JP2003074852A - Micro gas-turbine combustion equipment - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide small sized and compact micro gas-turbine combustion equipment. SOLUTION: Combustion equipment 2 are placed annularly around a vertical prolonged-line of a gas-turbine rotation axis. A plurality of air holes are provided in the combustion equipment 2 for supplying compressed air in combustion chambers 11. A nozzle 14 for injection of a fuel gas in the combustion chamber 11 is each provided in a baffle plate 13 as a partition board.

Description

Detailed Description of the Invention

[0001]

FIELD OF THE INVENTION The present invention relates to a micro gas turbine, and more particularly to a combustor thereof.

[0002]

2. Description of the Related Art In a distributed energy system in which a large number of medium-sized and small-sized power generation facilities are distributed and installed, instead of concentrating energy, particularly electric energy, in a large-scale power generation plant as in the conventional case,・ Various types of small power generation facilities are possible, but as a small power generation facility for small apartments or small living areas with less than about 100 families, in the future as a small power generation facility for families, 20 kW of fuel cell and micro gas turbine A hybrid system with a capacity of ~ 80 kW is considered to be a promising plan.

That is, if a fuel cell and a micro gas turbine are used in a hybrid manner, high efficiency may be obtained, and power generation in a region close to the consumer is high because cogeneration (cogeneration) is possible. There is a possibility that the heat utilization rate can be achieved, so the future is expected.

[0004]

As described above, such a micro gas turbine is expected as a small-sized power generation facility for small apartments or small living areas, and in the future for families. Stabilization of operation, cleaning of exhaust gas are very important for the development of micro gas turbine.

In order to miniaturize the micro gas turbine, stabilize the fire, and purify the exhaust, it is necessary to miniaturize the combustor, reduce the size of the combustor, stabilize the fire, and purify the exhaust.

The present invention has been made in view of the above points, and an object thereof is to provide a micro gas turbine combustor which is small, compact, stable, and has clean exhaust gas.

[0007]

In order to achieve the above-mentioned object, the present invention is constructed as follows.

That is, the micro gas turbine combustor according to the present invention is a micro gas turbine combustion system in which fuel gas and compressed air from a compressor are introduced to combust the fuel gas to generate combustion gas for driving the turbine. In the reactor, a plurality of combustion chambers are annularly arranged around a virtual extension line of the rotation axis of the turbine, and a partition plate having a plurality of air holes for discharging the compressed air into the combustion chambers is provided in each combustion chamber. A plurality of them are provided correspondingly.

According to the present invention, the plurality of combustion chambers are annularly arranged around the virtual extension line of the rotation axis of the turbine to form an annular combustor. Therefore, the micro gas turbine including the combustor can be miniaturized. In addition to the above, the combustion gas can be smoothly supplied to the radial gas turbine having the combustion gas inlet on the outer periphery.

Further, since the partition plate having the plurality of air holes for discharging the compressed air into the combustion chamber is provided, the compressed air is discharged into the combustion chamber from the plurality of air holes of the partition plate, and the fuel is blown from the nozzle. As a result, a circulating flow of air, fuel, and a mixture thereof is generated, flame stability can be ensured, and the concentration of non-clean component in exhaust gas can be reduced.

The micro gas turbine combustor of the present invention is a micro gas turbine combustion system in which fuel gas and compressed air from a compressor are introduced to combust the fuel gas to generate combustion gas for driving the turbine. In the vessel, concentric with the virtual extension of the rotation axis of the turbine,
A combustion chamber defined by a cylindrical inner wall and an outer wall is provided, and a partition plate having a plurality of air holes for discharging the compressed air into the combustion chamber is provided.

According to the present invention, since the combustion chamber is formed concentrically with the virtual extension line of the rotation axis of the turbine by the cylindrical inner wall and the outer wall, the combustion chamber becomes an annular combustor. The equipped micro gas turbine can be downsized, fire can be stabilized, and exhaust gas can be cleaned.
The combustion gas can be smoothly supplied to the radial gas turbine having the combustion gas inlet on the outer periphery.

Further, since the partition plate having the plurality of air holes for discharging the compressed air into the combustion chamber is provided, the compressed air is discharged into the combustion chamber from the plurality of air holes of the partition plate, and the fuel is blown from the nozzle. As a result, a circulating flow of air, fuel, and a mixture thereof is generated, flame stability can be ensured, and the concentration of non-clean component in exhaust gas can be reduced.

In another embodiment of the present invention, the partition plate is provided with a single or a plurality of nozzles for ejecting the fuel gas into the combustion chamber.

According to the present invention, the jet of fuel gas and the jet of air are jetted from the nozzle and the air hole of the same partition plate, so that the Reynolds number is prevented from decreasing and the mixing of fuel gas and air due to turbulence is excellent. In addition, as a result of the longer residence time due to the circulating flow of the air ejected from the air holes, the flame becomes shorter and the length of the combustion chamber can be shortened, so that the combustor can be downsized and the flame can be shortened. Can be stabilized and the concentration of the non-clean component in the exhaust can be reduced.

[0016]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be described in detail below with reference to the drawings.

FIG. 1 is a schematic configuration diagram of a micro gas turbine including a combustor 2 according to one embodiment of the present invention.

The micro gas turbine of this embodiment compresses air with a combustor 2, a turbine 3 which rotates with a combustion gas A from the combustor 2 and drives a generator and a compressor 4 (not shown), and air. The compressor 4 and the regenerative heat exchanger 1 for heating the compressed air D by exchanging heat between the exhaust C of the turbine 3 and the compressed air D from the compressor 4 are provided.

The air B introduced into the compressor 4 becomes a compressed air D having a high temperature, for example, about 250 ° C., and is exchanged with the exhaust gas C of the turbine 3 in the regenerative heat exchanger 1,
For example, it is heated to about 650 ° C. The temperature of the exhaust gas C of the turbine 3 introduced into the regenerative heat exchanger 1 is, for example,
It is about 700 ° C.

Hot compressed air E from the regenerative heat exchanger 1
Is introduced into the combustor 2 into which fuel (not shown) is introduced,
In the combustor 2, the fuel gas is burned to generate a combustion gas A having a high temperature, for example, about 1000 ° C., and the turbine 3
Is driven, and the compressor 4 is operated by the rotation of the turbine 3 and an unillustrated generator is operated to generate electric power.

In this embodiment, the micro gas turbine combustor is made small and compact with stable and high combustion efficiency, and a plurality of combustors 2 are connected to the rotary shaft of the turbine 3 in order to purify exhaust gas. It is arranged in a ring around the virtual extension of the heart.

As shown in FIG. 2, each combustor 2 is formed with a plurality of air holes 12 for discharging the hot compressed air E, which has been heat-exchanged by the regenerative heat exchanger 1, into the combustion chamber 11. The disk-shaped partition plate 13 is provided, and the partition plate 13 is provided.
Fuel gas at a substantially central position in the radial direction of the combustion chamber 11
A nozzle 14 that ejects inside is provided.

In this way, the plurality of combustors 2 are connected to the turbine 3
Since they are arranged in an annular shape around the rotation axis, the micro gas turbine including the combustor can be downsized. Further, since it is an annular combustor, the combustion gas can be smoothly supplied to the radial gas turbine having the inlet of the combustion gas on the outer periphery. The annularly arranged combustor 2 has a shape suitable for guiding the preheated compressed air E flowing out from the spiral-shaped regenerative heat exchanger 1 described later.

In this embodiment, each combustor 2 is further provided.
Includes a partition plate 13 in which a plurality of air holes 12 for discharging compressed air into the combustion chamber 11 are formed, and thus compressed air is discharged from the plurality of air holes 12 into the combustion chamber 11, When the fuel is blown from the nozzle 14, a circulating flow of air, fuel and a mixture thereof is generated, flame stability can be ensured, and the concentration of the non-clean component in the exhaust can be reduced.

Moreover, since the jet of fuel gas and the jet of air are jetted from the small-sized nozzle 14 and the air hole 12 of the same partition plate 13, the Reynolds number is prevented from decreasing and the fuel gas and air due to turbulence flow. As a result of improving the mixing and further increasing the residence time due to the circulation flow of the air ejected from the air holes 12, the flame is shortened and the length of the combustion chamber 11 can be shortened. Therefore, the combustor 2 can be downsized. can do.

Further, since the combustor 2 is arranged inside the regenerative heat exchanger 1, it is advantageous in keeping the temperature of the combustion gas A.

Further, in this embodiment, the performance of the regenerative heat exchanger 1 is enhanced, that is, heat can be quickly exchanged, and the pressure loss when the exhaust gas C and the compressed air D of the turbine 3 pass is small. In order to do so, it is configured as follows.

That is, in the regenerative heat exchanger 1 of this embodiment, as shown in FIG. 1, the exhaust gas C flow path 5 of the turbine 3 and the compressed air D flow path 6 of the turbine 3 are connected to each other. The plurality of flow paths 5 and 6 are formed in a spiral shape around the extension line of the rotation axis, and are formed in layers so as to be adjacent to each other via a thin plate 7 made of stainless steel, for example.

Since the flow path 5 for the turbine exhaust C and the flow path 6 for the compressed air D are formed around the extension line of the rotation axis of the turbine 3 as described above, the micro gas provided with the regenerative heat exchanger 1 concerned. It is possible to reduce the size of the turbine.

In this embodiment, the layers of the plurality of flow channels are
Although it is formed in a spiral shape, as another embodiment of the present invention, it may be formed in a concentric shape instead of the spiral shape.

In this embodiment, as shown in a partially enlarged view of FIG. 3, in each flow path, a large number of, for example, stainless steel wires are wound as a heat transfer member. A spiral spring 8 is filled and arranged along the flow paths 5 and 6.

As described above, a large number of spiral springs 8 in which the wire is spirally wound are provided along the flow paths 5 and 6 of the exhaust gas C and the compressed air D of the turbine 3 along the flow paths 5 and 6. Since it is filled and arranged in the
Compared with the case where the heat transfer member is not filled, the flow rate approaches the uniform distribution, the flow velocity near the thin plate 7 that divides the layered flow paths 5, 6 increases, and the flow path 5 of the turbine exhaust C and the flow path of the compressed air D are increased. The heat transfer area between the exhaust gas C and the compressed air D of the turbine 3 is increased by the large number of spiral springs 8, and the fin effect can be enhanced. This further promotes heat transfer between the flow path 5 of the turbine exhaust C and the flow path 6 of the compressed air D.

Moreover, since a large number of spiral springs 8 are arranged along the flow paths 5 and 6, the void ratio is high and an excessive pressure loss is not caused.

FIG. 4 is a diagram showing a method of manufacturing the regenerative heat exchanger 1. As shown in FIG. 3A, a wire 8 or a ribbon having a small width is wound around a rod 9 having a required outer diameter and length in a spiral shape at an appropriate pitch, and the rod 9 is pulled out. As a result, the spiral spring 8 is manufactured.

Next, a spiral spring 8 is provided on one surface of the thin plate 7 coated with the solder paste, for example, with a plurality of pitches arranged along the flow path direction as shown in FIG. They are arranged side by side, and the lower surface of the thin plate 7 is heated to melt the solder paste, and the spiral spring 8 is attached to the thin plate 7.
Then, the spiral spring 8 is soldered to the thin plate 7 by pressing the thin plate 7 to rapidly cool the thin plate 7 to manufacture the thin plate mat 10.

Next, as shown in FIG. 3C, the two thin plate mats 10 are stacked and wound in a spiral shape to be molded. In order to separate the flow path 5 of the exhaust gas C and the flow path 6 of the compressed air D of the turbine 3, the winding start end side and the winding end side are closed by appropriate means. After that, the header portion is attached and heat treatment is performed to remove the solder.

In this way, the spiral springs 8 formed by spirally winding the wire are arranged side by side on one surface of the two thin plates 7, and they are spirally wound to form a plurality of layered flow paths 5. Since 6 is formed, the regenerative heat exchanger 1 can be easily manufactured without requiring any special material or manufacturing method.

Further, since the filling layer of the spiral spring 8 also has a sound deadening effect, it is suitable as a hybrid system with a fuel cell as a micro gas turbine expected as a power generation facility for small apartments or small living areas. is there.

In the above-described embodiment, the heat transfer member has a spiral shape, but the shape is not limited to the spiral shape, and may be a bundle shape in which wires are bundled or other shapes.

Since the spiral spring and the bundle that bundles the wires are in close contact with the thin plate 7 even after the solder paste is melted and removed due to its elasticity, the contact heat conduction resistance with the thin plate is kept small, and the effective fin is effective. The effect is maintained.

In the above embodiment, the plurality of combustors 2
Is arranged around the rotation axis of the turbine 3, the combustor 2 ′ is replaced with a virtual extension line of the rotation axis of the turbine as shown in FIG. 5 as another embodiment of the present invention. A single combustor, which is concentrically divided by a cylindrical inner wall and an outer wall, is used as the combustor 2 ', and the high-temperature compressed air E heat-exchanged by the regenerative heat exchanger 1 is stored in the combustion chamber 11'. A plurality of air holes 12 'for discharging to the inside may be formed, and a hollow disk-shaped partition plate 13' provided with a nozzle 14 'for ejecting fuel gas into the fuel chamber 11' may be provided.

[0042]

As described above, according to the present invention, since the annular combustor is provided annularly around the virtual extension line of the rotational axis of the turbine, the side of the combustor is arranged so as to be orthogonal to the rotational axis of the turbine. It is possible to reduce the size of the micro gas turbine equipped with the combustor as compared with a part of the conventional structure in which the combustor is protruded toward the radial direction. Can be supplied with combustion gas.

Further, the compressed air is discharged into the combustion chamber from the plurality of air holes of the partition plate, and the fuel is blown from the nozzle, so that a circulating flow of air, the fuel and the air-fuel mixture is generated,
The flame can be held stably and at the same time the concentration of non-clean components in the exhaust can be reduced.Furthermore, the jet of fuel gas and the jet of air are jetted from the nozzles and air holes of the same partition plate. , The decrease of Reynolds number is prevented to improve the mixing of fuel gas and air due to turbulence, and the residence time is lengthened due to the circulating flow of air ejected from the air holes. Can be shortened and therefore the combustor can be miniaturized.

[Brief description of drawings]

FIG. 1 is a schematic configuration diagram of a micro gas turbine according to an embodiment of the present invention. .

2 is a block diagram of the combustor of FIG. 1. FIG.

FIG. 3 is an enlarged view showing a part of the regenerative heat exchanger of FIG.

FIG. 4 is a diagram for explaining a manufacturing procedure of the regenerative heat exchanger of FIG.

FIG. 5 is a configuration diagram of a combustor according to another embodiment of the present invention.

[Explanation of symbols]

1 Regenerative heat exchanger 2,2 'combustor 3 turbine 4 compressor 11,11 'combustion chamber 12,12 'air holes 13,13 'baffle board 14,14 'nozzle

Claims (3)

[Claims] 1. A micro gas turbine combustor in which fuel gas and compressed air from a compressor are introduced to combust the fuel gas to generate combustion gas for driving a turbine, wherein a plurality of combustion chambers are provided. A plurality of partition plates arranged annularly around a virtual extension line of the rotation axis of the turbine and having a plurality of air holes for discharging the compressed air into the combustion chamber are provided corresponding to each combustion chamber individually. Characteristic micro gas turbine combustor. 2. A micro gas turbine combustor in which fuel gas and compressed air from a compressor are introduced to combust the fuel gas to generate combustion gas for driving a turbine, wherein Concentric with the virtual extension line, equipped with a combustion chamber partitioned by a cylindrical inner wall and outer wall,
A micro gas turbine combustor comprising: a partition plate having a plurality of air holes for discharging the compressed air into a combustion chamber. 3. The micro gas turbine combustor according to claim 1, wherein the partition plate is provided with a single or a plurality of nozzles for ejecting the fuel gas into the combustion chamber.