CN101899966A - Be used for improving rig in the performance of high pressure pit shaft - Google Patents
Be used for improving rig in the performance of high pressure pit shaft Download PDFInfo
- Publication number
- CN101899966A CN101899966A CN2010101946205A CN201010194620A CN101899966A CN 101899966 A CN101899966 A CN 101899966A CN 2010101946205 A CN2010101946205 A CN 2010101946205A CN 201010194620 A CN201010194620 A CN 201010194620A CN 101899966 A CN101899966 A CN 101899966A
- Authority
- CN
- China
- Prior art keywords
- rig
- gun body
- carrier gun
- composite material
- nano composite
- 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
- 239000000463 material Substances 0.000 claims abstract description 90
- 239000002114 nanocomposite Substances 0.000 claims abstract description 73
- 230000000977 initiatory effect Effects 0.000 claims abstract description 5
- 239000002131 composite material Substances 0.000 claims description 19
- 238000000034 method Methods 0.000 claims description 15
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 14
- 229910045601 alloy Inorganic materials 0.000 claims description 14
- 239000000956 alloy Substances 0.000 claims description 14
- 238000003466 welding Methods 0.000 claims description 13
- 238000005507 spraying Methods 0.000 claims description 11
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 10
- CWYNVVGOOAEACU-UHFFFAOYSA-N Fe2+ Chemical compound [Fe+2] CWYNVVGOOAEACU-UHFFFAOYSA-N 0.000 claims description 9
- 238000005275 alloying Methods 0.000 claims description 7
- 229910052742 iron Inorganic materials 0.000 claims description 7
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 5
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 5
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 5
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 5
- 229910052796 boron Inorganic materials 0.000 claims description 5
- 229910052799 carbon Inorganic materials 0.000 claims description 5
- 229910052804 chromium Inorganic materials 0.000 claims description 5
- 239000011651 chromium Substances 0.000 claims description 5
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 claims description 5
- 229910052750 molybdenum Inorganic materials 0.000 claims description 5
- 239000011733 molybdenum Substances 0.000 claims description 5
- 229910052759 nickel Inorganic materials 0.000 claims description 5
- 229910052758 niobium Inorganic materials 0.000 claims description 5
- 239000010955 niobium Substances 0.000 claims description 5
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 5
- 229910052710 silicon Inorganic materials 0.000 claims description 5
- 239000010703 silicon Substances 0.000 claims description 5
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 5
- 229910052721 tungsten Inorganic materials 0.000 claims description 5
- 239000010937 tungsten Substances 0.000 claims description 5
- 229910052720 vanadium Inorganic materials 0.000 claims description 5
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims description 5
- 239000005300 metallic glass Substances 0.000 claims description 4
- 238000005474 detonation Methods 0.000 abstract description 4
- 238000002347 injection Methods 0.000 abstract description 2
- 239000007924 injection Substances 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 15
- 241000237509 Patinopecten sp. Species 0.000 description 14
- 235000020637 scallop Nutrition 0.000 description 14
- 229910052751 metal Inorganic materials 0.000 description 9
- 239000002184 metal Substances 0.000 description 9
- 229910000640 Fe alloy Inorganic materials 0.000 description 6
- 238000005336 cracking Methods 0.000 description 6
- 230000001066 destructive effect Effects 0.000 description 6
- 239000002159 nanocrystal Substances 0.000 description 6
- 230000015572 biosynthetic process Effects 0.000 description 5
- 238000005755 formation reaction Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 5
- 239000002360 explosive Substances 0.000 description 4
- 230000005484 gravity Effects 0.000 description 4
- 239000004215 Carbon black (E152) Substances 0.000 description 3
- 239000004568 cement Substances 0.000 description 3
- 238000004031 devitrification Methods 0.000 description 3
- 238000009826 distribution Methods 0.000 description 3
- 239000011521 glass Substances 0.000 description 3
- 229930195733 hydrocarbon Natural products 0.000 description 3
- 150000002430 hydrocarbons Chemical class 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000004567 concrete Substances 0.000 description 2
- 238000010891 electric arc Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 238000001338 self-assembly Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000035899 viability Effects 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 244000309464 bull Species 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002425 crystallisation Methods 0.000 description 1
- 230000008025 crystallization Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000000280 densification Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000005551 mechanical alloying Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000002086 nanomaterial Substances 0.000 description 1
- 238000006386 neutralization reaction Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000012255 powdered metal Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000001294 propane Substances 0.000 description 1
- QQONPFPTGQHPMA-UHFFFAOYSA-N propylene Natural products CC=C QQONPFPTGQHPMA-UHFFFAOYSA-N 0.000 description 1
- 125000004805 propylene group Chemical group [H]C([H])([H])C([H])([*:1])C([H])([H])[*:2] 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000002689 soil Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 238000001330 spinodal decomposition reaction Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
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
- E21B43/00—Methods or apparatus for obtaining oil, gas, water, soluble or meltable materials or a slurry of minerals from wells
- E21B43/11—Perforators; Permeators
- E21B43/116—Gun or shaped-charge perforators
- E21B43/117—Shaped-charge perforators
Landscapes
- Life Sciences & Earth Sciences (AREA)
- Engineering & Computer Science (AREA)
- Geology (AREA)
- Mining & Mineral Resources (AREA)
- Physics & Mathematics (AREA)
- Environmental & Geological Engineering (AREA)
- Fluid Mechanics (AREA)
- General Life Sciences & Earth Sciences (AREA)
- Geochemistry & Mineralogy (AREA)
- Coating By Spraying Or Casting (AREA)
- Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The present invention discloses a kind of rig (50), and it comprises the carrier gun body (52) with a plurality of radially sections of reducing (54).Radially the section of reducing (54) has nano composite material skin (72).Perforating bullet keeper (62) is set in carrier gun body (52).Support a plurality of lined-cavity charges (56) by perforating bullet keeper (62).Each lined-cavity charge (56) all has initiating terminal and ejecting end.The ejecting end of lined-cavity charge (56) is set to the radially section of reducing (54) of contiguous carrier gun body (52), and the injection thing that forms when making detonation of shaped charges (56) is advanced and passed the radially section of reducing (54).Radially the nano composite material skin (72) of the section of reducing (54) can improve the boring performance of rig (50) in high pressure and high temperature pit shaft.
Description
Technical field
The present invention briefly relates to a kind of use lined-cavity charge (shaped charge) well-sinking equipment of holing over the ground, and relates more specifically to a kind of rig that is used for improving in the performance of high temperature and high pressure pit shaft.
Background technology
Under the situation that does not limit the scope of the invention, will background of the present invention be described as an example about using the lined-cavity charge rig that hydrocarbon containing formation is holed.
After the part of passing hydrocarbon containing formation of well-sinking was holed over the ground, common metal tube with each length was fixed together and is positioned at the casing string of pit shaft with formation.This casing string has strengthened the globality of pit shaft, and a path is provided, can be via this path output to the face of land (surface) from the fluid on stratum.Traditionally, tubing string by cemented in pit shaft.For fluid is produced in the casing string, must form a plurality of hydraulic openings or the hole of passing casing string, cement and entering the stratum certain distance.
Usually, a series of lined-cavity charges that are positioned at one or more perforating guns by ignition produce these holes, and described one or more perforating guns are configured in the position on contiguous expectation stratum in the casing string.Routinely, perforating gun is formed by the hollow carrier gun body of the fluid-tight that is suitable for being put the wire rope (wire line) that falls in being sent to pit shaft or the sealing on the pipeline.Be provided with the perforating bullet keeper in hollow carrier gun body, it supports with selected spatial distribution and the location lined-cavity charge.Have in the lined-cavity charge and be restricted to conical explosive substance.The exploding wire that is used for detonation of shaped charges is positioned at the position at the rear portion of contiguous lined-cavity charge.When perforating gun has been set in the pit shaft, can light exploding wire by electricity or mechanical mode.
In the fluid-tight type rifle body of this sealing, the explosivity that produces during detonation of shaped charges is sprayed thing and penetrated hollow carrier gun body before the stratum of casing wall that penetrates pit shaft and vicinity.For the resistance that reduces to be produced by hollow carrier gun body and increase the degree of depth that is penetrated into the hole in the stratum, the perforating gun body can be provided with scallop or leave other section of reducing radially for explosive wall portion of spraying the relative thin that thing passes through, for example, and endless belt.Scallop in the hollow carrier gun body must be arranged on and be remained in the corresponding spatial distribution of spatial distribution of the lined-cavity charge in the rifle body by the perforating bullet keeper.
Yet find: near the thickness of the carrier gun body scallop place reaches has reduced to limit the intensity of perforating gun.Therefore, in order in the pit shaft of certain high pressure and high temperature, to hole the scallop degree of depth that the perforating gun of appointment external diameter must have increased wall thickness and/or reduce.In arbitrary situation, the performance of this perforating gun all decreases.Especially, the carrier gun body that uses wall thickness to increase makes the available space in the carrier gun body reduce, and this makes and must use littler lined-cavity charge.Similarly, the carrier gun body that uses the scallop degree of depth to reduce has limited the hole depth that is penetrated in the stratum.
Therefore, need a kind of rig that is used for carrier gun body high pressure and high temperature pit shaft, that do not need to increase wall thickness that be operable as.Also need a kind of rig that is used for carrier gun body high pressure and high temperature pit shaft, that do not need to reduce the scallop degree of depth that is operable as.In addition, need a kind of rig that is operable as the boring performance of raising in the high temperature and high pressure pit shaft.
Summary of the invention
The rig that the present invention includes the boring performance that is used for improving high pressure and high temperature pit shaft disclosed here.Rig of the present invention is operable as and is used for high pressure and high temperature pit shaft, and the carrier gun body (carrier gun body) that does not need to have increased wall thickness.In addition, rig of the present invention is operable as and is used for high pressure and high temperature pit shaft, and the carrier gun body that does not need to have scallop (scallop) degree of depth that reduces.
In a scheme, the present invention aims to provide a kind of rig that is used for high pressure and high temperature application.This rig comprises the carrier gun body with a plurality of radially sections of reducing, this radially the section of reducing have nano composite material skin (nanocomposite outer layer).The perforating bullet keeper is set in the carrier gun body.Support a plurality of lined-cavity charges by the perforating bullet keeper.Each lined-cavity charge has initiating terminal and ejecting end (discharge end), and is arranged so that the radially section of reducing of the contiguous carrier gun body of ejecting end.
In one embodiment, the radially section of reducing of carrier gun body is a groove.In another embodiment, the radially section of reducing of carrier gun body is endless belt (band).In certain embodiments, the outer field use of nano composite material is not limited to the radially section of reducing of carrier gun body.For example, the vicinity of carrier gun body radially the part of the section of reducing can have the nano composite material skin.Similarly, whole carrier gun body can have the nano composite material skin.Replacedly or additionally, the carrier gun body can have the nano composite material internal layer or can be made by nano composite material fully.
In one embodiment, all or part of the nano composite material of making the carrier gun body can be nano structured alloy (nanostructured alloy), for example, and nanometer iron-based alloy.In this embodiment, ferrous alloy can come from glassy metal.And, in this embodiment, the group that the optional free boron of the alloying component of ferrous alloy, carbon, chromium, iron, manganese, molybdenum, nickel, niobium, silicon, tungsten and vanadium are formed.
In one embodiment, can nanometer composite layer be coated on the carrier gun body by hot-spraying technique.In another embodiment, can nanometer composite layer be coated on the carrier gun body by welding procedure.In another embodiment, nanometer composite layer can be integrated with carrier gun body material.
In another program, the present invention aims to provide a kind of rig that high temperature and high pressure is used that is used for.This rig comprises the carrier gun body, and the external surface of this carrier gun body is made by nano composite material at least in part.The perforating bullet keeper is set in dispatch tube, and supports a plurality of lined-cavity charges by the perforating bullet keeper.
Description of drawings
Feature and advantage for a more complete understanding of the present invention now describe the present invention and accompanying drawing in detail, and in the accompanying drawings, the corresponding Reference numeral among each figure is represented corresponding parts, in the accompanying drawings:
Fig. 1 controls the schematic diagram of the marine oil and gas platform of rig according to an embodiment of the invention;
Fig. 2 is the partial sectional view of rig according to an embodiment of the invention;
Fig. 3 is the partial sectional view of rig according to an embodiment of the invention;
Fig. 4 is the cross-sectional view of the carrier gun body of rig according to an embodiment of the invention;
Fig. 5 is the cross-sectional view of the carrier gun body of rig according to an embodiment of the invention;
Fig. 6 is the cross-sectional view of the carrier gun body of rig according to an embodiment of the invention;
Fig. 7 is the cross-sectional view of the carrier gun body of rig according to an embodiment of the invention;
Fig. 8 is the cross-sectional view of the carrier gun body of rig according to an embodiment of the invention; And
Fig. 9 is the cross-sectional view of the carrier gun body of rig according to an embodiment of the invention.
The specific embodiment
Although elaborated structure and the use of each embodiment of the present invention below, should be realized that, the invention provides the many applicable inventive concept that can in various concrete conditions, implement.Specific embodiment described here is only as the example that makes up and use concrete mode of the present invention, and be scope demarcation of the present invention.
At first, schematically shown by the marine oil and gas platform and controlled rig of the present invention, and summary is expressed as 10 with reference to Fig. 1.Semisubmersible platform 12 is in the central authorities that are positioned at the hydrocarbon formations under water 14 below the seabed 16.Seabed pipeline 18 extends to the wellhead assembly 22 that comprises preventer 24 from the deck 20 of platform 12.Platform 12 has lifting means 26 and the drilling cramp 28 that is used for promoting and reducing tubing string (for example, work string 30).
Even Fig. 1 shows straight well, but those skilled in the art will appreciate that lined-cavity charge rig of the present invention is applicable in the well with other structure equally well, comprises high angle hole, inclined shaft, horizontal well, multilateral well etc.Therefore, use such as " top ", " below ", " on ", the D score directional terms to be conveniently to consult accompanying drawing.And, although Fig. 1 shows operation on the sea, those skilled in the art will appreciate that lined-cavity charge rig of the present invention is applicable to land operation equally well.
Referring now to Fig. 2, wherein show summary of the present invention and be expressed as 50 lined-cavity charge rig.Rig 50 comprises the carrier gun body of being made by sleeve (cylindrical sleeve) 52, and this sleeve has and shows a plurality of zones that radially reduce of making scallop or groove 54.Each lined-cavity charge of a plurality of lined-cavity charges 56 and each groove 54 radially aligneds.Each lined-cavity charge 56 comprises shell (for example, housing 58) and lining (for example, lining 60).Between each housing and lining, place a large amount of high explosives.
Lined-cavity charge 56 is remained in the carrier gun body 52 by perforating bullet keeper 62, and this perforating bullet keeper 62 comprises that outside perforating bullet keeps sleeve pipe (outer charge holder sleeve) 64 and inner perforating bullet to keep sleeve pipe 66.In this structure, exterior tube 64 supports the transmitting terminal of lined-cavity charge 56, and inner tube 66 supports the initiating terminal of lined-cavity charge 56.The exploding wire 70 (for example, detonating fuse) that is used for detonation of shaped charges 56 is arranged in the inner tube 66.In illustrated embodiment, the initiating terminal of lined-cavity charge 56 extends through the central longitudinal axis of rig 50, is connected via the hole on the top of the housing that is formed on lined-cavity charge 56 and lined-cavity charge 56 interior high explosives to allow exploding wire 70.
When rig 50 is assembled fully, the vertical and radially aligned of one of a plurality of grooves 54 in each lined-cavity charge 56 and the carrier gun body 52.In illustrated embodiment, lined-cavity charge 56 makes each lined-cavity charge 56 be arranged at self level or height, and is ignited respectively so that only light a lined-cavity charge at every turn with the spiral pattern setting.Yet, those skilled in the art should be realized that, in the case of without departing from the principles of the present invention, can use the interchangeable setting of lined-cavity charge, comprise cluster type design (cluster type design), wherein be positioned at same level height and ignited simultaneously more than one lined-cavity charge.As described below, each groove 54 of rig 50 has the nano composite material skin 72 of the intensity that increases carrier gun body 52, makes the rig 50 can operation in high pressure and high temperature pit shaft thus.
Referring now to Fig. 3, wherein show summary of the present invention and be expressed as 100 lined-cavity charge rig.Rig 100 comprises a plurality of lined-cavity charges 102, there is shown wherein three lined-cavity charges.Lined-cavity charge 102 is installed in the perforating bullet keeper 104 that is arranged in carrier gun body 106.In illustrated embodiment, perforating bullet keeper 104 can comprise one or more vertical section, each vertically section rotatably be supported in the carrier gun body 106 by pair of engage members 108, only this support member 108 is as seen in Fig. 2.Each support member 108 comprises rolling element or the bearing 110 that contacts with the inside of carrier gun body 106.In addition, can be at the support member 108 of carrier gun body 106 every ends and be attached between the device 114 of carrier gun body 106 every ends optional thrust bearing 112 is set.Device 114 can be the joint (tandem) that is used for two rifles are linked each other, be used to make the device of any other type of bull plug, firing head that gun barrel (gun string) stops or the carrier gun body 106 that is attachable to gun barrel.In this structure, perforating bullet 102 can rotate in carrier gun body 106.
In illustrated embodiment, use gravity to make carrier gun body 106 interior perforating bullets 102 rotate to the orientation of expectation.Especially, by making the center of gravity laterally offset of the rotary components 118 that comprises perforating bullet keeper 104, lined-cavity charge 102 and weight (weight) 120, assembly 118 is positioned at ad-hoc location under the rotation by gravity biased to rotate to center of gravity.
Referring now to Fig. 4, wherein show the cross section of a part that summary of the present invention is expressed as the carrier gun body of 150 rig.Carrier gun body 150 comprises a plurality of zones 152 that radially reduce, and radially reduces zone 152 and can show as other structure that has specific thin-walled portion such as the wall of above-mentioned scallop, groove or endless belt or carrier gun body 150.Each radially reduces the nano composite material skins 154 that zone 152 has the intensity that increases carrier gun body 150, makes the rig that comprises carrier gun body 150 can operation in high pressure and high temperature pit shaft thus.
The intensity of nano composite material skin 154 is greater than the intensity of the metal of the remainder that forms carrier gun body 150.For example, carrier gun body 150 can be made by the steel of routine, and nano composite material skin 154 is made by the nano structural material with nanofeature (the nano crystal iron alloy that for example, comprises nanocrystalline steel).As used herein, nano structural material will comprise the material with from 1 to 500 nanofeature, and more preferably comprise the material with from 1 to 100 nanofeature.
Nano composite material skin 154 can be made by the ferrous alloy with alloying component, and this alloying component is selected from the group of being made up of boron, carbon, chromium, iron, manganese, molybdenum, nickel, niobium, silicon, tungsten and vanadium.In an example, the percentage by weight of alloying component is between about 0% and 4% the boron, between about 0.1% and 8% the carbon, between about 0.5% and 21% the chromium, between about 55% and 95% the iron, between about 0% and 3% the manganese, between about 0.5% and 8% the molybdenum, between about 0% and 5% the nickel, between about 0% and 4% the niobium, between about 0% and 2% the silicon, between about 0% and 7% the tungsten and between about 0% and 4% the vanadium.
Can use the material of the self assembly phenomenon formation nano composite material skin 154 in the solid-state transformation (comprise single-phase supersaturated solid solution and be broken down into heterogeneous nanometer microstructure).Can use various technology such as comprising spinodal decomposition, eutectoid reaction, devitrification of glass to prepare the solid nano structure of self assembly.Replacedly, can form the material of nano composite material skin 154 by the mechanical alloying of using powdered-metal.Preferably, use devitrification of glass technology to form the material of nano composite material skin 154, in devitrification of glass technology, by heat treatment, crystallization is the material with heterogeneous nanocrystalline structure of expectation to the alloying component of iron-based system subsequently under the glassy metal attitude.
Can use various treatment technologies (comprising hot-spraying technique, welding procedure or other technology that is fit to) that nano composite material outer 154 is applied or is formed on the carrier gun body 150, perhaps nano composite material skin 154 can form with carrier gun body 150.For example, can use high-velocity oxy-fuel (HVOF) hot-spraying technique that nano composite material skin 154 is coated to carrier gun body 150, this high-velocity oxy-fuel (HVOF) hot-spraying technique utilizes oxygen and mixture such as one or more combustion gas of hydrogen, propane, propylene, kerosene etc. to be sprayed on the nanometer composite layer.Similarly, can use twin wire arc spray (TWAS) technology, in this twin wire arc spray technology, two electrical opposite live metal silks are put together, produce controlled arc with crosspoint at them, be compressed the jet atomization (atomize) of air or gas and be advanced to motlten metal on the carrier gun body 150 thereby form, to form nanometer composite layer thus.
Replacedly, can use various welding procedures that nano composite material outer 154 is applied or is formed on the carrier gun body 150.For example, plasma spray (PTAW) technology utilization plasma panel makes material powder (feedstock powder) fusing and form the full densification of nano composite material and the weld layer of metallurgical binding on carrier gun body 150.Similarly; continuous consumable silk electrode and protective gas that gas metal arc welding (GMAW) technology utilization is supplied with via welding gun; make electric arc between the surface of silk electrode and carrier gun body 150, transmit, and make the wire fusing to form nanometer composite layer.Similarly, the continuous consumable silk electrode that open arc welding (OAW) technology utilization is supplied with via welding gun, the electric arc that transmits between silk electrode and carrier gun body 150 makes the wire fusing simultaneously, thereby forms nanometer composite layer.
Carrier gun body 150 radially reduce use nano composite material skin 154 to improve the boring performance in the high temperature and high pressure pit shaft in the zone 152 by increasing carrier gun body 150 in the intensity that radially reduces regional 152 places.In addition, nano composite material skin 154 breaks or divides by the expansion, cracking, the destructive that make carrier gun body 150 and minimizes, thereby increases the survivability of carrier gun body 150 after the boring incident.
Referring now to Fig. 5, wherein show the cross section that summary of the present invention is expressed as the carrier gun body of 160 rig.Carrier gun body 160 comprises a plurality of zones 162 that radially reduce, and radially reduces zone 162 and can show as other structure that has specific thin-walled portion such as the wall of above-mentioned scallop, groove or endless belt or carrier gun body 160.Each radially reduce zone 162 and contiguous each radially reduce the nano composite material skin 164 that the zone in zone 162 has the intensity that increases carrier gun body 160, make the rig that comprises carrier gun body 160 can operation in high pressure and high temperature pit shaft thus.
Identical with above-mentioned nano composite material outer 154, the intensity of nano composite material skin 164 is greater than the intensity of the metal of the remainder that forms carrier gun body 160, and nano composite material skin 164 can be made by the nano structural material with nanofeature (for example, above-mentioned nano crystal iron alloy).Can use such as the above-mentioned various technologies that comprise hot spraying and welding procedure nano composite material outer 164 is applied or is formed on the carrier gun body 160, perhaps nano composite material skin 164 can form with carrier gun body 160.
Referring now to Fig. 6, wherein show the cross section of a part that summary of the present invention is expressed as the carrier gun body of 170 rig.Carrier gun body 170 comprises a plurality of zones 172 that radially reduce, and radially reduces zone 172 and can show as other structure that has specific thin-walled portion such as the wall of above-mentioned scallop, groove or endless belt or carrier gun body 170.The external surface of carrier gun body 170 has the nano composite material skin 174 of the intensity that increases carrier gun body 170, makes the rig that comprises carrier gun body 170 can operation in high pressure and high temperature pit shaft thus.
Identical with above-mentioned nano composite material skin 154,164, the intensity of nano composite material skin 174 is greater than the intensity of the metal of the remainder that forms carrier gun body 170, and nano composite material skin 174 can be made by the nano structural material with nanofeature (for example, above-mentioned nano crystal iron alloy).Can use such as the above-mentioned various technologies that comprise hot spraying and welding procedure nano composite material outer 174 is applied or is formed on the carrier gun body 170, perhaps nano composite material skin 174 can form with carrier gun body 170.
The use of the nano composite material skin 174 of carrier gun body 170 can improve the boring performance in the high temperature and high pressure pit shaft by the intensity that increases carrier gun body 170.In addition, nano composite material skin 174 breaks or divides by the expansion, cracking, the destructive that make carrier gun body 170 and minimizes, thereby increases the survivability of carrier gun body 170 after the boring incident.
Referring now to Fig. 7, wherein show the cross section of a part that summary of the present invention is expressed as the carrier gun body of 180 rig.Carrier gun body 180 comprises a plurality of zones 182 that radially reduce, and radially reduces zone 182 and can show as other structure that has specific thin-walled portion such as the wall of above-mentioned scallop, groove or endless belt or carrier gun body 180.The inner surface of carrier gun body 180 has the nanometer composite layer 184 of the intensity that increases carrier gun body 180, makes the rig that comprises carrier gun body 180 can operation in high pressure and high temperature pit shaft thus.
Identical with above-mentioned nano composite material skin 154,164,174, the intensity of nano composite material internal layer 184 is greater than the intensity of the metal of the remainder that forms carrier gun body 180, and nano composite material internal layer 184 can be made by the nano structural material with nanofeature (for example, above-mentioned nano crystal iron alloy).Can use such as the above-mentioned various technologies that comprise hot spraying and welding procedure nano composite material internal layer 184 is applied or is formed on the carrier gun body 180, perhaps nano composite material internal layer 184 can form with carrier gun body 180.
The use of the nano composite material internal layer 184 of carrier gun body 180 can improve the boring performance in the high temperature and high pressure pit shaft by the intensity that increases carrier gun body 180.In addition, nano composite material internal layer 184 breaks or divides by the expansion, cracking, the destructive that make carrier gun body 180 and minimizes, thereby increases the survivability of carrier gun body 180 after the boring incident.
Referring now to Fig. 8, wherein show the cross section of a part that summary of the present invention is expressed as the carrier gun body of 190 rig.Carrier gun body 190 comprises a plurality of zones 192 that radially reduce, and radially reduces zone 192 and can show as other structure that has specific thin-walled portion such as the wall of above-mentioned scallop, groove or endless belt or carrier gun body 190.Each radially reduces zone 192 and has nano composite material skin 194, and the inner surface of carrier gun body 190 has the nanometer composite layer 196 of the intensity that increases carrier gun body 190, makes the rig that comprises carrier gun body 190 can operation in high pressure and high temperature pit shaft thus.
Identical with above-mentioned nano composite material skin, the intensity of nanometer composite layer 194,196 is greater than the intensity of the metal of the remainder that forms carrier gun body 190, and nanometer composite layer 194,196 can be made by the nano structural material with nanofeature (for example, above-mentioned nano crystal iron alloy).Can use such as the above-mentioned various technologies that comprise hot spraying and welding procedure nanometer composite layer 194,196 is applied or is formed on the carrier gun body 190, perhaps nanometer composite layer 194,196 can form with carrier gun body 190.
The use of the nanometer composite layer 194,196 of carrier gun body 190 can improve the boring performance in the high temperature and high pressure pit shaft by the intensity that increases carrier gun body 190.In addition, nanometer composite layer 194,196 breaks or divides by the expansion, cracking, the destructive that make carrier gun body 190 and minimizes, thereby increases the viability of carrier gun body 190 after the boring incident.
Referring now to Fig. 9, wherein show the cross section of a part that summary of the present invention is expressed as the carrier gun body of 200 rig.Carrier gun body 200 is made by nano composite material 202, the intensity of this nano composite material 202 is greater than the intensity of the carrier gun body of the same size of being made by conventional material, makes the rig that comprises carrier gun body 200 can operation in high pressure and high temperature pit shaft thus.Identical with above-mentioned nanometer composite layer, nano composite material 202 can be made by the nano structural material with nanofeature (for example, above-mentioned nano crystal iron alloy).Except improving the boring performance, the carrier gun body of being made by nano composite material 202 200 also breaks by the expansion, division, the destructive that make carrier gun body 200 or cracking minimizes, thereby has increased the viability of carrier gun body 200 after the boring incident.
Although described the present invention with reference to exemplary embodiment, this description is not intended to the implication that is interpreted as limiting.In case consult this paper, various modification and the combination of exemplary embodiment of the present invention and other embodiment it will be apparent to those of skill in the art.Therefore, appended claims is intended to contain any this modification or embodiment.
Claims (26)
1. rig comprises:
Carrier gun body with a plurality of radially sections of reducing, the described radially section of reducing has the nano composite material skin;
The perforating bullet keeper is arranged in the described carrier gun body; And
By a plurality of lined-cavity charges that described perforating bullet keeper supports, each lined-cavity charge all has initiating terminal and ejecting end, and described ejecting end is set to the radially section of reducing of contiguous described carrier gun body.
2. rig as claimed in claim 1, the wherein said radially section of reducing also comprises groove.
3. rig as claimed in claim 1, the wherein said radially section of reducing also comprises endless belt.
4. rig as claimed in claim 1, at least a portion of the described radially section of reducing of the vicinity of wherein said carrier gun body also comprises the nano composite material skin.
5. rig as claimed in claim 1, wherein said carrier gun body also comprises the nano composite material skin.
6. rig as claimed in claim 1, wherein said carrier gun body also comprises the nano composite material internal layer.
7. rig as claimed in claim 1, the nano composite material skin of the wherein said radially section of reducing also comprises nano structured alloy.
8. rig as claimed in claim 1, the nano composite material skin of the wherein said radially section of reducing also comprises ferrous alloy.
9. rig as claimed in claim 8, wherein said ferrous alloy comes from glassy metal.
10. rig as claimed in claim 8, the alloying component of wherein said ferrous alloy is selected from the group of being made up of boron, carbon, chromium, iron, manganese, molybdenum, nickel, niobium, silicon, tungsten and vanadium.
11. rig as claimed in claim 1 wherein is coated on the described radially section of reducing by hot-spraying technique with described nano composite material skin.
12. rig as claimed in claim 1 wherein is coated on the described radially section of reducing by welding procedure with described nanometer composite layer.
13. rig as claimed in claim 1, wherein said nano composite material is outer integrated with described carrier gun body material.
14. a rig comprises:
Have the carrier gun body on a surface, described surface is made by nano composite material at least in part;
Be arranged on the perforating bullet keeper in the described carrier gun body; And
A plurality of lined-cavity charges by described perforating bullet keeper support.
15. rig as claimed in claim 14, wherein said carrier gun body has a plurality of radially sections of reducing, and wherein said nano composite material forms the external surface of the radially section of reducing of described carrier gun body.
16. rig as claimed in claim 15, wherein said nano composite material form the external surface of at least a portion of the described radially section of reducing of vicinity of described carrier gun body.
17. rig as claimed in claim 14, the surface of wherein said carrier gun body also comprises an external surface.
18. rig as claimed in claim 14, the surface of wherein said carrier gun body also comprises an inner surface.
19. rig as claimed in claim 14, wherein said carrier gun body is made by nano composite material fully.
20. rig as claimed in claim 14, wherein said nano composite material also comprises nano structured alloy.
21. rig as claimed in claim 14, wherein said nano composite material also comprises ferrous alloy.
22. rig as claimed in claim 21, wherein said ferrous alloy comes from glassy metal.
23. rig as claimed in claim 21, the alloying component of wherein said ferrous alloy is selected from the group of being made up of boron, carbon, chromium, iron, manganese, molybdenum, nickel, niobium, silicon, tungsten and vanadium.
24. rig as claimed in claim 14 wherein is coated on described carrier gun body by hot-spraying technique with described nano composite material.
25. rig as claimed in claim 14 wherein is coated on described carrier gun body by welding procedure with described nano composite material.
26. rig as claimed in claim 14, wherein said nano composite material and described carrier gun body material are integrated.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/473,569 US20100300750A1 (en) | 2009-05-28 | 2009-05-28 | Perforating Apparatus for Enhanced Performance in High Pressure Wellbores |
| US12/473,569 | 2009-05-28 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101899966A true CN101899966A (en) | 2010-12-01 |
Family
ID=42321175
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010101946205A Pending CN101899966A (en) | 2009-05-28 | 2010-05-28 | Be used for improving rig in the performance of high pressure pit shaft |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20100300750A1 (en) |
| EP (1) | EP2264279A2 (en) |
| JP (1) | JP2010281195A (en) |
| CN (1) | CN101899966A (en) |
| AR (1) | AR076933A1 (en) |
| MX (1) | MX2010005775A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105545261A (en) * | 2015-12-28 | 2016-05-04 | 北方斯伦贝谢油田技术（西安）有限公司 | Fracturing perforating bullet for oil and gas wells and shaped charge cover material thereof |
| CN109737844A (en) * | 2019-03-20 | 2019-05-10 | 福建省新华都工程有限责任公司 | A kind of mine blasthole explosive spacing installing mechanism |
Families Citing this family (34)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8919461B2 (en) * | 2010-07-21 | 2014-12-30 | Baker Hughes Incorporated | Well tool having a nanoparticle reinforced metallic coating |
| US9284824B2 (en) | 2011-04-21 | 2016-03-15 | Halliburton Energy Services, Inc. | Method and apparatus for expendable tubing-conveyed perforating gun |
| WO2013162490A1 (en) * | 2012-04-22 | 2013-10-31 | Halliburton Energy Services, Inc. | Method and apparatus for expendable tubing-conveyed perforating gun |
| US8794335B2 (en) | 2011-04-21 | 2014-08-05 | Halliburton Energy Services, Inc. | Method and apparatus for expendable tubing-conveyed perforating gun |
| WO2013130092A1 (en) * | 2012-03-02 | 2013-09-06 | Halliburton Energy Services, Inc. | Perforating apparatus and method having internal load path |
| WO2014084867A1 (en) | 2012-12-01 | 2014-06-05 | Halliburton Energy Services, Inc. | Protection of electronic devices used with perforating guns |
| US9238956B2 (en) | 2013-05-09 | 2016-01-19 | Halliburton Energy Services, Inc. | Perforating gun apparatus for generating perforations having variable penetration profiles |
| EP2946069A4 (en) * | 2013-05-09 | 2016-11-02 | Halliburton Energy Services Inc | Perforating gun apparatus for generating perforations having variable penetration profiles |
| US9702680B2 (en) | 2013-07-18 | 2017-07-11 | Dynaenergetics Gmbh & Co. Kg | Perforation gun components and system |
| US9790787B2 (en) | 2013-08-30 | 2017-10-17 | Halliburton Energy Services, Inc. | LWD resistivity imaging tool with adjustable sensor pads |
| WO2015102620A1 (en) * | 2013-12-31 | 2015-07-09 | Halliburton Energy Services, Inc. | Selective annealing process for perforation guns |
| BR112017000489A2 (en) | 2014-09-03 | 2017-11-07 | Halliburton Energy Services Inc | method of drilling a wellbore and method of forming at least one cannon in the lining of a wellbore |
| WO2016036358A1 (en) * | 2014-09-03 | 2016-03-10 | Halliburton Energy Services, Inc. | Perforating systems with insensitive high explosive |
| US9810048B2 (en) * | 2015-09-23 | 2017-11-07 | Benteler Steel/Tube Gmbh | Perforating gun |
| US9896915B2 (en) | 2016-04-25 | 2018-02-20 | Benteler Steel/Tube Gmbh | Outer tube for a perforating gun |
| US20180299036A1 (en) * | 2017-04-13 | 2018-10-18 | Chevron U.S.A. Inc. | High strength downhole tubulars and methods for forming and systems for using |
| CN111094889A (en) | 2017-09-14 | 2020-05-01 | 德力能欧洲有限公司 | Shaped charge liners, shaped charges for high temperature wellbore operations, and methods of perforating a wellbore therewith |
| US10669821B2 (en) * | 2018-04-25 | 2020-06-02 | G&H Diversified Manufacturing Lp | Charge tube assembly |
| US11808093B2 (en) | 2018-07-17 | 2023-11-07 | DynaEnergetics Europe GmbH | Oriented perforating system |
| US11339614B2 (en) | 2020-03-31 | 2022-05-24 | DynaEnergetics Europe GmbH | Alignment sub and orienting sub adapter |
| USD1034879S1 (en) | 2019-02-11 | 2024-07-09 | DynaEnergetics Europe GmbH | Gun body |
| USD1010758S1 (en) | 2019-02-11 | 2024-01-09 | DynaEnergetics Europe GmbH | Gun body |
| NO20211373A1 (en) | 2019-05-16 | 2021-11-15 | Schlumberger Technology Bv | Modular perforation tool |
| CZ2022302A3 (en) | 2019-12-10 | 2022-08-24 | DynaEnergetics Europe GmbH | Orientable piercing nozzle assembly |
| WO2021185749A1 (en) | 2020-03-16 | 2021-09-23 | DynaEnergetics Europe GmbH | Tandem seal adapter with integrated tracer material |
| US11988049B2 (en) | 2020-03-31 | 2024-05-21 | DynaEnergetics Europe GmbH | Alignment sub and perforating gun assembly with alignment sub |
| USD1016958S1 (en) | 2020-09-11 | 2024-03-05 | Schlumberger Technology Corporation | Shaped charge frame |
| US11293271B1 (en) * | 2020-10-28 | 2022-04-05 | Halliburton Energy Services, Inc. | Low-profile adjustable fastener for charge orientation of a downhole perforating tool |
| US12098623B2 (en) | 2020-11-13 | 2024-09-24 | Schlumberger Technology Corporation | Oriented-perforation tool |
| CA3206497A1 (en) | 2021-02-04 | 2022-08-11 | Christian EITSCHBERGER | Perforating gun assembly with performance optimized shaped charge load |
| US11499401B2 (en) | 2021-02-04 | 2022-11-15 | DynaEnergetics Europe GmbH | Perforating gun assembly with performance optimized shaped charge load |
| US11732556B2 (en) | 2021-03-03 | 2023-08-22 | DynaEnergetics Europe GmbH | Orienting perforation gun assembly |
| RU2759024C9 (en) * | 2021-04-19 | 2021-12-15 | Игорь Моисеевич Рафалович | Shaped-charge perforator |
| CN116163688B (en) * | 2023-04-26 | 2023-06-27 | 山东成林石油工程技术有限公司 | Device for exploiting oil gas by gas-water relay jet flow and application method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6767419B1 (en) * | 2000-11-09 | 2004-07-27 | Bechtel Bwxt Idaho, Llc | Methods of forming hardened surfaces |
| US6497285B2 (en) * | 2001-03-21 | 2002-12-24 | Halliburton Energy Services, Inc. | Low debris shaped charge perforating apparatus and method for use of same |
| US7360599B2 (en) * | 2004-11-18 | 2008-04-22 | Halliburton Energy Services, Inc. | Debris reduction perforating apparatus and method for use of same |
| US8704134B2 (en) * | 2005-02-11 | 2014-04-22 | The Nanosteel Company, Inc. | High hardness/high wear resistant iron based weld overlay materials |
-
2009
- 2009-05-28 US US12/473,569 patent/US20100300750A1/en not_active Abandoned
-
2010
- 2010-05-24 EP EP10163698A patent/EP2264279A2/en not_active Withdrawn
- 2010-05-26 MX MX2010005775A patent/MX2010005775A/en not_active Application Discontinuation
- 2010-05-27 AR ARP100101840A patent/AR076933A1/en unknown
- 2010-05-28 JP JP2010122469A patent/JP2010281195A/en not_active Withdrawn
- 2010-05-28 CN CN2010101946205A patent/CN101899966A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105545261A (en) * | 2015-12-28 | 2016-05-04 | 北方斯伦贝谢油田技术（西安）有限公司 | Fracturing perforating bullet for oil and gas wells and shaped charge cover material thereof |
| CN109737844A (en) * | 2019-03-20 | 2019-05-10 | 福建省新华都工程有限责任公司 | A kind of mine blasthole explosive spacing installing mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2010281195A (en) | 2010-12-16 |
| EP2264279A2 (en) | 2010-12-22 |
| MX2010005775A (en) | 2010-11-29 |
| US20100300750A1 (en) | 2010-12-02 |
| AR076933A1 (en) | 2011-07-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101899966A (en) | Be used for improving rig in the performance of high pressure pit shaft | |
| CN201620848U (en) | Vertical well orientation multi-pulse increase-benefit perforating device | |
| AU2009206508B2 (en) | System and method for enhanced wellbore perforations | |
| CN102839957B (en) | Pulse detonation fracturing device for ultra high-temperature high-pressure well | |
| CN2821154Y (en) | Composite hole punching device for module type medicine box holding medicine | |
| US7246548B2 (en) | Well perforating gun | |
| CN100552369C (en) | The method of beehive-shaped charge assembly and destruction target | |
| CN201574735U (en) | Inclined shaft azimuthal orientation multilevel pulse benefit increment perforating device | |
| CN103983153A (en) | Case circular discontinuous energy concentrating jet flow cracker | |
| WO2011079742A1 (en) | Controllable pulse gas energy fracturing machine | |
| US7819180B2 (en) | High-energy gas fracture apparatus for through-tubing operations | |
| CN110761750B (en) | Composite perforating gun | |
| CN201574736U (en) | Firing angle adjusting charge carrier for perforating gun | |
| CN104769213A (en) | Bi-directional shaped charges for perforating a wellbore | |
| CN111457800A (en) | Straight-eye barrel-shaped cutting hole arrangement structure and roadway straight-eye barrel-shaped cutting blasting method thereof | |
| CN113914843A (en) | Multi-detonation-point multi-stage detonation fracturing method for horizontal well of shale gas reservoir | |
| CN101004133B (en) | Sound wave shock and pulse combustion type pressing crack apparatus | |
| CN103590792A (en) | Gun perforation bullet | |
| CN110939424B (en) | Well-free underground coal gasification ignition method | |
| CN201045293Y (en) | High dense holes multilevel pulse sand carrying compound perforation device | |
| CN1332120C (en) | Throwing type fracturing equipment | |
| CN104832136A (en) | Low-confining-pressure perforator used for oil gas well | |
| CN204827395U (en) | Oil gas well is with low confined pressure perforator | |
| CN104929591A (en) | Inner orientation interception fixed-jet-angle multistage pulse enhanced-perforator | |
| CN101148982A (en) | Side direction detonation symmetrical bidirectional perforator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20101201 |