US3917007A - Method of sinking holes in earth{3 s surface - Google Patents

Method of sinking holes in earth{3 s surface Download PDF

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Publication number
US3917007A
US3917007A US404911A US40491173A US3917007A US 3917007 A US3917007 A US 3917007A US 404911 A US404911 A US 404911A US 40491173 A US40491173 A US 40491173A US 3917007 A US3917007 A US 3917007A
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Prior art keywords
rocket
hole
face
gas
jet
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Expired - Lifetime
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US404911A
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English (en)
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Mikhail Ivanovich Tsiferov
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    • E—FIXED CONSTRUCTIONS
    • E02—HYDRAULIC ENGINEERING; FOUNDATIONS; SOIL SHIFTING
    • E02F—DREDGING; SOIL-SHIFTING
    • E02F3/00—Dredgers; Soil-shifting machines
    • E02F3/04—Dredgers; Soil-shifting machines mechanically-driven
    • E02F3/88—Dredgers; Soil-shifting machines mechanically-driven with arrangements acting by a sucking or forcing effect, e.g. suction dredgers
    • E02F3/90—Component parts, e.g. arrangement or adaptation of pumps
    • E02F3/92—Digging elements, e.g. suction heads
    • E02F3/9206—Digging devices using blowing effect only, like jets or propellers
    • 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
    • E21B7/14—Drilling by use of heat, e.g. flame drilling

Definitions

  • the present invention relates to an improvement in the method of sinking holes in the earths surface and can be successfully employed in geology, construction, agriculture and other fields in which a high-speed sinking of holes is required.
  • the method according to the invention will be used with greatest advantage for drilling holes such as mapping, structure, key, reconnaissance and prospecting holes made during geological survey, prospecting and exploration of useful minerals; operational holes for the excavation of useful minerals, prospect holes for studying the physical and mechanical properties of rocks and soils, hydrological holes for determining the quality and discharge of subterranean waters.
  • the present method can be employed for making water drawdown holes to reduce the head of subterranean waters or theinflow of water during shaft sinking, gully holes for the discharge of water from water-bearing horizons, ventilation holes, holes for the supply of air to fire faces during underground gasification of coal and for conducting fuel gas to the surface.
  • the method can also be used for making special-purpose holes, e.g.
  • this method can be employed for obtaining drinking and utility water and for land reclamation, while in construction said method will prove useful for drilling holes for bridge piles, industrial and civil buildings, blast shafts and holes.
  • Another object of the present invention is to improve the reliability and efficiency of the method of sinking holes in the earths surface by means of a gas-dynamic jet.
  • FIG. 1 is a diagrammatic view of the rocket for sinking holes in the earths surface
  • FIG. 2 shows a device for determining the distance from the nozzle exit section to the hole face
  • FIG. 3 shows the position. of the rocket in the hole during operation
  • FIG. 4 shows the position of the rocket as it starts driving a horizontal hole
  • FIG. 5 is a section of the rocket shown in FIG. 4.
  • the method according to the invention can be realized with any solid-propellant rocket known at the present time.
  • any solid-propellant rocket known at the present time.
  • the best results will be obtained by using a special rocket shown diagrammatically in FIG. 1.
  • the rocket A comprises a body 2 provided with a combustion chamber 3 wich accommodates fuel cells 4 referred to hereinafter in a number of cases as fuel for the sake of brevity.
  • the rocket has a working element 5 provided with a nozzle 6.
  • the nozzle 6 is a facebreaking element because it is the gas-dynamic jet discharged from this nozzle which breaks the face of the hole.
  • the rocket Before starting, the rocket should be positioned at a certain distance from a face surface 7, for example as shown in FIG. 1, and held by grips 8.
  • the nozzle 6 should be set at such a distance from the face surface 7 that the sum of the forces acting on the face during rocket starting would be equal to zero.
  • the value of 1 can be found on the basis of the following considerations.
  • the working element 5 of the rocket A is acted upon by the force of the weight (P of the rocket, by the force of weight (P of its fuel, the reaction force (P of the gasdynamic jet discharged from the nozzle of the rocket and by the force (P of the counterpressure arising between the nose of the rocket and the hole face.
  • the force of the counterpressure depends on the distance 1 while the other variables depend on the class of the rocket. It should be understood that rockets of a certain class have the same thrust and weight.
  • the distance 1 should be selected so that the nozzle 6 would be at such a distance from the face surface at which, during rocket starting, the sum of the reaction force of the gasdynamic jet and the force of counter-pressure arising between the nose of the rocket and the hole face would be counterbalanced by the forces driving the rocket towards the surface of the hole face, in this case by the forces P and P Theoretical calculations of l are possible, though being extremely difficult.
  • FIG. 2 This device comprises a solid unbreakable base 9 made, for example, of steel; said base mounts a vertical metal pipe 10 simulating the hole in the earth and for which purpose the end of said pipe has a cylindrical portion and a tapered portion.
  • the rocket is provided with a rigidly fastened bar 11 while the pipe 10 has a rack 12.
  • the rocket is placed at a certain distance from the base 9 and started.
  • the rocket engine attains the rated working conditions, (i.e. the conditions under which it burns the rated amount of fuel per second)
  • the rocket becomes stabilized in a certain position.
  • the position of the bar 11 with relation to the rack 12 makes it possible to find the distance from the rocket nozzle 6 to the base 9. While using other rockets of the same class, this distance can be taken for a reference value, i.e. for a distance at which the nozzle of the rocket A should be set from the face surface. Experiments have shown that this distance should be equal to at least four diameters of the exit section of the rocket face-breaking nozzle.
  • the rocket will be in a suspended state relative to the hole face.
  • the gas-dynamic jet discharged from the nozzle 6 and acting on the face will break the rock and form a hole.
  • the rocket While sinking a downhole, the rocket moves towards the face as shown in FIG. 3 under the effect of forces driving the rocket towards the hole face; at the same time, the reaction force of the gas-dynamic jet tends to push the rocket out of the hole.
  • the forces driving the rocket A towards the face surface should be at least equal to or, for the best effect, somewhat larger than, the reaction force of the gasdynamic jet.
  • the force driving the rocket towards the hole face consists of the sum of weights (P, P of the rocket and its fuel which must exceed the rocket thrust. Even in such cases when the weight of the rocket and fuel is considerably larger than its thrust, the counterpressure grows so largely with the reduction of the distance between the nose of the rocket 1 and the hole face, that physical contact between the rocket nozzle and the face is rendered practically impossible. It should be noted that when the forces driving the rocket towards the hole face are equal to the reaction force of the gas-dynamic jet, the rocket will move towards the center of the earth because breaking of the rock in the face increases the distance between the rocket nozzle and the face which, in turn, reduces the force of counterpressure in which case the rocket will tend to occupy a position in which the equation (1) is satisfied.
  • the forces-which drive the rocket towards the face in this case the weight of the rocket and its fuel, should be selected so that their sum would exceed the sum of the reaction force and the forces of friction against the rocket body of the ascending stream containing the particles of rock and the waste gases discharged through the gap between the rocket body and the hole walls.
  • a gap must be provided between the rocket and the hole walls, and a certain velocity of the ascending stream.
  • the preliminary calculations of the amount of gas in the gas-dynamic jet ensuring the required velocity of the ascending stream can be based on the nature of the ground and the maximum size of the particles formed during face working. It has been found experimentally that an efficient clearing of the face and rapid removal of the rock particles or stones up to 50 mm in crosssection can be ensured when the ascending stream moves at a speed of 80 -l00 m/s. If one takes in account that the temperature of the gas discharged from the nozzle is about l000C and that the speed of hole sinking (about 1 m/s) ensures intensive heat exchange between the gas and the particles of soil, the volume of gas diminishes sharply under these conditions which should be borne in mind while calculating the velocity of the ascending stream.
  • Each particular design of the rocket characterized by the chemical composition of its fuel, working pressure in its combustion chamber, the critical section of its nozzle and a number of other factors has the high and low limits of gas discharge per second.
  • V of the ascending stream Given the cross-sectional area of the hole, the amount of gas discharged per second and an approximate percentage of solids in the stream of waste gases, one can derive the required speed (V of the ascending stream from the following formula:
  • the lift force of the stream (A) can be found from the formula:
  • the density (p) of the stream of gases can be determined as follows:
  • the criticial velocity is the velocity at which the particles of rock withdrawn with the stream of gases become weightless.
  • the critical velocity of the rock particles can be derived from the following formula:
  • the total velocity of the gas stream can be calculated with a certain degree of approximation by the formula:
  • the method according to the invention at this velocity of the gas stream ensures a complete clearing of the hole from the broken rock at the rate of about 1 ton per sec.
  • the rocket is driven towards the face surface in the down holes by the forces pressing the rocket towards the face; in the case of the rocket shown in FIG. 1, these forces are constituted by the weight of the rocket and its fuel.
  • the sum of weights of the rocket and its fuel should be larger than the sum of the reaction force of the gas-dynamic jet acting on the face and the forces of friction against the rocket body of the rock particles and the stream of waste gases discharged through the gap between the rocket body and the hole walls.
  • the rocket A is acted upon by the forces satisfying the following requirement:
  • the rocket is suspended relative to the face and the hole walls so that the face is worked by the gas-dynamic jet discharged from the face-breaking nozzle.
  • the rocket As soon as the hole has been sunk to the preset depth, the rocket is withdrawn by increasing its thrust to such a limit when P;, becomes larger than the sum of P P which pushes the rocket from the hole. It is also possible to use a rocket with a ballast weight which can be removed after sinking the hole so that P, P becomes smaller than P In this case, the rocket will also start backing out of the hole.
  • the rocket shown in FIG. 3 will be effective.
  • This rocket consists of a body 2a with a combustion chamber 3a accommodating fuel cells 4a.
  • the rocket has a working element provided with a nozzle 6a which discharges a gas-dynamic jet acting on the face along the axis of rocket movement, and a row of nozzles 13.
  • the working element of the rocket also has several nozzles 6b which discharge gas-dynamic jets acting on the face of the hole at a certain angle to the direction of rocket movement which increases the diameter of the hole.
  • the gas-dynamic jet discharged from the nozzles 13 is directed against the movement of the rocket thus creating a reaction force (ZP which drives the rocket towards the face and adds to the weight of the rocket proper. Besides, these nozzles increase additionally the hole diameter, thus improving the conditions of its sinking.
  • a angle at which gases are discharged from the nozzles 13 relative to the fore-and-aft axis of the rocket.
  • the face-breaking nozzle of the rocket should be set at the same distance from the face as that used in sinking a down-hole.
  • the thrust in this case should be directed towards the hole face. This thrust should be larger than the weight of the rocket and its fuel plus the forces of friction against the rocket body of the waste gases and rock particles in the gap between the rocket body and the hole walls.
  • FIGS. 4 and 5 show the rocket in a starting position before driving a horizontal working.
  • This rocket consists of a body 2c, a working element 50 provided with a face-breaking nozzle 6c and a group of nozzles 13c. Besides, the body 2c is fitted with fins 14 which stabilize the rocket in a horizontal position. The rocket is held horizontally by the lift force created by the stream of gases acting on the fins. The rocket is started from a pipe 15. At the beginning of the hole sinking, the rocket is set at the same distance 1 as in any other method of working. This method is efficient for making short holes. In this case, the relation of forces while the rocket is in the hole should be as follows:
  • the use of the method according to the invention increases the hole sinking speed dozens of times as compared with the existing methods, and at the same time ensures a high quality of the hole walls.
  • a method of sinking holes in the earth's surface by working the hole face with a gas-dynamic jet continuously discharged from the nozzle of a rocket suspended relative to the hole walls and face and gradually moving together with the sinking face characterized by holding a rocket before starting in such a position that the distance between its front nozzle and the surface of the hole face is not smaller than the distance at which, during rocket starting, the sum of a reaction force of the gas-dynamic jet and a counter-pressure arrising between the nose of the rocket and the hole face is counter balanced by forces driving the rocket towards the hole face, selecting said forces to exceed the sum of the reaction force and forces of friction against the rocket body of the particles of rock and the stram waste gases flowing between the rocket and the hole walls, and selecting the amount of gas in the gas-dynamic jet so thatthe velocity of the waste gases would exceed the velocity at which the particle of broken rock of a maximum pre-set size and mass is in the state of weightlessness, wherein the gap between the rocket body and the hole walls is about half the maximum rocket diameter.

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  • Engineering & Computer Science (AREA)
  • Mining & Mineral Resources (AREA)
  • Mechanical Engineering (AREA)
  • Geology (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Environmental & Geological Engineering (AREA)
  • Fluid Mechanics (AREA)
  • General Life Sciences & Earth Sciences (AREA)
  • Geochemistry & Mineralogy (AREA)
  • Physics & Mathematics (AREA)
  • Civil Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structural Engineering (AREA)
  • Drilling And Exploitation, And Mining Machines And Methods (AREA)
  • Earth Drilling (AREA)
US404911A 1973-06-07 1973-10-10 Method of sinking holes in earth{3 s surface Expired - Lifetime US3917007A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU1920252A SU522759A1 (ru) 1973-06-07 1973-06-07 Способ образовани м.и.циферова выработок в земной поверхности

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US (1) US3917007A (enExample)
CA (1) CA1004663A (enExample)
DD (1) DD114846A1 (enExample)
FR (1) FR2232670B1 (enExample)
GB (1) GB1443343A (enExample)
IT (1) IT997412B (enExample)
SU (1) SU522759A1 (enExample)
ZA (1) ZA738005B (enExample)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4301875A (en) * 1977-03-04 1981-11-24 Messerschmitt-Bolkow-Blohm Gmbh Method for making holes and producing gas in coal seams
FR2600373A1 (fr) * 1986-06-23 1987-12-24 Briggs Technology Inc Procede et appareil pour creuser le sol et analogue, utilisant un gaz envoye a une vitesse supersonique
US4923019A (en) * 1989-02-28 1990-05-08 Arctic Systems Limited Thermochemical penetrator for ice and frozen soils
US5022470A (en) * 1989-06-28 1991-06-11 Ocean Systems Research, Inc. Autonomous rapid thermal ice penetrating method and system
RU2161245C1 (ru) * 1999-04-21 2000-12-27 Плугин Александр Илларионович Технология образования скважин в геологических структурах
US6231270B1 (en) * 1999-05-27 2001-05-15 Frank Cacossa Apparatus and method of installing piles
RU2168599C1 (ru) * 1999-10-15 2001-06-10 Плугин Александр Илларионович Устройство для проходки скважин
WO2001079614A1 (en) * 2000-04-13 2001-10-25 Kayoshi Tsujimoto Equipments for excavating the underground
RU2178505C1 (ru) * 2000-09-18 2002-01-20 Азизов Азиз Мустафаевич Рабочий орган автономного бурильного аппарата
RU2178503C1 (ru) * 2000-09-18 2002-01-20 Азизов Азиз Мустафаевич Устройство для проходки горизонтальных и наклонных выработок
RU2178504C1 (ru) * 2000-09-18 2002-01-20 Азизов Азиз Мустафаевич Автономный аппарат для проходки скважин и выработок
US20030164253A1 (en) * 1995-12-08 2003-09-04 Robert Trueman Fluid drilling system
RU2222681C1 (ru) * 2002-08-05 2004-01-27 Плугин Александр Илларионович Устройство для проходки выработок в геологических структурах
RU2240420C2 (ru) * 2002-10-08 2004-11-20 Плугин Александр Илларионович Технический комплекс для образования скважин и выработок в осадочных горных породах
US20050034901A1 (en) * 2001-11-14 2005-02-17 Meyer Timothy Gregory Hamilton Fluid drilling head
US20050067166A1 (en) * 1997-06-06 2005-03-31 University Of Queensland, Commonwealth Erectable arm assembly for use in boreholes
US7195082B2 (en) 2002-10-18 2007-03-27 Scott Christopher Adam Drill head steering
RU2344264C2 (ru) * 2007-03-26 2009-01-20 Зао "Скафега" Технология образования выработок в осадочных горных породах
RU2409734C2 (ru) * 2008-12-04 2011-01-20 Миннибаев Эдуард Файзиевич Устройство для проходки скважин с отдаленным забоем
RU2455449C1 (ru) * 2011-02-15 2012-07-10 Общество с ограниченной ответственностью "Реактивное бурение" Способ разработки месторождения полезного ископаемого
RU2457311C1 (ru) * 2011-02-15 2012-07-27 Общество с ограниченной ответственностью "Реактивное бурение" Способ образования скважин и выработок в горных породах
US9169695B1 (en) * 2015-04-22 2015-10-27 OEP Associates, Trustee for Oil exploration probe CRT Trust Oil exploration probe
US10883810B2 (en) 2019-04-24 2021-01-05 Saudi Arabian Oil Company Subterranean well torpedo system
US10955264B2 (en) 2018-01-24 2021-03-23 Saudi Arabian Oil Company Fiber optic line for monitoring of well operations
US10995574B2 (en) 2019-04-24 2021-05-04 Saudi Arabian Oil Company Subterranean well thrust-propelled torpedo deployment system and method
US11365958B2 (en) 2019-04-24 2022-06-21 Saudi Arabian Oil Company Subterranean well torpedo distributed acoustic sensing system and method

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2307118A1 (fr) * 1975-04-11 1976-11-05 Ts Geofizichesky Trest Dispositif pour le percement du sol
RU2593504C1 (ru) * 2015-03-04 2016-08-10 Николай Евгеньевич Староверов Окопокопатель

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US2935303A (en) * 1957-01-15 1960-05-03 Union Carbide Corp Thermal rock piercing control apparatus
US3093197A (en) * 1958-12-09 1963-06-11 Union Carbide Corp Method and apparatus for thermally working minerals and mineral-like materials
US3207238A (en) * 1962-08-06 1965-09-21 Bucyrus Erie Co Thermal piercing control
US3216320A (en) * 1962-07-09 1965-11-09 Harvey Aluminum Inc Apparatus for excavating by means of explosives
US3482640A (en) * 1968-04-29 1969-12-09 Browning Eng Corp Blast hole drilling method
US3620313A (en) * 1969-10-27 1971-11-16 Pulsepower Systems Pulsed high-pressure liquid propellant combustion-powered liquid jet drills

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Publication number Priority date Publication date Assignee Title
US2882016A (en) * 1953-05-19 1959-04-14 Union Carbide Corp Thermal mineral piercing employing a free suspension blowpipe

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935303A (en) * 1957-01-15 1960-05-03 Union Carbide Corp Thermal rock piercing control apparatus
US3093197A (en) * 1958-12-09 1963-06-11 Union Carbide Corp Method and apparatus for thermally working minerals and mineral-like materials
US3216320A (en) * 1962-07-09 1965-11-09 Harvey Aluminum Inc Apparatus for excavating by means of explosives
US3207238A (en) * 1962-08-06 1965-09-21 Bucyrus Erie Co Thermal piercing control
US3482640A (en) * 1968-04-29 1969-12-09 Browning Eng Corp Blast hole drilling method
US3620313A (en) * 1969-10-27 1971-11-16 Pulsepower Systems Pulsed high-pressure liquid propellant combustion-powered liquid jet drills

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4301875A (en) * 1977-03-04 1981-11-24 Messerschmitt-Bolkow-Blohm Gmbh Method for making holes and producing gas in coal seams
FR2600373A1 (fr) * 1986-06-23 1987-12-24 Briggs Technology Inc Procede et appareil pour creuser le sol et analogue, utilisant un gaz envoye a une vitesse supersonique
EP0251660A1 (en) * 1986-06-23 1988-01-07 Air Technologies Inc. Method and apparatus for soil excavation and the like
US4923019A (en) * 1989-02-28 1990-05-08 Arctic Systems Limited Thermochemical penetrator for ice and frozen soils
US5022470A (en) * 1989-06-28 1991-06-11 Ocean Systems Research, Inc. Autonomous rapid thermal ice penetrating method and system
US20030164253A1 (en) * 1995-12-08 2003-09-04 Robert Trueman Fluid drilling system
US6866106B2 (en) * 1995-12-08 2005-03-15 University Of Queensland Fluid drilling system with flexible drill string and retro jets
US20050067166A1 (en) * 1997-06-06 2005-03-31 University Of Queensland, Commonwealth Erectable arm assembly for use in boreholes
US7370710B2 (en) 1997-06-06 2008-05-13 University Of Queensland Erectable arm assembly for use in boreholes
RU2161245C1 (ru) * 1999-04-21 2000-12-27 Плугин Александр Илларионович Технология образования скважин в геологических структурах
US6231270B1 (en) * 1999-05-27 2001-05-15 Frank Cacossa Apparatus and method of installing piles
RU2168599C1 (ru) * 1999-10-15 2001-06-10 Плугин Александр Илларионович Устройство для проходки скважин
WO2001079614A1 (en) * 2000-04-13 2001-10-25 Kayoshi Tsujimoto Equipments for excavating the underground
RU2178505C1 (ru) * 2000-09-18 2002-01-20 Азизов Азиз Мустафаевич Рабочий орган автономного бурильного аппарата
RU2178504C1 (ru) * 2000-09-18 2002-01-20 Азизов Азиз Мустафаевич Автономный аппарат для проходки скважин и выработок
RU2178503C1 (ru) * 2000-09-18 2002-01-20 Азизов Азиз Мустафаевич Устройство для проходки горизонтальных и наклонных выработок
US20050034901A1 (en) * 2001-11-14 2005-02-17 Meyer Timothy Gregory Hamilton Fluid drilling head
US7083011B2 (en) * 2001-11-14 2006-08-01 Cmte Development Limited Fluid drilling head
RU2222681C1 (ru) * 2002-08-05 2004-01-27 Плугин Александр Илларионович Устройство для проходки выработок в геологических структурах
RU2240420C2 (ru) * 2002-10-08 2004-11-20 Плугин Александр Илларионович Технический комплекс для образования скважин и выработок в осадочных горных породах
US7195082B2 (en) 2002-10-18 2007-03-27 Scott Christopher Adam Drill head steering
RU2344264C2 (ru) * 2007-03-26 2009-01-20 Зао "Скафега" Технология образования выработок в осадочных горных породах
RU2409734C2 (ru) * 2008-12-04 2011-01-20 Миннибаев Эдуард Файзиевич Устройство для проходки скважин с отдаленным забоем
RU2455449C1 (ru) * 2011-02-15 2012-07-10 Общество с ограниченной ответственностью "Реактивное бурение" Способ разработки месторождения полезного ископаемого
RU2457311C1 (ru) * 2011-02-15 2012-07-27 Общество с ограниченной ответственностью "Реактивное бурение" Способ образования скважин и выработок в горных породах
US9169695B1 (en) * 2015-04-22 2015-10-27 OEP Associates, Trustee for Oil exploration probe CRT Trust Oil exploration probe
US10955264B2 (en) 2018-01-24 2021-03-23 Saudi Arabian Oil Company Fiber optic line for monitoring of well operations
US10883810B2 (en) 2019-04-24 2021-01-05 Saudi Arabian Oil Company Subterranean well torpedo system
US10995574B2 (en) 2019-04-24 2021-05-04 Saudi Arabian Oil Company Subterranean well thrust-propelled torpedo deployment system and method
US11365958B2 (en) 2019-04-24 2022-06-21 Saudi Arabian Oil Company Subterranean well torpedo distributed acoustic sensing system and method

Also Published As

Publication number Publication date
SU522759A1 (ru) 1977-03-05
CA1004663A (en) 1977-02-01
IT997412B (it) 1975-12-30
FR2232670B1 (enExample) 1976-12-17
ZA738005B (en) 1974-09-25
GB1443343A (en) 1976-07-21
AU6166373A (en) 1975-04-24
DD114846A1 (enExample) 1975-08-20
DE2350422A1 (de) 1975-01-02
FR2232670A1 (enExample) 1975-01-03
DE2350422B2 (de) 1976-02-26

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