JP2002071137A - Micro gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a micro gas turbine generator also applicable as the auxiliary power supply of a fuel cell, which can be carried together with a portable personal computer, a portable communication terminal or various digital apparatus while being contained in an attache case and can generate power continuously for a time longer by a factor of ten to several tens as compared with a current battery power supply having highest performance. SOLUTION: One rotary shaft extending from the central part on the opposite sides of a hollow disc or a deformed hollow disc and supported at the opposite ends is interconnected as a hollow shaft with the space section of the disc, and the end face is opened to the atmosphere. Fuel fed from the center of the other rotary shaft is mixed with air compressed centrifugally in the hollow rotary disc and combusted in the vicinity of the outermost circumferential part of the disc. Generated combustion gas is jetted in the circumferential direction of the disc in order to rotate the disc. A steel disc carrying a permanent disc magnet is fixed integrally to the rotary shaft and electricity is taken out from a winding coil of conductor secured to a stationary part oppositely to the permanent disc magnet.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

TECHNICAL FIELD The present invention relates to a portable personal computer,
The drawback of fuel cells as a source of power required for continuous use of various portable electrical and electronic devices such as portable communication terminals, video cameras, and portable televisions for long periods of time indoors and outdoors where there is no power supply The present invention relates to an ultra-small gas turbine as a heat source for preheating a fuel cell, which also serves as an auxiliary power source for reducing the time required from startup to full power.

[0002]

2. Description of the Related Art When a portable electric device such as a portable personal computer, a portable communication terminal, a portable printer, a portable boombox, a video camera, and a portable television is used indoors and outdoors without a power supply, Conventionally, rechargeable batteries or dry batteries have been used. These power supplies
Technology is being developed to store lighter and more electrical energy.

On the other hand, technological development for reducing the power consumption of portable electric equipment has been progressing, and the continuous use time has been greatly increased due to the synergistic effect of the performance improvement of the power consumption equipment and the performance of the power supply. However, even with such continuous technological progress, the method of storing chemical energy and converting it into electric energy is still the same, and the ability to generate electricity per weight is limited. Therefore, when a portable electric device is used continuously for a long time indoors and outdoors without a power source, there is a disadvantage that a plurality of spare batteries or a large number of spare batteries must be carried.

As an example, when a sports or live show is broadcasted live on the Internet using a portable personal computer, a digital camera, and a communication terminal, the continuous use time of a battery usually included in each device is one to one. It takes about two hours, and in order to carry out live broadcasting for several hours to several tens of hours, a heavy storage battery or a generator had to be separately carried in order to supply necessary power for a long time.

[0005] Fuel cells are expected as a power source for vehicles of the next generation and power sources for small- and medium-scale cogeneration, and many technological developments are being carried out continuously. Reducing the required time is one of the major technical issues. At present, a fuel cell having excellent start-up characteristics, such as a vehicle driven by a gasoline engine or a diesel engine, which is a conventional technology, capable of starting the vehicle immediately by turning a starter key has not yet been realized.

[0006]

With the rapid spread of the Internet and the spread of video equipment such as portable personal computers, portable communication terminals, digital cameras and video cameras, personal use as well as business use. Also, the frequency of using these devices indoors and outdoors without a power source for a long time, connecting to the Internet as needed, and transmitting and receiving data tends to increase further in the future.

A first object of the present invention is to provide a portable personal computer,
A set of video equipment such as a portable communication terminal, digital camera, video camera, etc. can be stored in a single attache case or travel bag together with documents and travel goods, and can be carried for more than ten hours without charging with an external power supply. An object of the present invention is to provide an ultra-small and lightweight portable gas turbine power generator capable of continuous use for several tens of hours.

In the case of a fuel cell, especially for a vehicle, electric power that can be started within a few seconds after startup must be generated due to competition with conventional gasoline engines and diesel engines. It is extremely difficult to configure the fuel cell to generate the electric power required for starting.

A second object of the present invention is to provide a vehicle and stationary fuel cells that function as an auxiliary power supply for supplying insufficient power from startup to full power, and that exhaust gas is supplied to the fuel cell. To provide a gas turbine power generator for a fuel cell auxiliary power supply that is small and lightweight and can also function as a fuel cell preheating or reformed gas generator.

[0010]

In order to achieve the above object, means for realizing a micro gas turbine power generator according to claim 1 will be described with reference to FIGS. 1 and 2 showing a basic principle. I do.

A hollow cylindrical disk I having a guide wing 1 inside the hollow portion or a cylindrical I-shaped hollow shaft 4 communicating with a disk space 3 formed inside the deformed hollow disk 2, and a central portion along the wall surface of the hollow disk 2 A second shaft 7 having a fuel supply hole 6 at the center thereof communicating with a fuel flow path 5 provided toward the outer circumferential direction from the center of the hollow disk 2
Extending to both sides of the center of the

The first hollow shaft 4 and the second shaft 7 are mounted on bearings 9 and 1
0 to make it freely rotatable, open the end face 11 of the I-th hollow shaft 4 to the outside air to allow the board space 3 to communicate with the outside air, and supply fuel from the outside to the fuel supply hole 6 at the center of the II-th shaft. A fuel supply pipe 12 is inserted between the fuel supply pipe 12 and the fuel supply hole 6, and a seal device 13 is provided to shut off the outside air and rotate freely.

A fuel passage 5 provided along the wall surface of the hollow disk 2 is provided with a fuel nozzle 13 provided near the outer peripheral portion of the hollow disk 2.
And a combustor 17 comprising a mixing section 14, a combustion section 15 and a combustion gas injection nozzle section 16 for mixing the fuel ejected from the fuel nozzle 13 with the outside air centrifugally compressed in the panel space 3. At least two or more are provided at rotationally symmetric positions on the outermost peripheral portion of the hollow disk 2, and an ignition plug or an ignition pilot burner 19 is provided on a casing side wall 18 near an outlet of the combustion gas injection nozzle portion 16. The combustion gas ejected from the nozzle is ejected in a substantially circumferential direction of the hollow disk 2.

Further, a steel disk 21 carrying a disk-shaped permanent magnet 20 having at least one pair of N-poles and S-poles alternately arranged in the circumferential direction is attached to either the I-shaft 4 or II-shaft 7. At least one or both of the winding coils 22a made of an electric conductor are provided facing the disk-shaped permanent magnet 20 and provided at least one in the circumferential direction. Whether to fix to the stationary part 35 and take out single-phase AC electricity from the terminals 23a and 24a at both ends of the coil 22a;

Alternatively, each of the winding coils is formed into a winding coil group 22b connected by a Y connection or a △ connection, and the winding coil group 22b is fixed to a stationary portion to form the winding coil group 22b.
Characterized in that three-phase AC electricity is extracted from both ends 23b and 24b of the. FIGS. 1 and 2 show the second embodiment.
An example in which a set of generators is provided on the shaft 7 side is shown.

The outside air sucked in the direction of arrow 25 from the end face 11 of the I-th hollow shaft 4 by the rotation of the hollow disk 2 is centrifugally compressed by the action of the guide blade 1 while flowing in the direction of arrow 26, and Reach 14.

The fuel supplied from the fuel supply pipe 12 in the direction of arrow 27 is provided on the hollow disk 2 through the fuel supply hole 6 provided at the center of the second shaft 7 while being blocked from the outside air by the sealing device 13. Centrifugally compressed while flowing through the fuel flow path 5 in the direction of arrow 28,
While being mixed with the centrifugally compressed outside air in step 4, the gas continuously burns in the combustion section 15 and becomes high-temperature combustion gas, which is ejected from the combustion gas injection nozzle section 16 in the direction of arrow 29 at subsonic or supersonic speed.

The hollow disk 2 supported at both ends by bearings 9 and 10, the first hollow shaft 4, the second shaft 7, and the generator disk 21
The rotating body 8 composed of the combustion gas injection nozzle portion 16 reacts with combustion gas ejected in the
Rotate in the direction of.

The combustion gas ejected from the combustion gas injection nozzle section 16 of the rotating combustor 17 at a speed V in the direction of arrow 29 relatively is the absolute value of C, which is the vector sum with the peripheral speed U of the injection nozzle section 16. It flows out into the diffuser part 31 with the speed and the direction, is decelerated, and has a scroll-shaped exhaust chamber 3.
2 and flows out of the combustion gas outlet 33 in the direction of the arrow 34.

A generator disk 21 made of a steel disk carrying a disk-shaped permanent magnet 20 is integrally attached to one or both of the first hollow shaft 4 and the second shaft 7 with the rotation axis coinciding. The winding coil 22a or the winding coil group 22b made of a conductor faces the disc-shaped permanent magnet 20,
The winding coil 22a is provided at least one or more in the circumferential direction.
Alternatively, the winding coil group 22b is fixed to the stationary portion 35, and electricity is taken out from the terminals 23a and 24a or 23b and 24b provided at both ends of the winding coil 22a or the winding coil group 22b, so that the mechanical connection with the rotating body is achieved. It is possible to provide a single-phase AC generator or a three-phase AC generator that does not require a contact portion and that does not need to apply a voltage for excitation.

The winding coil 22a or the winding coil group 22
terminals 23a and 24a or 23b provided at both ends of b
And the high-frequency single-phase or three-phase alternating current extracted from 24b may be converted into direct current through a not-shown alternating current / direct current converter and then extracted.

[0022]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to FIG.
This will be described in detail with reference to FIG. FIG. 1 is a schematic front sectional view showing a basic structure of a micro gas turbine power generator according to an embodiment of the present invention, and FIG. 2 is a plan sectional view taken along section AA shown in FIG.

Inside the hollow disk or the deformed hollow disk 2, a guide blade 1 is provided in the radial direction, and an end face 11 of the I-th hollow shaft 4 extending from the center of the disk 2 is opened to the outside air. The structure in which the inner disk space 3 communicates with the hollow portion of the I-hollow shaft 4 is a so-called centrifugal compressor, in which the I-hollow shaft 4 and the II-shaft 7 extending to both sides of the center portion of the disk 2. Are supported by bearings 9 and 10, respectively, and are made rotatable. By applying a rotational force to the disk 2, the outside air sucked from the end face 11 is accelerated in the disk space 3 by the action of the guide blades 1. , Centrifuged and compressed.

On the other hand, a fuel supply hole 6 communicating with a fuel flow path 5 provided from the center to the outer periphery along the wall surface of the disk 2 along the wall surface of the disk 2 is provided at the center of the second shaft 7, and gas from the outside is provided. A fuel supply pipe 12 for supplying fuel is inserted into the fuel supply hole 6, and a seal device 1 is provided between the fuel supply pipe 12 and the fuel supply hole 6.
The fuel gas is provided from the center portion to the outer peripheral direction along the wall surface of the disk 2 without leaking to the outside air and without sucking the outside air by making the structure shut off from the outside air and being rotatable by 3. The fuel is supplied to the fuel nozzle 13 at the outermost periphery of the disk 2 via the fuel flow path 5.

Since the fuel is centrifugally compressed by the rotational force when passing through the fuel flow path 5 provided on the wall surface of the disk 2, the fuel also functions as a suction blower or a pump for the fuel. There is no need to pump.

The gaseous or mist-like fuel ejected from the fuel nozzle 13 at the outermost periphery of the disk 2 via the fuel flow path 5 is mixed with the outside air centrifugally compressed in the disk space 3 and the mixing part. The mixture is mixed at 14 and burned in the combustion section 15 to become high-temperature combustion gas, which is ejected from the combustion gas injection nozzle section 16 at a subsonic or supersonic speed in a substantially circumferential direction of the disk 2. The rotating body 8 including the disk 2, the I-th hollow shaft 4, and the II-shaft gives a rotational force in the direction of arrow 30 due to the reaction of the high-speed combustion gas ejected from the combustion gas injection nozzle unit 16.

The number of combustors 17 comprising the fuel gas mixing section 14, the combustion section 15, and the combustion gas injection nozzle section 16 is as follows.
At least two or more at the rotation target position, and preferably, both advantages of stability against vibration and increase in single machine output can be obtained3.
It is better to do above.

An ignition plug or a pilot burner 19 for starting the gas turbine is provided on the casing side wall 18 near the injection nozzle 16.

The bearings 9 and 10 for supporting the rotating body 8 consisting of the disk 2, the hollow shaft I and the shaft II can be any of rolling bearings, sliding bearings, magnetic bearings and gas bearings. Since the bearing peripheral speed is high, it is desirable to use a gas bearing, especially a dynamic pressure type gas bearing. The thrust bearing 3 for restraining the axial displacement of the rotating body 8
It is desirable that the bearings 6 and 37 are also dynamic pressure type gas bearings.

The fuel used in the gas turbine according to the present invention does not need to be a gas at normal temperature, but is a fuel that can be sprayed in a gaseous or mist form from the fuel nozzle 13 and is mixed with an oxidizing gas and ignited to generate heat. Any gaseous or liquid substance that causes a reaction can be a fuel. Examples of substances applicable as fuel include gaseous and liquid hydrocarbons, alcohols, ethers, as well as liquid and gaseous hydrogen, hydrazine, and the like. Examples of the oxidizing gas include air, pure oxygen or a mixed gas of oxygen, and a mixed gas of hydrogen peroxide in addition to air.

The combustor is more preferably a catalytic combustor capable of maintaining stable combustion without misfiring even with lean fuels, in addition to normal burner combustion. As a material for the catalytic combustor, it is preferable to use a honeycomb, lattice or sintered product in which a metal such as platinum, copper, vanadium, tungsten, molybdenum, manganese or an oxide thereof is coated on a substrate.

The exhaust chamber 32 connected to the diffuser section 31 is an example of a scroll shape in which the sectional area gradually increases in the circumferential direction toward the combustion gas outlet 33.
It is not always necessary to make the scroll shape, and the exhaust may be exhausted from the entire circumference or a part thereof in the circumferential direction after a sufficient volume of the exhaust chamber 32 connected to the diffuser section 31 is secured.

The micro gas turbine according to the present invention further comprises a steel disk 2 carrying a disk-shaped permanent magnet 20 having at least one pair of circumferentially alternately arranged N poles and S poles.
1 is integrally attached to one or both of the first hollow shaft 4 and the second shaft 7 with the rotation axis coinciding, and the winding coil 22 made of a conductor faces the disk-shaped permanent magnet 20; At least one or more coils are provided in the circumferential direction, and the coil 22 is fixed to the stationary portion 35 so that the gas turbine and the generator of the coil 22 are integrally connected to each other. It is characterized in that it is a very small gas turbine power generator. In addition, the winding coil 22a shown in FIG. 1 indicates a winding coil group for extracting single-phase AC electricity, and the winding coil 22b indicates a winding coil group connected by Y connection or △ connection.

The micro gas turbine generator according to the present invention, in which the generator is integrally connected, further includes a winding coil group 22a.
Single-phase alternating current or winding coil group 22 obtained from
b) an AC / DC converter for converting the three-phase AC electricity obtained from b into a DC current of 12 to 24 volts, and a fuel flow control device for controlling the output voltage to be constant regardless of the power load. With the provision, all functions required as a power generation device can be provided.

It is to be noted that the convenience can be further enhanced by housing both the AC / DC converter and the fuel flow rate control device in the same container housing the micro gas turbine generator according to the present invention.

[0036]

3 and 4 show a further development of the structure shown in FIGS. 1 and 2 showing the basic principle, and have a structure closer to the actual structure. FIG. 3 is a front cross-sectional view of the micro gas turbine generator according to the embodiment of the present invention, and FIG. 4 is a plan cross-sectional view along the cross section AA shown in FIG. The structure shown in FIGS. 1 and 2 is different from the structure shown in FIGS. 3 and 4 in the following five points, but does not deviate from the basic principle shown in FIGS. (1) Three combustors are arranged at rotationally symmetric positions on the circumference for the purpose of improving the stability against vibration and the output of a single unit. (2) The combustor has a double cylindrical structure and a structure capable of cooling the combustor wall in order to prevent the strength of the combustor from decreasing due to high temperature. (3) The combustor is shortened by relocating the header of the fuel nozzle upstream of the cylinder of the combustor and at a position parallel to the side wall of the hollow disk. (4) A configuration in which an oxidation catalyst is arranged in the combustion section to cause catalytic combustion, and stable combustion is obtained without misfiring even in a fuel-air-lean mixture. (5) The second shaft is a hollow shaft, and the inner surface of the hollow shaft is supported by a bearing, so that the axial dimension is shortened and the size is further reduced. In the following, a part different from those in FIGS. 1 and 2 showing the basic principle will be described with particular emphasis. Parts having the same functions as those in FIGS. 1 and 2 are denoted by the same symbols as those in FIGS.

It has a substantially triangular cross section, and 3
By providing a guide vane 1 in the radial direction toward the apex of the triangle and rotating the deformed hollow disk 2 inside the deformed hollow disk 2 in which the set of combustors 17 are arranged, the first space I in which the disk space 3 communicates is provided. The outside air sucked from the end face 11 of the hollow shaft reaches the mixing section 14 located near the outermost periphery of the deformed hollow disk 2 while being centrifugally compressed.

On the other hand, the fuel supplied to the fuel supply pipe 12 passes through the fuel supply hole 6 provided at the center of the second shaft 7 while being blocked from the outside air by the sealing device 13, and is applied to the wall surface of the deformed hollow disk 2. A fuel nozzle 1 located in the vicinity of a combustor 17 through a fuel flow path 5 provided radially from a center portion along
It gushes from 3.

The fuel ejected from the fuel nozzle 13 is
It mixes with the outside air sucked from the end face 11 of the hollow shaft and centrifugally compressed in the board space part 3 in the mixing part 14, and flows into the catalytic combustion part 38 as a mixed gas.

The catalytic combustion section is composed of a lattice-like or honeycomb-like substrate made of a heat-resistant metal or ceramic, and platinum, gold,
It is coated with a metal consisting of a single component or a composite component selected from vanadium, copper, manganese, and palladium or their oxides.Stable combustion without misfiring even when the fuel concentration is extremely low. There are benefits to be gained. In addition, particularly during high-load operation, stable combustion can be obtained without blowing out.

By employing the catalytic combustion, the length of the combustion section 15 for holding the flame can be shortened, and the size of the combustor 17 can be reduced. There is also an advantage that stress can be reduced.

In this embodiment, the combustor 17 has a double shell structure disposed inside the cylindrical shell 39 of the deformed hollow disk 2, and an opening 40 for introducing cooling air is provided between the shells. Since the cooling holes 41 for film cooling the inner surface of the combustor 17 are provided, the temperature of the portion where the combustor 17 is exposed to a high temperature is reduced, and sufficient strength can be secured.

In this embodiment, three combustors 17 are arranged at rotationally symmetric positions.
As compared with the configuration in which two combustors are arranged at the 180 ° symmetrical position shown in FIG.
The advantage of increased stability against vibration can also be expected.

Further, in the present embodiment, the second shaft is a hollow shaft and the inner surface of the hollow shaft is supported by the bearing 10, so that the outer surface of the second shaft is the bearing 1 as shown in FIGS.
Compared to the case of supporting at zero, the axial dimension can be further reduced, and a great effect can be expected in realizing the reduction in size and weight of the device.

[0045]

As described above, according to the present invention,
A combustor is arranged near the outermost periphery of the centrifugal compressor, and high-temperature combustion gas is ejected from the outermost periphery of the centrifugal compressor at high speed in a substantially circumferential direction, and the centrifugal compressor is driven by the reaction of the ejected combustion gas. So, like a conventional gas turbine, after converting air to pressure energy using a compressor and taking it out, and adding fuel to make high-temperature, high-pressure combustion gas,
Compared to the method in which pressure energy is converted into velocity energy by introducing it into a gas turbine and power is taken out, the intermediate process is omitted, and the rotating body by compression / combustion and reaction of injected gas inside one rotating body Is realized, and a small, lightweight and inexpensive gas turbine can be obtained. In addition, since the gas turbine according to the present invention is integrally assembled with the disk-shaped ultra-thin AC generator, the entire device is small, lightweight and inexpensive, and in addition to the very thin disk-shaped gas turbine. It has become possible to construct a power generator.

The smallest gas turbine power generating device according to the present invention has a gas turbine main body, a generator, and a gas turbine in a volume of approximately 150 mm in length, 190 mm in width and 25 mm in height, which are substantially the same dimensions as a video cassette tape. A cassette fuel cylinder, a DC converter, and a combustion control device can be housed therein.
Continuous power generation is possible for 0 hours.

As described above, a small and light-weight, continuous power generation for a long time is possible, so that it can be used not only as a business power source for broadcasting live video of sports, various events, etc.
It can be expected to be effective on a personal and business level, such as in business, leisure, academic research outdoors, military applications, and emergency power supplies.

Furthermore, the micro gas turbine power generator according to the present invention can be expected to have a great effect on improving the starting characteristics of a fuel cell, especially a fuel cell for a vehicle. Fuel cells convert chemical energy into electrical energy,
It is extremely difficult to turn on the starter key and immediately start the vehicle, such as a gasoline engine or a diesel engine, which is a conventional motor for a vehicle. Therefore, by adopting a hybrid configuration of the gas turbine generator and the fuel cell according to the present invention, the gas turbine generator according to the present invention functions as an auxiliary power supply for the fuel cell until the fuel cell warms up,
The biggest disadvantage of the fuel cell can be compensated. Also,
By supplying gas turbine exhaust to the fuel cell,
A secondary effect of shortening the warm-up time of the fuel cell can also be expected.

[0049]

[Brief description of the drawings]

FIG. 1 is an assembled sectional view showing a basic configuration of the present invention.

[0050]

FIG. 2 is a sectional view taken along line AA of FIG. 1 showing a basic configuration of the present invention.

[0051]

FIG. 3 is an assembled sectional view according to the embodiment of the present invention.

[0052]

FIG. 4 is a sectional view taken along line AA of FIG. 3 according to the embodiment of the present invention.

[0053]

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Guide blade 2 Hollow disk or deformed hollow disk 3 Disk space part 4 I hollow shaft 5 Fuel flow path 6 Fuel supply hole 7 II shaft 8 Rotating body 9 Bearing for I hollow shaft 10 Bearing for II shaft 11 Hollow shaft End face 4 12 Fuel supply pipe 13 Fuel nozzle 14 Mixing part 15 Combustion part 16 Combustion gas injection nozzle 17 Combustor 18 Casing side wall 19 Spark plug or pilot burner 20 Disc-shaped permanent magnet 21 Steel disc 22a Winding coil (for single phase) 22b Winding coil group (for three phases) 23a Winding coil terminal 1 (for single phase) 23b Winding coil terminal 1 (for three phases) 24a Winding coil terminal 2 (for single phase) 24b Winding coil terminal 2 (For three phases) 25 Outside air intake direction 26 Intake outside air flow direction 27 Fuel gas supply direction 28 Fuel flow direction 29 Combustion gas ejection direction 30 Rotation direction 31 Diffuser part 32 Exhaust chamber 33 Combustion gas outlet 34 Combustion gas outflow direction 35 Stationary part 36 Thrust bearing (suction side) 37 Thrust bearing (generator side) 38 Catalyst combustion part 39 Cylindrical shell 40 Opening 41 Cooling hole

Claims (7)

[Claims] A hollow cylindrical disk having a guide wing inside a hollow portion or a hollow cylindrical portion formed inside a deformed hollow disk communicates with a hollow cylindrical I-shaft, and an outer peripheral portion extending from a central portion along a wall surface of the hollow disk. The second shaft having a fuel supply hole at the center communicating with the fuel flow path provided in the direction at the center is configured to extend on both sides of the center of the hollow disk, and the first hollow shaft and the second shaft are bearings. It is supported and rotatable, and the end face of the hollow shaft I is open to the outside air, allowing the space in the panel to communicate with the outside air.
A fuel supply pipe for supplying gaseous fuel from the outside is inserted into the fuel supply hole at the center of the second shaft, and the space between the fuel supply hole and the fuel supply pipe is shut off from the outside air by a sealing device and is rotatable. The fuel flow path provided along the wall surface of the hollow disk communicates with a fuel nozzle provided in the vicinity of the outer periphery of the hollow disk, and the fuel ejected from the fuel nozzle is centrifugally compressed in the disk space. At least two or more combustors each including a mixing section for mixing with outside air, a combustion section, and a combustion gas injection nozzle section are provided at rotationally symmetric positions on the outermost periphery of the hollow disk, and a casing near the combustion gas injection nozzle section exit. An ultra-small gas, wherein an ignition plug or a pilot burner for ignition is provided on a side wall, and combustion gas ejected from the combustion gas injection nozzle portion is ejected in a substantially circumferential direction of a hollow disk. Turbine. 2. The micro gas turbine according to claim 1, wherein the outside air is air or an oxidizing gas containing an oxidizing agent. 3. The micro gas turbine according to claim 1, wherein the combustor is a catalytic combustor using a metal or metal oxide catalyst made of platinum, gold, vanadium, copper, manganese, or palladium. 4. A rolling bearing, a sliding bearing, a magnetic bearing,
The micro gas turbine according to claim 1, wherein a hydrostatic or dynamic gas bearing is used. 5. A steel disk carrying a disk-shaped permanent magnet having at least one pair of pairs of alternating N-poles and S-poles in the circumferential direction is mounted on one of the first hollow shaft and the second shaft. Attached integrally with both rotating shafts coincident with each other, provided with at least one winding coil made of a conductor facing the disk-shaped permanent magnet in the circumferential direction, fixing the winding coil to the stationary part,
Either take out single-phase AC electricity from both ends of the winding coil, or make each winding coil group into a Y-connection or △ -connection winding coil group, and fix the winding coil group to the stationary part The micro gas turbine according to claim 1, further comprising a generator configured to extract three-phase AC power from both ends of the coil group. 6. An AC / DC converter for converting single-phase or three-phase AC electricity obtained from both ends of a winding coil group into a DC current.
The micro gas turbine according to claim 1, further comprising a DC converter. 7. A fuel flow control device for detecting the voltage and frequency of single-phase or three-phase AC electricity obtained from both ends of a winding coil group and maintaining the voltage and frequency at constant values, Alternatively, a fuel flow control device for detecting an output voltage obtained from an AC / DC converter outlet terminal and maintaining the output voltage at a constant value is provided. The micro gas turbine according to claim 5.