitterr vanes | |
| CN102536590A (en) | Two-stage through-flow turbine with ultralow specific speed | |
| CN111042869A (en) | Small centripetal turbine adopting axial air inlet mode with straight guide vanes | |
| CN102889237B (en) | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor | |
| CN201281045Y (en) | Conformal passage type diffuser | |
| CN110439724A (en) | A kind of francis turbine runner for hydraulic | |
| CN101363452A (en) | Conformality passage type diffuser and three-dimensional design method thereof | |
| CN101344059A (en) | Reverse S type runner of mixed-flow turbine | |
| CN103742204A (en) | Adjustable turbine | |
| JP2010168903A (en) | Centrifugal hydraulic machine | |
| CN110145225A (en) | A kind of turbodrill worm gear pair with tandem cascade | |
| CN202348525U (en) | Axial-flow rotary propeller type water turbine | |
| CN108443218B (en) | Pump impeller with secondary splitter blade | |
| CN100427753C (en) | Mixed flow type water turbin having H-type flow path rotary wheel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190820 |