U.S. patent number 3,917,007 [Application Number 05/404,911] was granted by the patent office on 1975-11-04 for method of sinking holes in earth's surface.
Invention is credited to Mikhail Ivanovich Tsiferov.
United States Patent |
3,917,007 |
Tsiferov |
November 4, 1975 |
Method of sinking holes in earth's surface
Abstract
A rocket is placed with its front nozzle directed towards the
hole face with the distance between said nozzle and the face being
about four diameters of the nozzle exit section. Then the rocket is
released, started and the face of the hole is worked by the
gas-dynamic jet continuously discharged from the rocket nozzle. The
force driving the rocket towards the hole face is somewhat stronger
than the reaction force of the gas-dynamic jet and other forces
directed contrary to the rocket movement. The broken rock is
removed from the hole by the streams of waste gases passing out
through the gap between the rocket body and the hole walls. Thus,
the hole is sunk by breaking the face with the gas-dynamic jet of
the rocket being suspended relative to the hole walls and face.
Inventors: |
Tsiferov; Mikhail Ivanovich
(Moscow, SU) |
Family
ID: |
20553113 |
Appl.
No.: |
05/404,911 |
Filed: |
October 10, 1973 |
Foreign Application Priority Data
Current U.S.
Class: |
175/14; 175/67;
299/17 |
Current CPC
Class: |
E02F
3/9206 (20130101); E21B 7/14 (20130101) |
Current International
Class: |
E02F
3/92 (20060101); E21B 7/14 (20060101); E02F
3/88 (20060101); E21B 007/14 (); E21C 021/00 () |
Field of
Search: |
;175/11-17,67,2,3.5
;299/17 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Abbott; Frank L.
Assistant Examiner: Favreau; Richard E.
Attorney, Agent or Firm: Holman & Stern
Claims
I claim:
1. 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 that the 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.
2. The method according to claim 1 wherein, in case of a small
weight of the rocket and its fuel relative to the reaction force of
the jet pushing the rocket out of the hole, an additional
gas-dynamic jet is formed and dischared in a direction contrary to
the movement of the rocket, increasing the force which drives the
rocket towards the hole face, and enlarging the diameter of the
hole.
3. The method according to claim 1 wherein, in case of a large
weight of the rocket and its fuel relative to the reaction jet
acting on the face, an additional gas-dynamic jet is formed and
discharged in the direction of rocket movement thus creating an
additional force which assists in holding the rocket above the hole
face and increases the efficiency of face working.
4. The method according to claim 1 wherein, for raising up-holes, a
gas-dynamic jet is created and discharged in a direction contrary
to rocket movement to provide a force compensating for the weight
of the rocket.
5. The method according to claim 1 wherein, a gas-dynamic jet is
formed and discharged along the rocket movement at a certain angle
thereto.
Description
BACKGROUND OF THE INVENTION
The present invention relates to an improvement in the method of
sinking holes in the earth's 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. In addition, the present method can be
employed for making water drawdown holes to reduce the head of
subterranean waters or the inflow 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. for the delivery of materials required in fighting
underground fires, for lowering electric cables, water and air
conduits into underground workings, for delivering air and food and
raising the force in case of shaft failures and for building
underground gas and oil stores. In agriculture 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.
Known at the present time are a large number of various methods of
sinking holes in the earth's surface with the aid of a
rock-breaking element, for example, a bit brought into direct
contact with the rock to be broken. This method is realized,
depending on the hardness of the encountered rocks and the required
sinking speed, by means of drill rigs provided with bits of metal
or an extra-hard material, e.g. diamond.
The use of rotary bits limits the maximum speed of rock working;
thus, even with the bits characterized by a maximum hardness at 600
rpm, the speed of hole sinking is equal to 40 m/hr. The known
methods are capable of increasing the drilling speeds by 2 -3 times
as a maximum. This impairs the commercial value of drill rigs.
An increase in the speed of hole sinking, particularly in the case
of large-diameter holes, leads inevitably to a corresponding
increase in the power of the main and auxiliary equipment which, in
turn, increases the weight of this equipment.
Since almost all of the units of a drill rig are of metal, the
increase in power increases the metal requirement which raises
considerably the cost of drill rigs. It should also be borne in
mind that the large size and weight of drill rigs impair
considerably their transportability; finally, one of the
disadvantages of the known methods resides in a comparatively rapid
wear of the rock-breaking tool which is in positive contact with
the rock.
Thus, at present the employment of the above-described known method
restricts the possibility of a sharp increase in the output of
drilling equipment.
I have provided a radically new method of sinking holes in the
earth's surface by working the 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. This method involved additional bombardment
of the face with small explosive charges. The rock was broken with
a jet of gas discharged under a pressure of 500 -2500 atm. In the
case of vertical down-holes, this method ensures a sinking speed of
about 1 m/s which exceeds the hole sinking speeds attainable at the
present time by one order approximately.
However, this method can be successfully used only for sinking
holes with a depth up to a few hundred meters because in the case
of longer holes, the broken rock cannot sometimes be taken out
together with the stream of gases. Moreover, bombardment of the
face with explosives hinders the engineering realization of the
method.
It should also be taken in consideration that the above-described
method is not adapted for making up-holes by a rocket moving from
the rock towards the earth's surface and for driving horizontal and
inclined workings.
Lastly, the rockets with a relatively small weight, i.e. those
whose weight is smaller than the rocket thrust are difficult to use
at the above-mentioned pressures.
OBJECTS AND SUMMARY OF THE INVENTION
An object of the present invention resides in eliminating the
abovementioned disadvantages.
Another object of the present invention is to improve the
reliability and efficiency of the method of sinking holes in the
earth's surface by means of a gas-dynamic jet.
These and other objects are accomplished by providing a method of
sinking holes in the earth's surface by breaking the 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 wherein, according to the invention,
the rocket is held before starting in such a position that the
distance before its front nozzle and the surface of the face is not
smaller than the distance at which, during the rocket starting, the
sum of the reaction force of the gas-dynamic jet and the
counter-pressure arising between the nose of the rocket and the
hole face is counterbalanced by the forces driving the rocket
towards the hole face, with said forces being selected to exceed
the sum of the reaction force and the forces of friction against
the rocket body of the particles of rock and the stream of exhaust
gases flowing between the rocket and the hole walls, the amount of
gas in the gas-dynamic jet being selected so that the velocity of
the exhaust gases exceeds the velocity at which the particle of
broken rock of a maximum preset size and mass is in the state of
weightlessness.
It has been proved in practice that it is sufficient if the
distance from the front nozzle to the hole face is more than four
diameters of the nozzle exit section.
For the best conditions of gas and rock discharge, the gap between
the rocket body and the hole walls should be about half the maximum
diameter of the rocket.
If the weight of the rocket and its fuel is small relative to the
reaction force of the jet directed onto the face, it is practicable
than an additional gas-dynamic jet be formed and discharged in a
direction contrary to the movement of the rocket so as to increase
the force which drives the rocket against the hole face.
If the weight of the rocket and its fuel is large relative to the
reaction force of the jet acting on the hole face, it is
practicable that an additional gas-dynamic jet be formed, moving in
the direction of the rocket movement in order to create an
additional force assisting in holding the rocket above the hole
face.
For making workings directed from the center of the earth towards
its surface, it is necessary to provide a gas-dynamic jet directed
contrary to the movement of the rocket and creating a force
compensating for the weight of the rocket.
Now the invention will be described by way of example with
reference to the accompanying drawings in which:
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a diagrammatic view of the rocket for sinking holes in
the earth's 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; and
FIG. 5 is a section of the rocket shown in FIG. 4.
DETAILED DESCRIPTION OF THE INVENTION
Theoretically, the method according to the invention can be
realized with any solid-propellant rocket known at the present
time. However, 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
face-breaking element because it is the gas-dynamic jet discharged
from this nozzle which breaks the face of the hole.
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. Theoretically, the
value of 1 can be found on the basis of the following
considerations. At the moment of starting, the working element 5 of
the rocket A is acted upon by the force of the weight (P.sub.1) of
the rocket, by the force of weight (P.sub.2) of its fuel, the
reaction force (P.sub.3) of the gas-dynamic jet discharged from the
nozzle of the rocket and by the force (P.sub.4) of the
counterpressure arising between the nose of the rocket and the hole
face. Thus, it is necessary to satisfy the following condition:
P.sub.1 + P.sub.2 - P.sub.3 - P.sub.4 = 0 (1)
in the above equation, 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.
Hence, for satisfying equation (1), 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 gas-dynamic 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.sub.1 and P.sub.2. Theoretical calculations of 1 are possible,
though being extremely difficult.
However, in each specific instance, the value of 1 for the rockets
of the given class can be found experimentally by means of a device
illustrated in 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. As soon as 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. Now 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.
Thus, if the above requirement is satisfied, then immediately after
starting, 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. Let us
consider the process of forming the hole. While sinking a
down-hole, 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. Hence, it is necessary
that 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 gas- dynamic jet. The force
driving the rocket towards the hole face consists of the sum of
weights (P.sub.1 + P.sub.2) 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 movement of the rocket in the hole creates an additional force
tending to push the rocket out of the hole. This force is created
by friction against the rocket body of the rock particles and the
stream of waste gases of the gas-dynamic jet.
Therefore, 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.
To ensure normal functioning of the rocket in the hole, a gap must
be provided between the rocket and the hole walls, and a certain
velocity of the ascending stream.
It has been established that the most stable operation of the
rocket in the hole is ensured when the gap between the rocket body
and the hole wall is 0.3 the rocket diameter and over.
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
cross-section can be ensured when the ascending stream moves at a
speed of 80 -100 m/s. If one takes in account that the temperature
of the gas discharged from the nozzle is about 1000.degree.C 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.
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.sub.1) of the ascending stream from the following formula:
##EQU1## where
Q.sub.1 = volume of gas, m.sup.3 /s, at a mean stable temperature
of the stream;
Q.sub.2 = volumetric content of rock per cubic meter of gas;
F = cross-sectional area of the hole, m.sup..
The volume of gas can be calculated by the formula: ##EQU2##
where
Q.sub.0 = amount of gas generated per second at t = 0.degree.C;
t = temperature of gas in the hole mouth, degrees Centigrade.
The lift force of the stream (A) can be found from the formula:
A = .rho.V.sub.1.sup.2 (4)
where .rho. = density of the ascending stream of gases.
The density (.rho.) of the stream of gases can be determined as
follows: ##EQU3## where G = weight of gas.
To determine the speed of removal of the broken rock particles, it
is necessary to find the excess speed which is the difference
between the actual velocity of the stream and the critical velocity
for the particles of a certain weight, size (d) and shape. In this
case, 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: ##EQU4## where
V.sub.2 = velocity of gas stream at which the rock particle becomes
weightless;
C = correction factor for the shape of particles;
d = maximum diameter of the particle (m)
.gamma..sub.1 = volumetric weight of discharged rock, kg/m.sup.3
;
.gamma..sub.2 = volumetric weight of gas, kg/m.sup.3.
For example, for round particles of 50 mm diameter C = 3.5. When
the volumetric weight of the discharged rock is 2400 kg/m.sup.3 and
that of gas if 0.5 kg/m.sup.3, the critical velocity of particles
is 54.5 m/s.
The actual speed (V.sub.3) of the calculated particle in the hole
is:
V.sub.3 = V.sub.1 - V.sub.2 (7)
thus, the total velocity of the gas stream can be calculated with a
certain degree of approximation by the formula: ##EQU5##
When the amount of gas is 15 m.sup.3 at 0.degree.C and the
temperature of gas stream is 300.degree.C, the value of Q is 30.9
m.sup.3. The value of V.sub.1 = 80 m/s.
Hence, the actual speed of rock particles of a maximum size
discharged from the hole is:
v.sub.3 = V.sub.1 - V.sub.2 = 80 - 54.5 = 25.5 m/s.
As shown by experiments, 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.
It has been stated above that 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. In the
present case, it is necessary that 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.
Thus, in the process of hole sinking, the rocket A is acted upon by
the forces satisfying the following requirement:
P.sub.1 + P.sub.2 - P.sub.3 - P.sub.4 - P.sub.5 = 0 (9)
where
P.sub.1 = weight of the rocket;
P.sub.2 = weight of the fuel;
P.sub.3 = reaction force of the gas-dynamic jet;
P.sub.4 = force of the counterpressure arising between the nose
portion of the rocket and the hole face;
P.sub.5 = force of friction against the rocket body of the rock
particles and stream of waste gases.
If this requirement is satisfied, 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.
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.sub.3
becomes larger than the sum of P.sub.1 + P.sub.2 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.sub.1 + P.sub.2 becomes smaller than P.sub.3. In this case, the
rocket will also start backing out of the hole.
If the weight of the rocket and its fuel is considerably smaller
than the thrust of the rocket engine, it is necessary to provide an
additional force driving the rocket towards the face, i.e. to
ensure conditions under which the forces driving the rocket towards
the face are stronger than the sum of the reaction force of the
gas-dynamic jet and the force 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. For
this purppose, 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
(.SIGMA.P.sub.13) 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.
Thus, when a hole is sunk by means of a rocket whose own weight is
smaller than its thrust, the following condition must be satisfied:
P.sub.1 + P.sub.2 + .SIGMA.P.sub.13.sup.. cos .alpha. - P.sub.3 -
P.sub.4 = 0 (10)
where .SIGMA.P.sub.13 = reaction force created by the discharge of
gases through nozzles 13;
.alpha.= angle at which gases are discharged from the nozzles 13
relative to the fore-and-aft axis of the rocket.
While raising an up-hole, 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. However, 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.
Thus, when the rocket is used for raising an up-hole, the following
condition must be satisfied:
.SIGMA.P.sub.13 < .SIGMA.P (P.sub.1 + P.sub.2 + P.sub.3 +
P.sub.5) (11)
the method according to the invention can also be employed for
driving horizontal working. 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 5c 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:
.SIGMA.P.sub.13 cos .alpha. > .SIGMA. (P.sub.3 + P.sub.5)
(12)
here the weight of the rocket and its fuel is compensated for
mainly by the aerodynamic lift force.
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.
Moreover, the employment of the method according to the invention
reduces the weight of the drilling equipment also by dozens of
times.
* * * * *