U.S. patent application number 09/814498 was filed with the patent office on 2003-03-13 for pressurized gas turbine engine.
Invention is credited to Johnson, Neldon P..
Application Number | 20030049119 09/814498 |
Document ID | / |
Family ID | 25215226 |
Filed Date | 2003-03-13 |
United States Patent
Application |
20030049119 |
Kind Code |
A1 |
Johnson, Neldon P. |
March 13, 2003 |
PRESSURIZED GAS TURBINE ENGINE
Abstract
A pressurized gas turbine engine is disclosed which utilizes a
new turbine design. Pressurized gas is supplied by nozzle gas ways
in the turbine to gas nozzles affixed to the perimeter of the
turbine. The gas nozzles may be recessed in the turbine perimeter
or extend from the turbine perimeter. The gas nozzles may be
equipped with gas exit cones to enhance the efficiency of the
nozzles. The axis of the nozzles have an oblique angle with the
direction of rotation of the turbine. Pressurized gas is supplied
to the nozzle gas ways through one or more shaft gas ways in the
turbine shaft, or is supplied through engine gas ports in the front
wall of the turbine engine to gas supply zones which are
hydraulically separated by seal rings on the front face of the
turbine, each gas supply zone being hydraulically connected to one
or more nozzle gas ways.
Inventors: |
Johnson, Neldon P.;
(American Fork, UT) |
Correspondence
Address: |
J. David Nelson
NELSON, SNUFER, DAHLE & POULSEN, P.C.
10885 South State Street
Sandy
UT
84070
US
|
Family ID: |
25215226 |
Appl. No.: |
09/814498 |
Filed: |
March 21, 2001 |
Current U.S.
Class: |
415/82 |
Current CPC
Class: |
F02K 7/005 20130101;
H02N 3/00 20130101; F01D 1/32 20130101; F05D 2210/13 20130101 |
Class at
Publication: |
415/82 |
International
Class: |
F03B 001/00 |
Claims
What is claimed is:
1. Pressurized gas turbine having a plurality of gas nozzles, one
or more nozzle gas ways, and a turbine shaft with one or more
internal shaft gas ways, each gas nozzle being affixed at the
perimeter of the turbine in a respective nozzle position, the axis
of each of the gas nozzles forming an oblique angle with the
direction of rotation of the perimeter of the turbine at the
respective nozzle position, and each gas nozzle being hydraulically
connected to one or more shaft gas ways in the turbine shaft by one
or more nozzle gas ways.
2. Pressurized gas turbine as recited in claim 1 wherein the
perimeter of the turbine has a plurality of nozzle recesses and
each nozzle is installed in a respective nozzle recess.
3. Pressurized gas turbine as recited in claim 1 wherein each of
the nozzles further comprises a gas exit cone.
4. Pressurized gas turbine as recited in claim 3 wherein each of
the gas nozzles is affixed to the perimeter of the turbine and
hydraulically connected to one or more nozzle gas ways by a nozzle
support tube.
5. Pressurized gas turbine as recited in claim 1 wherein each of
the gas nozzles further comprises a gas exit cone and wherein each
of the gas exit cones is recessed in the perimeter of the
turbine.
6. Pressurized gas turbine as recited in claim 1, wherein the shaft
gas ways and nozzle gas ways provide for the transmission of
pressurized liquid to the gas nozzles, and the gas nozzles provide
for flashing the pressurized liquid to gas at the gas nozzle.
7. Pressurized gas turbine as recited in claim 6, wherein the
pressurized liquid is pressurized and superheated water, and the
pressurized and superheated water is flashed to steam at the gas
nozzles..
8. Pressurized gas turbine engine comprising: a) Pressurized gas
turbine having a plurality of gas nozzles and one or more nozzle
gas ways, and a turbine shaft with one or more internal shaft gas
ways, each gas nozzle being affixed at the perimeter of the turbine
in a respective nozzle position, the axis of each of the gas
nozzles forming an oblique angle with the direction of rotation of
the perimeter of the turbine at the respective nozzle position, and
each gas nozzle being hydraulically connected to one or more shaft
gas ways in the turbine shaft by one or more nozzle gas ways; and
b) turbine engine body enclosing the turbine in a turbine chamber,
the turbine engine body having an expansion chamber in the turbine
chamber.
9. Pressurized gas turbine engine as recited in claim 8 wherein
each of the nozzles further comprises a gas exit cone.
10. Pressurized gas turbine engine as recited in claim 9 wherein
each of the gas nozzles is affixed to the perimeter of the turbine
and hydraulically connected to one or more nozzle gas ways by a
nozzle support tube.
11. Pressurized gas turbine engine as recited in claim 6 wherein
each of the gas nozzles further comprises a gas exit cone which is
recessed in the perimeter of the turbine.
12. Pressurized gas turbine engine as recited in claim 1 further
comprising a plurality of pressurized gas receiving chambers
recessed in the turbine seat peripheral surface.
13. Pressurized gas turbine engine as recited in claim 12 wherein
the angular spacing of the pressurized gas receiving chambers is
the same as the angular spacing of the gas nozzles.
14. Pressurized gas turbine engine as recited in claim 12 further
comprising a plurality of back flow receiving chambers recessed in
the perimeter of the turbine.
15. Pressurized gas turbine engine as recited in claim 14 wherein
each back flow receiving chamber is located between two successive
gas exit cones.
16. Pressurized gas turbine engine as recited in claim 15 further
comprising a plurality of gas dissipation chambers.
17. Pressurized gas turbine engine as recited in claim 16 wherein
the number of pressure dissipation chambers is equal to the number
of gas receiving chambers and wherein each pressure dissipation
chamber is recessed in the turbine perimeter at an angular position
which provides for the pressure dissipation chamber to
hydraulically connect with a gas receiving chamber before that gas
receiving chamber hydraulically disconnects from a back flow
receiving chamber a the turbine rotates.
18. Pressurized gas turbine engine as recited in claim 8 further
comprising one or more turbine shaft beatings affixed in each shaft
way around the turbine shaft.
19. Pressurized gas turbine engine as recited in claim 8 wherein
the turbine shaft extends through shaft ways in opposing side walls
of the turbine engine body.
20. Pressurized gas turbine engine as recited in claim 8 further
comprising a heat exchanger for capturing heat released from the
pressurized gas and heat carried by the spent gas.
21. Pressurized gas turbine engine as recited in claim 8 wherein
each turbine shaft way has a gas seal affixed in the respective
shaft way around the turbine shaft.
22. Pressurized gas turbine engine as recited in claim 21 wherein
the gas seal is a pressurized oil seal.
23. Pressurized gas turbine engine as recited in claim 18 wherein
the turbine shaft bearings have a pressurized oil seal.
24. Pressurized gas turbine engine as recited in claim 8 wherein
the annular turbine seat peripheral surface has a close tolerance
with the gas exits of the nozzles, thereby inducing a ground effect
for gas exiting the nozzles.
25. Pressurized gas turbine engine as recited in claim 24 wherein
the annular peripheral surface has a nozzle groove which is
proximal to the perimeter of the turbine and to the gas exits of
the nozzles to enhance the ground effect.
26. Pressurized gas turbine engine as recited in claim 8 further
comprising one or more pressurized gas sources and connecting means
for connecting each of the shaft gas ways to one or more of the
respective pressurized gas sources.
27. Pressurized gas turbine engine as recited in claim 20 further
comprising recycling means for recycling the recaptured thermal
energy to the pressurized gas source.
28. Pressurized gas turbine engine as recited in claim 8 further
comprising spent gas control means for controlling the discharge of
spent gas from the expansion chamber.
29. Pressurized gas turbine engine as recited in claim 8 further
comprising a plurality of controllable pressurized gas sources,
each of the nozzle gas ways being hydraulically connected to one or
more of the respective pressurized gas sources, thereby providing
for a variation in the number of nozzles which are pressurized and
providing for a variation in the pressure of the gas delivered to
each nozzle.
30. Pressurized gas turbine engine as recited in claim 8 wherein
the gas nozzles are distributed on the perimeter of the turbine
such as to provide for a balance of forces imposed on the shaft by
the nozzles.
31. Pressurized gas turbine engine as recited in claim 8 further
comprising condensation collecting means for collecting
condensation in the expansion chamber.
32. Pressurized gas turbine engine as recited in claim 8 further
comprising preheating means for pre-heating the liquid used for
generating the gas by pumping the liquid around the expansion
chamber in cooling tubes.
33. Pressurized gas turbine engine as recited in claim 8 further
comprising exhaust heat exchange means for improving the efficiency
of the gas turbine by pumping a heat exchange liquid in exhaust
heat exchangers around the exhaust of the steam generators.
34. Pressurized gas turbine engine as recited in claim 8 further
comprising balancing means for automatically balancing the
turbine.
35. Pressurized gas turbine engine as recited in claim 8 further
comprising speed determining means for determining the speed of
rotation of the turbine.
36. Pressurized gas turbine engine as recited in claim 8 further
comprising speed control means for controlling the speed of
rotation of the turbine.
37. Pressurized gas turbine engine as recited in claim 8 further
comprising reversing means for reversing rotation of the
turbine.
38. Pressurized gas turbine engine as recited in claim 18 further
comprising gas leakage control means for reducing the amount of
pressurized gas escaping through the turbine shaft bearings.
39. Pressurized gas turbine engine as recited in claim 23 further
comprising means for pumping cool oil through the oil seals.
40. Pressurized gas turbine engine as recited in claim 31 further
comprising means for separating the oil from the liquid.
41. Pressurized gas turbine engine as recited in claim 8 wherein
the perimeter of the turbine has a plurality of nozzle recesses and
each nozzle is installed in a respective nozzle recess.
42. Pressurized gas turbine engine as recited in claim 8 wherein
the turbine seat peripheral surface has transverse serrations to
enhance the ground effect.
43. Pressurized gas turbine engine as recited in claim 8 further
comprising a spent gas evacuator which is affixed to the turbine,
and wherein the turbine engine body has a spent gas evacuation
channel.
44. Pressurized gas turbine engine as recited in claim 43 wherein
the spent gas evacuator occupies the turbine expansion chamber.
45. Pressurized gas turbine engine as recited in claim 44 wherein
the turbine seat peripheral surface is serrated and the serrations
extend into the expansion chamber and are proximal to the perimeter
of the spent gas evacuator.
46. Pressurized gas turbine engine as recited in claim 8, wherein
the shaft gas ways and nozzle gas ways of the turbine provide for
the transmission of pressurized liquid to the gas nozzles, and the
gas nozzles provide for flashing the pressurized liquid to gas at
the gas nozzle.
47. Pressurized gas turbine engine as recited in claim 46, wherein
the pressurized liquid is pressurized and superheated water, and
the pressurized and superheated water is flashed to steam at the
gas nozzles.
48. Pressurized gas turbine having a plurality of gas nozzles, one
or more nozzle gas ways, one or more turbine gas intakes, and a
turbine shaft, each gas nozzle being affixed at the perimeter of
the turbine in a respective nozzle position, the axis of each of
the gas nozzles forming an oblique angle with the direction of
rotation of the perimeter of the turbine at the respective nozzle
position, each nozzle gas way being hydraulically connected to one
or more gas nozzles, and each turbine gas intake being
hydraulically connected to at least one nozzle by a nozzle gas
way.
49. Pressurized gas turbine as recited in claim 48 wherein the
perimeter of the turbine has a plurality of nozzle recesses and
each nozzle is installed in a respective nozzle recess.
50. Pressurized gas turbine as recited in claim 48 wherein the
turbine has two or more groups of coordinated nozzles and wherein
each group of coordinated nozzles is hydraulically connected to a
respective turbine gas intake.
51. Pressurized gas turbine as recited in claim 48 wherein the
turbine has a front face and a rear face, and has a turbine seal
ring affixed to the front face of the turbine for sealing against
the front wall of a turbine engine, and the turbine shaft is
connected to the rear of the turbine with the axis of the turbine
shaft being alined with the axis of the turbine.
52. Pressurized gas turbine as recited in claim 48, wherein the
turbine gas intakes and nozzle gas ways provide for the
transmission of pressurized liquid to the gas nozzles, and the gas
nozzles provide for flashing the pressurized liquid to gas at the
gas nozzle.
53. Pressurized gas turbine as recited in claim 52, wherein the
pressurized liquid is pressurized and superheated water, and the
pressurized and superheated water is flashed to steam at the gas
nozzles.
54. Pressurized gas turbine engine comprising: a) a turbine having
a plurality of gas nozzles, one or more nozzle gas ways, one or
more turbine gas intakes, and a turbine shaft, each gas nozzle
being affixed at the perimeter of the turbine in a respective
nozzle position, the axis of each of the gas nozzles forming an
oblique angle with the direction of rotation of the perimeter of
the turbine at the respective nozzle position, each nozzle gas way
being hydraulically connected to one or more gas nozzles, and each
turbine gas intake being hydraulically connected to at least one
nozzle by a nozzle gas way; and b) a turbine engine body enclosing
the turbine in a turbine chamber, the turbine engine body having a
front wall and a rear wall, the front wall having one or more
engine gas ports, and the rear wall having a shaftway passing the
turbine shaft.
55. Pressurized gas turbine engine as recited in claim 54 wherein
each of the nozzles further comprises a gas exit cone.
56. Pressurized gas turbine engine as recited in claim 55 wherein
each of the gas nozzles is affixed to the perimeter of the turbine
and hydraulically connected to one or more nozzle gas ways by a
nozzle support tube.
57. Pressurized gas turbine engine as recited in claim 54 wherein
each of the gas nozzles further comprises a gas exit cone which is
recessed in the perimeter of the turbine.
58. Pressurized gas turbine engine as recited in claim 57 further
comprising a plurality of pressurized gas receiving chambers
recessed in the turbine seat peripheral surface.
59. Pressurized gas turbine engine as recited in claim 58 wherein
the angular spacing of the pressurized gas receiving chambers is
the same as the angular spacing of the gas nozzles.
60. Pressurized gas turbine engine as recited in claim 59 further
comprising a plurality of back flow receiving chambers recessed in
the turbine perimeter.
61. Pressurized gas turbine engine as recited in claim 60 wherein
each back flow receiving chamber is located between two successive
gas exit cones.
62. Pressurized gas turbine engine as recited in claim 61 further
comprising a plurality of gas dissipation chambers.
63. Pressurized gas turbine engine as recited in claim 62 wherein
the number of pressure dissipation chambers is equal to the number
of gas receiving chambers and wherein each pressure dissipation
chamber is recessed in the turbine perimeter at an angular position
which provides for the pressure dissipation chamber to
hydraulically connect with a gas receiving chamber before that gas
receiving channel hydraulically disconnects from a back flow
receiving chamber as the turbine rotates.
64. Pressurized gas turbine engine as recited in claim 54 wherein
the turbine has two or more coordinated groups of nozzles and
wherein each group of nozzles is hydraulically connected to a
respective turbine gas intake.
65. Pressurized gas turbine engine as recited in claim 54 wherein
the turbine has a front face and a rear face, and has a turbine
seal ring affixed to the front face of the turbine for sealing
against the front wall of a turbine engine, and the turbine shaft
is connected to the rear of the turbine with the axis of the
turbine shaft being alined with the axis of the turbine.
66. Pressurized gas turbine engine as recited in claim 54 wherein
the turbine has a front face and a rear face, and the turbine
engine body has a turbine seal ring affixed to the inside surface
of the front wall of the turbine engine body for sealing against
the front face of the turbine, and the turbine shaft is connected
to the rear of the turbine with the axis of the turbine shaft being
alined with the axis of the turbine.
67. Pressurized gas turbine engine as recited in claim 54 wherein
the nozzles are affixed to the turbine in nozzle recesses in the
perimeter of the turbine.
68. Pressurized gas turbine engine as recited in claim 54 further
comprising one or more turbine shaft bearings affixed in each shaft
way around the turbine shaft.
69. Pressurized gas turbine engine as recited in claim 54 further
comprising a heat exchanger for capturing heat released from the
pressurized gas and heat carried by the spent gas.
70. Pressurized gas turbine engine as recited in claim 54 wherein
the turbine shaft way has a gas seal affixed in the shaft way
around the turbine shaft.
71. Pressurized gas turbine engine as recited in claim 70 wherein
the gas seal is a pressurized oil seal.
72. Pressurized gas turbine engine as recited in claim 68 wherein
the turbine shaft bearings have a pressurized oil seal.
73. Pressurized gas turbine engine as recited in claim 54 wherein
the turbine chamber has an annular turbine seat peripheral surface
having a close tolerance with the gas exits of the nozzles, thereby
inducing a ground effect for gas exiting the nozzles.
74. Pressurized gas turbine engine as recited in claim 73 wherein
the annular peripheral surface has a nozzle groove which is
proximal to the perimeter of the turbine and to the gas exits of
the nozzles to enhance the ground effect.
75. Pressurized gas turbine engine as recited in claim 73 wherein
the annular peripheral surface has transverse serrations to enhance
the ground effect.
76. Pressurized gas turbine engine as recited in claim 54 further
comprising a spent gas evacuator and wherein the turbine engine
body has a spent gas evacuation channel and spent gas port.
77. Pressurized gas turbine engine as recited in claim 54 further
comprising one or more pressurized gas sources and connecting means
for connecting each of the engine gas ports to one or more of the
respective pressurized gas sources.
78. Pressurized gas turbine engine as recited in claim 69 further
comprising recycling means for recycling the recaptured thermal
energy to the pressurized gas sources.
79. Pressurized gas turbine engine as recited in claim 54 further
comprising spent gas control means for controlling the discharge of
spent gas from the expansion chamber.
80. Pressurized gas turbine engine as recited in claim 54 wherein
the turbine has two or more gas seal rings of differing diameters
affixed to the front face of the turbine sealing between the front
face of the turbine and the front wall of the turbine engine and
creating two or more gas supply zones between the front face of the
turbine and the front wall of the turbine engine, and wherein the
front wall of the turbine engine has one or more gas supply ports,
each gas supply port being hydraulically connected to a gas supply
zone and each gas supply port being hydraulically connectable to
one or more pressurized gas sources, and wherein the front face of
the turbine has two or more turbine gas ports, one or more of the
respective turbine gas ports being hydraulically connected to each
gas supply zone and each respective turbine gas port being
hydraulically connected to selected nozzle gas ways.
81. Pressurized gas turbine engine as recited in claim 54 wherein
two or more gas seal rings of differing diameters are affixed to
the inside surface of the front wall of the turbine body, sealing
between the front face of the turbine and the front wall of the
turbine engine and creating two or more gas supply zones between
the front face of the turbine and the front wall of the turbine
engine, and wherein the front wall of the turbine engine has one or
more gas supply ports, each gas supply port being hydraulically
connected to a gas supply zone and each gas supply port being
hydraulically connectable to one or more pressurized gas sources,
and wherein the front face of the turbine has two or more turbine
gas ports, one or more of the respective turbine gas ports being
hydraulically connected to each gas supply zone and each respective
turbine gas port being hydraulically connected to selected nozzle
gas ways.
82. Pressurized gas turbine engine as recited in claim 80 further
comprising a plurality of controllable pressurized gas sources,
each of the gas supply ports being hydraulically connected to one
or more of the respective pressurized gas sources, thereby
providing for a variation in the number of nozzles which are
pressurized and providing for a variation in the pressure of the
gas delivered to each nozzle.
83. Pressurized gas turbine engine as recited in claim 81 further
comprising a plurality of controllable pressurized gas sources,
each of the gas supply ports being hydraulically connected to one
or more of the respective pressurized gas sources, thereby
providing for a variation in the number of nozzles which are
pressurized and providing for a variation in the pressure of the
gas delivered to each nozzle.
84. Pressurized gas turbine engine as recited in claim 54 wherein
the gas nozzles are distributed on the perimeter of the turbine
such as to eliminate unbalanced forces imposed on the shaft by the
nozzles.
85. Pressurized gas turbine engine as recited in claim 54 further
comprising condensation collecting means for collecting
condensation in the expansion chamber.
86. Pressurized gas turbine engine as recited in claim 54 further
comprising preheating means for pre-heating the liquid used for
generating the gas by pumping the liquid around the expansion
chamber in cooling tubes.
87. Pressurized gas turbine engine as recited in claim 54 further
comprising exhaust heat exchange means for improving the efficiency
of the gas turbine by pumping a heat exchange liquid in exhaust
heat exchangers around the exhaust of the steam generators.
88. Pressurized gas turbine engine as recited in claim 54 further
comprising balancing means for automatically balancing the
turbine.
89. Pressurized gas turbine engine as recited in claim 54 further
comprising speed determining means for determining the speed of
rotation of the turbine.
90. Pressurized gas turbine engine as recited in claim 54 further
comprising speed control means for controlling the speed of
rotation of the turbine.
91. Pressurized gas turbine engine as recited in claim 54 further
comprising reversing means for reversing rotation of the
turbine.
92. Pressurized gas turbine engine as recited in claim 54 further
comprising gas leakage control means for reducing the amount of
pressurized gas escaping through the turbine shaft bearings.
93. Pressurized gas turbine engine as recited in claim 71 further
comprising means for pumping cool oil through the oil seals.
94. Pressurized gas turbine engine as recited in claim 85 further
comprising means for separating the oil from the liquid.
95. Pressurized gas turbine engine as recited in claim 54 wherein
the turbine seat peripheral surface is serrated to enhance the
ground effect.
96. Pressurized gas turbine engine as recited in claim 54 further
comprising a spent gas evacuator which is affixed to the turbine,
and wherein the turbine engine body has a spent gas evacuation
channel.
97. Pressurized gas turbine engine as recited in claim 96 wherein
the spent gas evacuator occupies the turbine expansion chamber.
98. Pressurized gas turbine engine as recited in claim 97 wherein
the turbine seat peripheral surface is serrated and the serrations
extend into the expansion chamber and are proximal to the perimeter
of the spent gas evacuator.
99. Pressurized gas turbine engine as recited in claim 54, wherein
the turbine gas intakes and nozzle gas ways of the turbine provide
for the transmission of pressurized liquid to the gas nozzles, and
the gas nozzles provide for flashing the pressurized liquid to gas
at the gas nozzle.
100. Pressurized gas turbine engine as recited in claim 99, wherein
the pressurized liquid is pressurized and superheated water, and
the pressurized and superheated water is flashed to steam at the
gas nozzles.
Description
FIELD OF THE INVENTION
[0001] This invention is in the field of turbine engines and in
particular in the field of pressurized gas driven turbine
engines.
BACKGROUND OF THE INVENTION
[0002] The conventional design for the turbines used in turbine
engines incorporates small fins on the turbine. In order for the
turbine engine to be efficient, there must be extremely close
tolerances are required between the expansion chamber and the
turbine fins. Also, the expansion chamber and the turbine,
including the fins, must be able to withstand high temperatures.
These restraints on conventional turbines makes them very expensive
to manufacture. This has greatly limited the use of turbine engines
in many applications.
[0003] Essentially all automobiles, trucks, buses, boats, ships,
trains and smaller aircraft are powered by internal combustion
engines. These engines are either spark plug ignited gasoline
engines or compression heat ignited diesel engines. The efficiency
of these engines, in the conversion of chemical energy to
mechanical energy, is only in the rage of 20 to 25 percent. The
remaining 75 to 80 percent is lost as heat in the exhaust or in the
liquid cooling system through a radiator.
[0004] By comparison, the conversion of chemical energy to
mechanical energy in an efficient turbine engine is approximately
45 percent. Despite the substantially higher efficiency of a
turbine engine, turbine engines have not found wide application,
primarily due to initial cost.
[0005] Many attempts have been made to devise an apparatus to
reduce the large amount of heat which is wasted by internal
combustion engines. The device disclosed in U.S. Pat. No. 4,406,127
to Dunn utilizes steam generated by injecting water onto an exhaust
manifold to generate steam for powering a separate steam cylinder.
Similarly, the device disclosed in U.S. Pat. No. 4,433,548 to
Hallstrom utilizes steam generated by injecting water onto an
exhaust manifold to provide supplemental energy to each of the
cylinders.
[0006] An exhaust gas steam turbine for providing supplemental
power to an automobile is disclosed in U.S. Pat. No. 4,590,766 to
Striebich. For this drive unit, waste heat in the exhaust gases is
utilized to produce steam for powering a supplemental turbine. A
similar drive unit is disclosed in another U.S. Patent to
Striebich, U.S. Pat. No. 4,785,631 and incorporates a turbine
rotating element with spiral blading.
[0007] U.S. Pat. No. 4,996,845 to Kim discloses a device for
utilizing waste heat from an internal combustion engine to generate
steam and drive a turbine which is used for a generation of power
for auxiliary use in the automobile and for heating and cooling of
the passenger compartment.
[0008] U.S. Pat. No. 5,000,003 to Wicks discloses an apparatus
which utilizes waste heat from an internal combustion engine to
power a turbine. The inventor claims that this device has the
ability to increase the overall efficiency of the engine from 25
percent to approximately 40 percent.
[0009] A hybrid internal combustion/turbine engine is disclosed in
U.S. Pat. No. 5,176,000 to Dauksis. For this device, an internal
combustion engine is utilized to generate heat for the production
of steam which is used to power a turbine. The turbine is then
utilized to drive an electric generator to charge batteries which
are used as a complimentary or alternate source of propulsion for a
ground vehicle.
[0010] The apparent lack of commercial success for any of the
foregoing inventions is probably attributable primarily to cost.
The additional cost cannot be amortized, over the lifetime of the
vehicle by the fuel cost savings. The result of the foregoing is
that, as consumers, we have elected to live with the low efficiency
and environmental problems associated with internal combustion
engines. However, the extent of the effort made to attempt to deal
with the efficiency and environmental problems, as manifest by the
foregoing prior art, demonstrates the extent of the need for a high
efficiency engine for these applications.
[0011] The high cost of turbine engines is primarily the
consequence of the close tolerance required for the construction of
the turbine and the turbine body and the very high cost of
materials required for heat tolerance and durability required for
the traditional turbines. Particularly, the turbine fins and the
turbine seat in the turbine body must be machined to very close
tolerance of highly durable material. Otherwise, high efficiency
will not be achieved and wear and loss of efficiency will be
excessive.
[0012] The device disclosed in U.S. Pat. No. 4,883,404 to Sherman
provides for the passage of fluids through a turbine for use in
cooling the turbine.
[0013] The present invention utilizes steam or other pressurized
gas which is directed from the center of the turbine to nozzles at
the perimeter of the turbine. The nozzles have a gas discharge
which is oblique to the direction of rotation of the turbine.
[0014] The present invention may also be utilized with a geothermal
well, with the heated water being passed directly to the nozzles
where the water is flashed to steam as the water is passed through
the nozzles. Conventional geothermal generator facilities require
the flashing of hot water extracted from the geothermal well to
steam, and the steam is then passed to the turbine. This results in
a substantial loss of energy from the water in converting it to
steam. .The direct flashing of the hot water in the nozzles of the
present invention increases the efficiency substantially. This
advantage of the present invention can be used for other
applications as well, to increase efficiency and decrease
complexity.
[0015] An objective of the present invention is to provide a
turbine for a high efficiency engine which is economical enough for
automobile and other small engine applications.
[0016] A further objective of the present invention is to provide a
high efficiency turbine engine which is economical enough for
automobile and other small engine applications.
[0017] A further objective of the present invention is to provide a
high efficiency turbine engine for which the need for close
tolerance machining and the need for high cost parts and materials
are greatly reduced.
[0018] A further objective of the present invention is to provide a
turbine engine which can utilize fuel types other than gasoline or
diesel.
[0019] A further objective of the present invention is to provide a
turbine engine which does not require the burning of fossil fuel at
high pressure, thereby lessening the amount of oxide type air
pollutants.
[0020] A further objective of the present invention is to provide a
turbine engine that can be used with electric motor driven or
partially electric motor driven vehicles which utilize battery
storage of energy.
[0021] A further objective of the present invention is to provide a
turbine engine that provides for the direct flashing of heated
water to steam gas nozzles which power the turbine.
SUMMARY OF THE INVENTION
[0022] Preferred embodiments of the turbine engine of the present
invention comprise a turbine, a turbine shaft, a turbine body and
turbine shaft bearings. For these embodiments the turbine has at
least two gas nozzles which are hydraulically connected by nozzle
gas ways to internal shaft gas ways in the turbine shaft. For these
embodiments, the turbine shaft is hollow or tubular with one or
more internal shaft gas ways.
[0023] The turbine is contained within the turbine chamber of the
turbine body. The turbine seat is dimensioned to be proximal to the
perimeter of the turbine, thereby inducing a ground effect for gas
exiting the nozzles. The close tolerance between the gas exits and
the turbine seat peripheral surface is the only aspect of the
turbine body that requires accurate machining. Unlike a
conventional turbine, the front face of the turbine does not need
to closely fit the front wall of the turbine chamber. The turbine
nozzles, the turbine seat peripheral surface, the shaft gas ways
and the nozzle gas ways are the only components of the turbine
engine that experience very high temperatures.
[0024] For preferred embodiments, to provide for inertial balance
of the turbine, if there is only one gas shaft way, the internal
gas shaft way is circular and annular centered in the turbine
shaft, and the gas nozzles are equally spaced at nozzle locations
around the perimeter of the turbine. The nozzle angle between the
axis of the gas exit nozzles and the direction of rotation of the
perimeter of the turbine at the nozzle locations is also
uniform.
[0025] Certain preferred embodiments utilize multiple shaft gas
ways with each shaft gas way linked to one or more opposing pairs
or equally spaced groups of coordinated gas nozzles, thereby
providing for balance of the torque applied to turbine. Each shaft
gas way may be connected to an independently controlled steam flash
generator or other pressurized gas source, providing for
independent activation, deactivation and gas feed for each pair of
gas nozzles connected to the shaft gas way. This provides for
increasing and decreasing the power supplied to the turbine while
maintaining the pressure and the rate of gas flow at each gas
nozzle within a desired range.
[0026] The nozzle angle is oblique to the direction of rotation of
the perimeter of the turbine. Lesser nozzle angles increases the
ground effect but decreases the efficiency of the direct momentum
transfer of the exiting gas to the turbine, while greater nozzle
angles increase the direct momentum transfer while decreasing the
ground effect.
[0027] Pressurized gas is routed from a gas source through a shaft
gas connector to the turbine shaft gas ways. The gas passes through
the turbine shaft gas ways to the shaft gas distributor which
directs the gas from each of the turbine shaft gas ways to the
respective connected nozzles through the nozzle gas ways.
[0028] For certain preferred embodiments, as the pressurized gas is
discharged from the gas exit nozzles in a direction opposite the
desired direction of rotation of the turbine, it is also discharged
against the turbine seat annular peripheral surface. This produces
a back force that creates the ground effect, thereby increasing the
efficiency of the engine. Other embodiments do not utilize a ground
effect.
[0029] Some preferred embodiments incorporate a gas exit cone on
each nozzle to enhance the efficiency of the turbine engine. The
gas exit cones can be recessed in the perimeter of the turbine or
affixed to the perimeter of the turbine by nozzle support
tubes.
[0030] For embodiments of the present invention using steam to
power the turbine, steam generators have steam chambers with
controlled outputs. These outputs are controlled by a control
valve, which are monitored and controlled by a steam control
computer. For preferred embodiments the steam generators will be
flash steam generators. The flash chambers for flash steam
generators will be quite small in relation to the heat source,
thereby providing for a quick recovery. A pressure sensor is used
by the steam control computer to monitor the steam pressure in the
flash chamber. The control computer allows the pressure in the
flash chamber to reach a desired pressure and maintains the
pressure at that level. When the need for more steam is determined
by the control computer, the control valve is opened for that flash
chamber. If more steam is required, more control valves are opened,
bringing more flash chambers on line. As the steam pressure in the
flash chamber is depleted, the control computer determines that
more water is required and increases the water flow. Other
embodiments may incorporate a combination of flash generators and
other types of steam generators. This can provide for a fixed
amount of steam at a constant rate while leaving the flash
generators for quick response to special power demands for the
turbine. Other embodiments may utilize only a fixed steam system.
For these embodiments, the rotation speed or the amount of power
that is delivered to the turbine is still controlled by a series of
valves which are controlled by the control computer. This type of
steam generator may be more readily adapted to an engine used to
generate electric power for battery storage for use with an
electric motor driven device.
[0031] The control computer continually monitors and controls the
operating parameters of the turbine engine through use of sensors,
feed back controls, and output devices. Turbine speed, required
torque, gas or steam pressure, turbine balance and direction of
rotation of the turbine are some of the parameters that are
monitored and controlled. The control computer also controls water
levels, water temperature, and water flow for cooling in a steam
system and air flow around the expansion chamber for pressurized
gas. By controlling water flow, the control computer can maximize
the efficiency of the engine.
[0032] For other preferred embodiments of the pressurized gas
turbine engine, pressurized gas may be supplied through an engine
gas port in the front wall of the turbine engine. A preferred
embodiment of the turbine engine with the front wall of the turbine
engine removed. A turbine seal ring is affixed to the front face of
the turbine and provides a gas seal between the front face of the
turbine and the front wall of the turbine engine, thereby creating
a gas supply zone between the front face of the turbine and the
front wall of the turbine engine which is bounded by the gas seal.
This provides for pressurized gas to be directed from the engine
gas port to the turbine gas port. For some embodiments, the turbine
seal ring is not centered on the axis of the turbine. This provides
for the more uniform distribution of seal oil for all points of
contact between the turbine seal and the front wall of the turbine
engine. The seal oil enhances the ability of the turbine seal to
minimize pressurized gas leakage between the turbine seal and the
front wall of the turbine engine. The seal oil is typically
injected into the contact zone between the turbine seal and the
turbine engine front wall through a seal oil injector port in the
front wall of the turbine engine.
[0033] For some embodiments, the nozzle gas ways are machined,
formed or cast in the turbine and sealed by the turbine front face
plate. The nozzles are installed in a nozzle recess in the turbine
perimeter. The nozzle recesses provide for the tip of each of the
nozzles to be inside the turbine perimeter, thereby providing for
streamlining the turbine perimeter and allowing for a closer
tolerance between the turbine perimeter and the turbine seat
peripheral surface.
[0034] The turbine engine may have a turbine seat peripheral
surface with transverse serrations which increase the ground effect
experienced by the turbine as pressurized gas is discharged through
the nozzles. A spent gas evacuator may be attached to the turbine
or the turbine may have an evacuator spindle extending from the
rear face with the spent gas evacuator anchored to the evacuator
spindle. The transverse serrations typically will extend also to
the gas expansion area of the turbine seat which is proximal to the
perimeter of the spent gas evacuator. For these embodiments, the
rear face of the spent gas evacuator is proximal to the turbine
engine rear wall. The expansion chamber is occupied by the spent
gas evacuator and the spent gas is directed to a spent gas
evacuation channel for discharge through a spent gas port.
[0035] A nozzle or one or more opposing pairs or equally spaced
groups of coordinated nozzles may be connected to separate
pressurized gas sources through the use of multiple turbine gas
seals and turbine gas ports which direct the pressurized gas
received through respective engine gas ports in the front wall of
the turbine engine and respective gas supply zones between the
front face of the turbine and the front wall of the turbine engine,
to respective nozzle gas ways and thus to the respective nozzle or
pairs or groups of coordinated nozzles. Another embodiment which
provides for two separate gas sources to be utilized with pairs or
groups of coordinated nozzles utilizes a central internal shaft gas
way to transmit gas from one pressurized gas source through
interconnected nozzle gas ways to a first group of coordinated
nozzles, and utilizes the annular space between the shaft gas way
and the inside surface of the shaft tube of the turbine shaft as a
second shaft gas way to transmit gas from a second pressurized gas
source through other interconnected nozzle gas ways to a second
group of coordinated nozzles.
[0036] The present invention can also be used with simplified, high
efficiency systems by providing for the direct flashing of hot
water to steam in the nozzles. This has use for a number of
applications such a geothermal wells. This avoids the high energy
losses which occur as hot water is flashed to steam and the steam
is used to power the turbine.
BRIEF DESCRIPTION OF THE DRAWINGS
[0037] FIG. 1 is a longitudinal schematic of an embodiment of a
turbine engine of the present invention, including a horizontal
cross-section of an embodiment of a turbine engine body, and
including a connected steam generator system.
[0038] FIG. 2 is a rear cross section view showing the rear face of
the turbine, the gas nozzles, and the nozzle gas ways of an
embodiment of the present invention.
[0039] FIG. 3 is a rear view cross-section detail of a shaft gas
distributor of an embodiment of the present invention.
[0040] FIG. 4 is a detail of a nozzle gas way and gas nozzle
arrangement of an embodiment of the present invention.
[0041] FIG. 5 is a detail of a turbine seat peripheral surface
nozzle groove.
[0042] FIG. 6 is a cross-section of a steam generator of the
present invention.
[0043] FIG. 7 is a side perspective view of an embodiment of a
turbine engine of the present invention.
[0044] FIG. 8 is a front perspective view of an embodiment of a
turbine engine of the present invention with the front wall of the
turbine engine removed.
[0045] FIG. 9 is a front perspective view of an embodiment of a
turbine seal ring of the present invention.
[0046] FIG. 10 is a front perspective view of an embodiment of a
turbine engine of the present invention with the front wall of the
turbine engine and the turbine front face removed, showing an
embodiment of a turbine of the present invention and showing an
embodiment of the turbine seat peripheral surface with transverse
serrations.
[0047] FIG. 11 is a front perspective view of an embodiment of a
turbine front face of the present invention.
[0048] FIG. 12 is a front perspective view of an embodiment of a
turbine of the present invention with the turbine front face
removed.
[0049] FIG. 13 is a rear perspective view of an embodiment of a
turbine of the present invention with an integral evacuator
spindle.
[0050] FIG. 14 is a rear perspective view of an embodiment of a
turbine engine of the present invention with the evacuator cover
plate removed, showing a spent gas evacuator attached to the
evacuator spindle, evacuation channel and turbine seat peripheral
surface transverse serrations.
[0051] FIG. 15 is a rear perspective view of an embodiment of a
turbine engine of the present invention.
[0052] FIG. 16 is a rear perspective view of an embodiment of a
evacuator cover plate of the present invention.
[0053] FIG. 17 is a front perspective view of an embodiment of a
turbine engine of the present invention showing gas seal rings and
gas supply zones, providing for keying independent pressurized gas
sources to specific nozzles or coordinated groups of nozzles.
[0054] FIG. 18 is a perspective detail of an embodiment of a
turbine shaft of the present invention with two internal shaft gas
way, providing for utilization of two pressurized gas sources.
[0055] FIG. 19 is a front view perspective detail of an embodiment
of a turbine of the present invention for use with a turbine shaft
with two internal shaft gas way, providing for utilization of two
pressurized gas sources.
[0056] FIG. 20 is a front view of an embodiment of a turbine engine
of the present invention with the front wall removed, the turbine
having gas nozzles with gas exit cones affixed to the perimeter of
the turbine by nozzle support tubes.
[0057] FIG. 21 is a longitudinal cross section of a pressurized gas
nozzle, gas exit cone and gas plume of a gas nozzle of the present
invention.
[0058] FIG. 22 is a front view of an embodiment of the turbine
engine of the present invention with the front wall removed, the
turbine having gas nozzles with gas exit cones affixed to the
perimeter of the turbine by nozzle support tubes, and the turbine
seat peripheral surface having transverse serrations.
[0059] FIG. 23 is a front view of an embodiment of the turbine
engine of the present invention with the front wall removed, the
turbine having gas nozzles with gas exit cones, back flow receiving
chambers, and depletion chambers recessed in the perimeter of the
turbine, and the turbine seat peripheral surface having recessed
gas receiving chambers.
[0060] FIG. 24 is a cross-section detail of an embodiment of a gas
nozzle of the present invention with a gas exit cone.
DETAILED DESCRIPTION
[0061] Referring first to FIG. 1, some preferred embodiments of the
pressurized gas turbine engine 74 of the present invention are
comprised of a turbine 1, a turbine shaft 2, a turbine body 3 and
turbine shaft bearings 4. Referring also to FIG. 2, for these
embodiments the turbine has at least two gas nozzles 5 which are
hydraulically connected by nozzle gas ways 6 to internal shaft gas
ways 8 in the turbine shaft. A shaft gas distributor 7 is used for
these preferred embodiments to connect the nozzle gas ways to the
shaft gas ways. The turbine shaft is hollow or tubular with one or
more internal shaft gas ways. The turbine axis 116 is alined with
the turbine shaft axis 117.
[0062] The turbine is contained within the turbine chamber 9 of the
turbine body. The front wall 10 of the turbine chamber has a
turbine seat 63 which is dimensioned to conform roughly to the
front face 11 of the turbine. The turbine seat peripheral surface
12 of the turbine seat is dimensioned to be proximal to the
perimeter 13 of the turbine and thereby has a close tolerance 14
with the gas exits 15 of the nozzles, thereby inducing a ground
effect for gas 16 exiting the nozzles. The close tolerance between
the gas exits and the turbine seat peripheral surface is the only
aspect of the turbine body that requires accurate machining. Unlike
a conventional turbine, the front face of the turbine does not need
to closely fit the front wall of the turbine chamber. The turbine
nozzles, the turbine seat peripheral surface, the shaft gas ways
and the nozzle gas ways are the only components of the turbine
engine that experience very high temperatures.
[0063] The gas nozzles are typically of a uniform design and are
inexpensive to manufacture. Certain embodiments use standard
nozzles which are shelf items. The turbine itself can be made of
very inexpensive metals. Referring also to FIG. 2, the turbine seat
63 is merely a cylindrically shaped cavity 64 machined or formed
into the front wall of the turbine chamber. Alternative embodiments
provide an expansion chamber which is cylindrical with a uniform
diameter which is equal to the diameter of the turbine seat annular
peripheral surface.
[0064] For preferred embodiments, to provide for inertial balance
of the turbine, if there is only one gas shaft way, the internal
gas shaft way is circular and annular centered in the turbine
shaft, and the gas nozzles are equally spaced 17 at nozzle
locations 18 around the perimeter of the turbine. The nozzle angle
19 between the axis 20 of the gas exit nozzles and the direction of
rotation 21 of the perimeter of the turbine at the nozzle locations
is also uniform. Other means for obtaining inertial balance of the
turbine will be obvious to persons skilled in the art, thereby
allowing variations in the cross section of the turbine shaft and
in the locations and nozzle angles of the gas exit nozzles.
[0065] Certain preferred embodiments utilize multiple shaft gas
ways 8 as shown in FIG. 3. Each shaft gas way is linked to one or
more opposing pairs 66 of gas nozzles, thereby providing for
balance of the torque applied to turbine. Each shaft gas way may be
connected to an independently controlled steam flash generator 67
or other pressurized gas source, providing for independent
activation, deactivation and gas feed for each pair of gas nozzles
connected to the shaft gas way. This provides for increasing and
decreasing the power supplied to the turbine while maintaining the
pressure and the rate of gas flow at each gas nozzle within a
desired range.
[0066] Referring now to FIG. 4, the nozzle angle 19 is oblique to
the direction of rotation 21 of the perimeter of the turbine. A
nozzle angle in a range 22 between 135.degree. and 180.degree. is
believed by the inventor to be preferred. Lesser nozzle angles in
this range increases the ground effect but decreases the efficiency
of the direct momentum transfer of the exiting gas to the turbine,
while greater nozzle angles increase the direct momentum transfer
while decreasing the ground effect.
[0067] Referring again to FIG. 1, the turbine shaft passes through
the first end wall 25 by a first shaft way 26 and through the
second end wall 27 by a second shaft way 28. Structural support and
free rotation of the turbine shaft is provided in the first shaft
way by a first shaft bearing installation 29 and through the second
shaft way by second shaft bearing installation 30. Preferred
embodiments also incorporate a main bearing and bearing retainer
assembly 32. An oil seal 31 is incorporated in the main bearing and
bearing retainer assembly to prevent pressure leakage. In order to
prevent the pressurized gas from escaping through the main bearing
and bearing retainer assembly, cooled oil is pumped by a seal oil
pump 39 from a seal oil reservoir 38 to the oil seal. The viscosity
and back pressure of the oil minimize leakage of the pressurized
gas.
[0068] Pressurized gas 33 is routed from a gas source 34 through a
shaft gas connector 35 to the turbine shaft gas ways. The gas
passes through the turbine shaft gas ways to the shaft gas
distributor 7 which directs the gas from each of the turbine shaft
gas ways to the respective connected nozzles through the nozzle gas
ways.
[0069] Referring now to FIG. 2, the pressurized gas is directed
from the turbine nozzles, imparting a rotational force 36 on the
turbine. Also, because of the proximity of the annular peripheral
surface to the gas exit nozzles and because of the nozzle angle, a
ground effect is experienced as the gas is released from the gas
exit nozzles. This further increases the efficiency of the energy
transfer from the pressurized gas to the turbine. Referring also to
FIG. 5, the annular peripheral surface may have a nozzle groove 70
which is proximal to the perimeter of the turbine to enhance the
ground effect.
[0070] Spent gas is cooled in an expansion chamber 37 which is the
space between the rear face 71 of the turbine and the rear wall 72
of the turbine body. In the case of steam, as the gas is cooled, it
is condensed into water. Oil from the oil seal pressure system and
the condensed water are separated by an oil separator 40. The oil
is then cooled by an oil cooler assembly 41. As the turbine and the
turbine shaft rotate, the front element 42 of the main bearing
assembly rotates with the turbine shaft, but the rear element 43 of
the main bearing assembly is attached to the turbine body and does
not rotate.
[0071] For certain preferred embodiments, as the pressurized gas is
discharged from the gas exit nozzles in a direction opposite the
desired direction of rotation of the turbine, it is also discharged
against the turbine seat annular peripheral surface. This produces
a back force that creates the ground affect, thereby increasing the
efficiency of the engine.
[0072] As pressurized gas is allowed to expand in the expansion
chamber. This cooling process is enhanced by cooled liquid being
circulated through cooling tubes 45 in the walls 46 of the turbine
body. The cooled steam is condensed into water by pumping the steam
by means of the steam pump 47 through the radiator 48. The cooled
water is then pumped into the reservoir 49.
[0073] Referring also to FIG. 6, for embodiments of the present
invention using steam to power the turbine, an embodiment of a
steam generator system 73 which may be used is illustrated. Steam
generators 50 have steam chambers 51 with controlled outputs. These
outputs are controlled by a control valve 52, which are monitored
and controlled by a steam control computer. For preferred
embodiments the steam generators will be flash steam generators 54
as shown in FIG. 1 and FIG. 6. The flash chambers 53 for flash
steam generators will be quite small in relation to the heat
source, thereby providing for a quick recovery. A pressure sensor
56 is used by the steam control computer to monitor the steam
pressure in the flash chamber. The control computer allows the
pressure in the flash chamber to reach a desired pressure and
maintains the pressure at that level. When the need for more steam
is determined by the control computer, the control valve is opened
for that flash chamber. If more steam is required, more control
valves are opened, bringing more flash chambers on line. As the
steam pressure in the flash chamber is depleted, the control
computer determines that more water is required and increases the
water flow.
[0074] The steam generators have several safety devices. One is an
over pressure relief valve 57 and the other is a heat source high
temperature shutoff sensor 58.
[0075] Other embodiments may incorporate a combination of flash
generators and other types of steam generators. This can provide
for a fixed amount of steam at a constant rate while leaving the
flash generators for quick response to special power demands for
the turbine.
[0076] Other embodiments may utilize only a fixed steam system. For
these embodiments, the rotation speed or the amount of power that
is delivered to the turbine is still controlled by a series of
valves which are controlled by the control computer. This type of
steam generator may be more readily adapted to an engine used to
generate electric power for battery storage for use with an
electric motor driven device.
[0077] Turbine balance sensors 59 on the turbine shaft provide data
to the control computer for the determination of whether the
turbine is in balance. If the turbine is determined by the control
computer to be out of balance, the control computer uses a turbine
balancing device 60 to balance the turbine. The turbine balancing
device may consist of four motors on the turbine. The motors are
used to move weights on the turbine. As the weights are moved, the
balance sensors on the output shaft 62 indicate to the computer
whether the turbine is coming into balance or moving further out of
balance. Using this feed back mechanism, the control computer
brings the turbine back into balance.
[0078] The control computer continually monitors and controls the
operating parameters of the turbine engine through use of sensors,
feed back controls, and output devices. Turbine speed, required
torque, gas or steam pressure, turbine balance and direction of
rotation of the turbine are some of the parameters that are
monitored and controlled. The control computer also controls water
levels, water temperature, and water flow for cooling in a steam
system and air flow around the expansion chamber for pressurized
gas. By controlling water flow, the control computer can maximize
the efficiency of the engine.
[0079] Communications between sensors, output devices and the
control computer can be by wire or wireless transmissions. Power to
the control sensors on the turbine may be by rotating connections
61 on the turbine shaft.
[0080] Referring now to FIG. 7, for other preferred embodiment of
the pressurized gas turbine engine 74, steam or other pressurized
gas may be supplied through the engine gas port 75 in the front
wall 10 of the turbine engine.
[0081] Referring now also to FIG. 8, a preferred embodiment of the
turbine engine with the front wall of the turbine engine removed.
For the preferred embodiment shown, the turbine shaft 2 connects to
the rear of the turbine 1 and a seal ring 76 is affixed to the
front face 11 of the turbine and provides a gas seal between the
front face of the turbine and the front wall of the turbine engine,
thereby creating a gas supply zone 77 between the front face of the
turbine and the front wall of the turbine engine which is bounded
by the gas seal. This provides for pressurized gas to be directed
from the engine gas port to the turbine gas port 78. For some
embodiments, such as that shown in the FIG. 8, the turbine seal
ring is not centered on the axis of the turbine 79. This provides
for the more uniform distribution of seal oil for all points of
contact 80 between the turbine seal and the front wall of the
turbine engine. The seal oil enhances the ability of the turbine
seal to minimize pressurized gas leakage between the turbine seal
and the front wall of the turbine engine. The seal oil is typically
injected into the contact zone between the turbine seal and the
turbine engine front wall through a seal oil injector port 81 in
the front wall of the turbine engine as shown in FIG. 7. A detail
of a typical turbine seal ring is shown in FIG. 9.
[0082] Referring now to FIG. 10, the turbine engine is shown with
the front face of the turbine removed. A detail of a typical
turbine front face for these embodiments is shown in FIG. 11.
[0083] For these embodiments, the pressurized gas which is supplied
to the turbine flows into the turbine gas port from the gas supply
zone as shown in FIG. 8, and is distributed down respective nozzle
gas ways 6 to each of the turbine nozzles 5 as shown in FIG. 10.
Referring also to FIG. 12, for the embodiment of the turbine shown
in FIG. 10 and FIG. 12, the nozzle gas ways are cast, formed or
machined in the turbine in the configuration shown. The nozzle gas
ways are then sealed by the turbine front face as shown in FIG.
11.
[0084] For the embodiment of the turbine shown in FIG. 10 and FIG.
12, the nozzles are installed in a nozzle recess 82 in the turbine
perimeter. The nozzles are typically screwed into a nozzle collar
83 thereby connecting each nozzle to the nozzle gas way. The nozzle
recesses provide for the tip 84 of each of the nozzles to be inside
the turbine perimeter 85, thereby providing for streamlining the
turbine perimeter and allowing for a closer tolerance between the
turbine perimeter and the turbine seat peripheral surface 12.
[0085] Referring to FIG. 10, preferred embodiments of the turbine
engine may have a turbine seat peripheral surface 12 with
transverse serrations 86 which increase the ground effect
experienced by the turbine as pressurized gas is discharged through
the nozzles.
[0086] For the embodiments of the turbine engine shown in FIGS. 7
and 8, a spent gas evacuator 87 may be attached to the turbine as
shown in FIG. 14. Referring also to FIG. 13, for these embodiments,
the turbine may have an evacuator spindle 88 extending from the
rear face 89. The spent gas evacuator is anchored to the evacuator
spindle as shown in FIG. 14.
[0087] Referring again to FIG. 14, the transverse serrations 86
typically will extend also to the gas expansion area 90 of the
turbine seat which is proximal to the perimeter of the spent gas
evacuator. For these embodiments, the rear face 91 of the spent gas
evacuator is proximal to the turbine engine rear wall 72 as shown
in FIG. 15. FIG. 14 shows the pressurized gas turbine engine with
the turbine engine rear wall and the spent gas evacuator cover
plate 93 removed.. A detail of the spent gas evacuator cover plate
is shown in FIG. 16. Therefore, for these embodiments, the
expansion chamber is occupied by the spent gas evacuator and the
spent gas is directed to the spent gas evacuation channel 94 for
discharge through the spent gas port 95 as shown in FIG. 15.
[0088] As shown in FIG. 1, the spent gas, seal oil and condensate
are recycled.
[0089] For the embodiments shown in FIG. 15, the turbine shaft 2 is
only supported by turbine shaft bearings 96 in the rear wall of the
turbine engine. Energy output from the turbine engine is from the
turbine shaft.
[0090] Referring now to FIG. 17, a nozzle or one or more opposing
pairs or equally spaced groups of coordinated nozzles may be
connected to separate pressurized gas sources through the use of
multiple turbine gas seals 97 and turbine gas ports 98 which direct
the pressurized gas received through respective engine gas ports in
the front wall of the turbine engine and the respective gas supply
zones 77 between the front face of the turbine and the front wall
of the turbine engine, to respective nozzle gas ways 6 and thus to
the respective nozzle or pairs or groups of coordinated nozzles
102.
[0091] Another embodiment which provides for two separate gas
sources to be utilized with pairs or groups of coordinated nozzles
is shown in FIG. 18 and FIG. 19. This embodiment utilizes a central
internal shaft gas way 8 to transmit gas from one pressurized gas
source through interconnected nozzle gas ways 6 to a first group of
coordinated nozzles 105, and utilizes the annular space 99 between
the central shaft gas way and the inside surface 100 of the shaft
tube 101 of the turbine shaft 2 as a second shaft gas way to
transmit gas from a second pressurized gas source through other
interconnected nozzle gas ways 6 to a second group of coordinated
nozzles 103.
[0092] Referring now to FIG. 20, a preferred embodiment of the
pressurized gas turbine engine of the present invention which
utilizes a pressurized gas turbine 1 having gas nozzles 5 with gas
exit cones 106. A detail of a typical gas nozzle and gas exit cone
are shown in FIG. 24. The utilization of the gas exit cones with
the gas nozzle is to improve the efficiency of the nozzles and to
take advantage of the additional thrust generated by nozzle exit
cones as a result of the formation of a compression or eddy zone
107 in the tip of the plume 108 as shown in FIG. 21. The inventor
has found that gas exit cones with dimensions which are
proportionally similar to the dimensions of a typical rocket engine
exhaust cone work well for certain embodiments of the present
invention.
[0093] As shown for preferred embodiments described above, the
turbine seat peripheral surface 12 can be circular and uniform as
shown in FIG. 20 or can have transverse serrations 86 as shown in
FIG. 22. The gas nozzles and nozzle exit cones can be supported
beyond the perimeter of the turbine central disk 109 by nozzle
support tubes 110 as shown in FIGS. 20 and 22 or can be machined,
formed or cast into the perimeter of the turbine 13 as shown in
FIG. 23.
[0094] Referring to FIG. 23, for this embodiment there is a close
tolerance between the turbine perimeter and the turbine seat
peripheral surface 12. For this embodiment with the gas nozzles and
gas exit cones in the position shown, pressurized gas from each
nozzle pressurizes the gas exit cone in the turbine perimeter and
the pressurized gas receiving chamber 111 in the turbine seat
peripheral surface. The flow of pressurized gas from a nozzle to
the gas exit cone and into the gas receiving chamber, propels the
turbine causing it to rotate in the desired direction 21. As the
turbine rotates, each gas receiving chamber that has been
pressurized subsequently aligns with a back flow receiving chamber
112 in the turbine perimeter, thereby causing pressurized gas to be
transferred from the receiving chamber to the turbine back flow
receiving chamber, thereby imparting additional thrust on the
turbine. Therefore, each gas receiving chamber is used for
consecutive cycles of pressurization, with pressurized gas flowing
from the nozzle and gas exit cones into the gas receiving chamber
when the gas nozzle, the gas exit cone and the gas receiving
chamber are in a pressurization position 113, and de-pressurization
with gas flowing from the gas receiving chamber into the back flow
receiving chamber when the back flow receiving chamber and the gas
receiving chamber are in a de-pressurization position 114.
Depletion of the remaining pressure in the gas receiving chamber
and the back flow receiving chamber, is accomplished by the
depletion chamber 115 as the turbine rotates and the depletion
chamber becomes hydraulically connected to the pressurized gas
receiving chamber prior to the back flow receiving chamber being
hydraulically disconnected from the gas receiving chamber. The
dissipation chamber may be hydraulically connected to a spent gas
receiving and processing system, particularly in the case of steam
driven turbine, so that moisture and heat can be reclaimed and
recycled and oil can be removed.
[0095] Simplified embodiments of the turbine of the present
invention may utilize a single nozzle gas way or interconnected
nozzle gas ways to provide pressurized gas to all of the nozzles.
For the simplest of these embodiments, a single nozzle gas way will
comprise a single chamber in the turbine which is connected to all
the nozzles. A hollow turbine would be one version of this
simplified embodiment of the turbine. A hollow turbine with
dividers to form nozzle gas ways would constitute a simplified
embodiment with two or more nozzle gas ways.
[0096] The present invention can also be used with simplified, high
efficiency generator systems by providing for the direct flashing
of hot water to steam in the nozzles. This has use for a number of
applications such a geothermal wells which usually rely on
superheated water extracted from the wells. The high energy losses
which occur as hot water is flashed to steam and the steam is then
used to power the turbine are substantially reduced through the
direct flashing of superheated water as it is passed through the
gas nozzles of the present invention.
[0097] Other embodiments of the invention and other variations and
modifications of the embodiments described above will be obvious to
a person skilled in the art. Therefore, the foregoing is intended
to be merely illustrative of the invention and the invention is
limited only by the following claims.
* * * * *