JP3378850B2 - Heat exchanger and gas turbine device using the same - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a heat exchanger in which a core for heat exchange is housed inside a casing having a circular cross section, and a gas turbine device using the heat exchanger.

[0002]

2. Description of the Related Art In a gas turbine, a heat exchanger is provided in order to improve thermal efficiency, and exhaust gas discharged from the turbine is
There is a device that exchanges heat with the compressed air before it leaves the compressor and is introduced into the combustor. As a heat exchanger provided in such a gas turbine, as shown in FIG. 6, a cross section in which a plurality of flat heat transfer plates 32 partitioning the exhaust gas passage 33 and the air passage 34 are arranged in parallel at a predetermined interval. A structure is known in which a rectangular core 31 is housed inside a casing (not shown).

The front and rear ends of the air passage 34 in the core 31 are closed by blind plates, and the air passage 34 is formed on the rear side surface.
An inflow port 35 for inflowing air is provided, and an outflow port 36 for air passing through the air passage 34 is provided on the front side surface. While the compressed air A exiting the compressor flows from the inflow port 35 through the air passage 34 and out the outflow port 36, heat exchange is performed between the compressed air A and the exhaust gas E passing through the exhaust gas passage 33. The compressed air A is heated by the heat of the exhaust gas E and then introduced into the combustor of the gas turbine.

[0004]

However, the housing of the gas turbine is generally circular in cross section, and the casing of the heat exchanger installed on the exhaust gas outflow side is rectangular in cross section according to the cross sectional shape of the core 31. Then, the exhaust gas will flow from the housing with a circular cross section to the casing with a rectangular cross section, and the flow of the exhaust gas E to the heat exchanger will be non-uniform, and the heat exchange efficiency will decrease.

Further, since the compressed air A is supplied to the heat exchanger installed in the gas turbine as described above, it is necessary to make the casing of the heat exchanger a pressure resistant structure. Therefore, in order to obtain high compressive strength, the casing 37 has a circular cross section as shown in FIG. 7. However, in the heat exchanger, the core 31 has a rectangular cross section. A large space S is generated between them, and the size of the heat exchanger becomes large.

The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a small-sized heat exchanger having high heat exchange efficiency and a gas turbine device using the same.

[0007]

In order to achieve the above-mentioned object, in the heat exchanger according to the present invention, a heat exchange between a first fluid and a second fluid is provided inside a casing having a circular cross section. The core of is stored. The core has a hexagonal cross-sectional shape and is divided into three core divided bodies each having a parallelogrammatic cross-section including two adjacent sides of the hexagon.
In each core division body, a plurality of flat heat transfer plates that partition the first passage through which the first fluid flows and the second passage through which the second fluid flow are arranged in parallel at predetermined intervals. Here, the cross section means a cross section in a direction orthogonal to the axis.

According to the heat exchanger, since the cross-sectional shape of the core housed inside the casing is hexagonal, there is no waste generated between the casing and the core having a circular cross-section capable of ensuring the compressive strength. The space is reduced, and the heat exchanger can be small and have high heat exchange efficiency. Further, since each core divided body is configured by disposing a plurality of flat heat transfer plates, it is easy to manufacture.

In a preferred embodiment of the present invention, a first inlet for introducing a low temperature first fluid into the first passage is provided on a side surface of a rear portion of the core, and a first passage is provided on a side surface of a front portion of the core. First fluid outlets therethrough are each provided,
An introduction path for introducing the first fluid from the front of the core through the side surface of the core to the first inlet is formed between the core and the casing, and the second fluid flows from the front surface of the core to the second passage. It flows into the passage and is discharged from the rear surface of the core.

In such a structure, since the low temperature first fluid passes through the introduction passage formed between the core and the casing, the temperature rise of the casing is suppressed and at the same time,
The loss due to heat dissipation of the heat exchanger is reduced.

Further, the gas turbine device according to the present invention is
It has the heat exchanger of the said structure, and the gas turbine connected to the front part of this heat exchanger. On the front of the heat exchanger,
A second inlet for introducing air from the compressor of the gas turbine into the inlet passage, a combustor outlet for introducing air from the outlet to a combustor of the gas turbine, and the turbine of the gas turbine were exited. An exhaust gas inlet is formed to allow the exhaust gas to flow into the second passage of the core. On the back of the heat exchanger,
An exhaust port for discharging the exhaust gas passing through the second passage to the outside is formed.

According to the gas turbine apparatus, the heat exchanger performs heat exchange between the air discharged from the compressor of the gas turbine and the exhaust gas discharged from the turbine of the gas turbine.
Since the heated air is guided to the combustor of the gas turbine, the thermal efficiency of the gas turbine is improved. Further, the miniaturization of the heat exchanger enables miniaturization of the entire gas turbine device.

[0013]

Preferred embodiments of the present invention will be described in detail below with reference to the drawings. FIG. 1 is a vertical sectional view of a gas turbine device using a heat exchanger according to an embodiment of the present invention. This gas turbine device has a gas turbine 1 and a heat exchanger 3 connected to the rear part thereof.

The gas turbine 1 includes a centrifugal compressor 4 and a turbine 6 fixed to a rear end of a rotary shaft 5 of the compressor 4.
And a combustor 7. The compressor 4 compresses the air IA introduced from the intake passage 8 and supplies the compressed air A to the combustor 7 via the heat exchanger 3 at the rear part of the gas turbine 1 and is driven by the turbine 6. To be done. The combustor 7 has a fuel nozzle 10 for injecting a gas or liquid fuel F into the combustion chamber 9, and the fuel F and the compressed air A fed into the combustion chamber 9 through the heat exchanger 3. It is mixed and burned. The high-temperature and high-pressure combustion gas G is sent to the turbine 6, and the energy of the combustion gas G drives the turbine 6. A load is connected to the front end of the rotary shaft 5.

The heat exchanger 3 includes the high temperature exhaust gas E discharged from the turbine 6 of the gas turbine 1 and the compressor 4 of the gas turbine 1.
The heat exchange core 19 having a hexagonal cross section as shown in FIG. 2 is provided inside the casing 18 having a circular cross section. It is configured to be stored. The core 19 is divided into three core divided bodies 20 (FIG. 4) having a parallelogram cross section including two adjacent hexagonal sides P1 and P2. Each core division 20
Is a plurality of flat heat transfer plates 23 that partition the first passage 21 through which the low-temperature compressed air A that is the first fluid flows and the second passage 22 through which the high-temperature exhaust gas E that is the second fluid flows. It is arranged in parallel at intervals of. The heat transfer plate 23 extends parallel to the axis of the core 19, that is, the axis of the casing 18. As a result, the first passages 21 and the second passages 22 are alternately arranged with the heat transfer plate 23 interposed therebetween.

As described above, the heat exchanger 3 is constructed by housing the core 19 having a hexagonal cross section inside the casing 18 having a circular cross section capable of withstanding the pressure of the compressed air A discharged from the compressor 4. Since it is configured, as shown in FIG. 5, the space S formed between the casing 18 and the core 19 becomes small,
The heat exchanger 3 can be downsized accordingly. Further, since the ratio of the cross-sectional area of the core 19 to the cross-sectional area of the casing 18 is higher than that in the conventional example, the heat exchange efficiency is improved accordingly. In addition, each core division body 19 has a flat shape,
That is, since a plurality of straight plate-shaped heat transfer plates 23 are arranged, the manufacturing is easy.

As shown in FIG. 2, a first inlet port 24 for allowing compressed air A to flow into the first passage 21 is provided on the side surface of the rear portion of the core 19. Further, on the side surface of the front portion of the core 19, the outlet 2 for the compressed air A passing through the first passage 21 is provided.
5 are provided. FIG. 3A shows a cross-sectional view of the first passage 21 cut parallel to the plate surface of the heat transfer plate 23. The first passage 21 is divided into a plurality of passage portions by a plurality of partition plates 21a parallel to the longitudinal direction of the passage.
The front and rear ends of the first passage 21 are closed by blind plates 21b. FIG. 3B is a cross-sectional view of the second passage 22 cut parallel to the plate surface of the heat transfer plate 23. The second passage 22 is also divided into a plurality of passage portions by a plurality of partition plates 22a parallel to the longitudinal direction of the passage.

As shown in FIG. 1, between the core 19 and the casing 18, compressed air A is passed from the front of the core 19 to the side of the core 19, that is, to the outside of the side surface thereof. An introduction path 26 that is introduced into the inflow port 24 is formed. As a result, the low temperature compressed air A passing through the introduction path 26 comes into contact with the casing 18, and it is possible to suppress the temperature of the casing 18 from increasing. The housing 13 of the gas turbine 1 and the casing 18 of the heat exchanger 3 are connected to each other by the connecting portion 1
The second inlet 27 is formed on the front surface of the heat exchanger, which is connected to the connecting portion 14, and allows the compressed air A to flow into the introduction passage 26. The housing 13
And a ring-shaped combustor 7 arranged radially outward of the turbine 4, a compressed air passage 15 for guiding the compressed air A discharged from the compressor 4 to the second inlet 27 is formed. There is.

Further, on the front surface of the heat exchanger 3, the second
A combustor outlet 28 for guiding the compressed air A from the outlet 25 of the heat exchanger 3 to the combustor 7 of the gas turbine 1 is formed on the inner peripheral side of the inlet 27, and the inner peripheral side of the outlet 28 is formed. To
The exhaust gas E discharged from the turbine 6 of the gas turbine 1 is used as a core 19
An exhaust gas inlet 29 is formed so as to flow into the second passage 22. An exhaust port 30 for discharging the exhaust gas E passing through the second passage 22 to the outside is formed on the rear surface of the heat exchanger 3.

In the gas turbine system thus constructed, the heat exchanger 3 is used to connect the compressed air A discharged from the compressor 4 of the gas turbine 1 and the exhaust gas E discharged from the turbine 6 of the gas turbine 1. Since the heat exchange is performed and the temperature of the compressed air A is guided to the combustor 7 of the gas turbine 1, the thermal efficiency of the gas turbine 1 is improved. Further, the miniaturization of the heat exchanger 3 also enables miniaturization of the gas turbine device. Further, the exhaust gas E flowing from the turbine to the heat exchanger 3 is
Since the gas flows from the housing 13 having a circular cross section in the gas turbine 1 into the casing 18 having a circular cross section in the heat exchanger 3, the flow of the exhaust gas E becomes uniform, and the heat exchange efficiency is improved accordingly.

In the above embodiment, the case where the heat exchanger 3 is used in the gas turbine device has been described, but the same effect can be obtained even if the heat exchanger 3 is used in another device.

[0022]

As described above, according to the heat exchanger of the present invention, the cross-sectional shape of the core accommodated inside the casing is hexagonal, so that the casing having a circular cross-sectional shape capable of ensuring pressure resistance. The useless space generated between the core and the core is reduced, and the heat exchanger having a small size and high heat exchange efficiency can be obtained. Further, since each core divided body is configured by disposing a plurality of flat heat transfer plates, it is easy to manufacture.

Further, according to the gas turbine apparatus of the present invention, heat exchange is performed by the heat exchanger between the air discharged from the compressor of the gas turbine and the exhaust gas discharged from the turbine of the gas turbine. Since the converted air is guided to the combustor of the gas turbine, the thermal efficiency of the gas turbine is improved. Further, the miniaturization of the heat exchanger also enables miniaturization of the gas turbine device.

[Brief description of drawings]

FIG. 1 is a vertical cross-sectional view of a gas turbine device using a heat exchanger according to an embodiment of the present invention.

FIG. 2 is a perspective view showing a core of the heat exchanger.

FIG. 3A is a sectional view of a first passage in the core,
(B) is a cross-sectional view of a second passage in the core.

FIG. 4 is an exploded front view showing a state in which the core is divided into three core divided bodies.

FIG. 5 is a front sectional view showing a schematic configuration of the heat exchanger.

FIG. 6 is a perspective view of a core in a conventional heat exchanger.

FIG. 7 is a front sectional view showing a schematic configuration of the heat exchanger.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Gas turbine, 3 ... Heat exchanger, 4 ... Compressor, 6 ... Turbine, 7 ... Combustor, 8 ... Intake passage, 13 ... Housing, 18 ... Casing, 19 ... Core, 20 ... Core division body, 21 ... 1st passage, 22 ... 2nd passage, 23 ... Heat transfer plate, 24 ... 1st inflow port, 25 ... Outflow port, 26 ... Introduction path, 27 ... 2nd inflow port, 28 ... Combustor outlet, 29
... Exhaust gas inlet port, 30 ... Exhaust port, A ... Compressed air (first fluid), E ... Exhaust gas (second fluid), P1, P2 ... Hexagonal two sides

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Claims (3)

(57) [Claims] 1. A first casing is provided inside a casing having a circular cross section.
And a core for heat exchange between the second fluid and the second fluid is accommodated, and the core has a hexagonal cross section and has a parallelogram cross section including two adjacent sides of the hexagon. The core divided body is divided into three core divided bodies, and each of the core divided bodies has a plurality of flat heat transfer plates partitioning a first passage through which the first fluid flows and a second passage through which the second fluid flows, at predetermined intervals. Heat exchangers arranged in parallel at. 2. The first flow passage according to claim 1, wherein a low temperature first fluid is flown into the side surface of the rear portion of the core into the first passage.
An inflow port is provided on a front side surface of the core, and an outflow port of the first fluid passing through the first passage is provided, and the first fluid is introduced between the core and the casing from the front of the core to the core. An inlet passage is formed through the side surface of the core to the first inlet, and the second fluid flows into the second passage from the front surface of the core and is discharged from the rear surface of the core. 3. The heat exchanger according to claim 2, and a gas turbine connected to a front portion of the heat exchanger, wherein a compressor of the gas turbine is discharged to a front surface of the heat exchanger. A second inlet for allowing air to flow into the inlet passage, a combustor outlet for guiding air from the outlet to a combustor of the gas turbine, and exhaust gas leaving the turbine of the gas turbine for the second passage of the core. And an exhaust gas inlet for flowing into
A gas turbine device in which an exhaust port for discharging the exhaust gas passing through the second passage to the outside is formed on the rear surface of the heat exchanger.