JPH0416613B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention provides an intercooler between a plurality of compressors, and burns and heats gas containing oxygen from a downstream compressor in a combustion chamber to drive a turbine. The present invention relates to a gas turbine device connected to drive a gas turbine.

FIG. 1 is a system diagram of a gas turbine installation including a generator 1 of the prior art. A drive shaft 3 that transmits power from a turbine 2 is connected to the generator 1 . A plurality of compressors 4, 5, and 6 are coaxially connected to the drive shaft 3. Therefore, by driving the turbine 2, the compressors 4 to 6 and the generator 1 are driven. The compressor 4 sucks in oxygen-containing gas 11, adiabatically compresses it, and discharges it to the compressor 5. This compressed gas is further adiabatically compressed by compressors 5 and 6 and guided to regenerator 7 . Intercoolers 8 and 9 are interposed between the compressors 4 and 5 and between the compressors 5 and 6, respectively, in order to increase the compression efficiency of the compressors 5 and 6. In the intercoolers 8 and 9, for example, 20% of the electric power generated by the generator 1 is used to cool the gas discharged from the compressors 4 and 5. Therefore, power generation efficiency is inferior.

The compressed oxygen-containing gas led to the regenerator 7 is heated within the regenerator 7 by the exhaust heat of the gas discharged from the turbine 2, and is sent into the combustion chamber 10. A fuel gas 12 is introduced into the combustion chamber 10 at the same time as the aforementioned gases, and drives the combustion heating turbine 2 . This drives the generator 1 to generate electricity. High temperature exhaust gas 13 is discharged from the regenerator 7 to the outside. This exhaust heat of the exhaust gas 13 is not fully utilized.

An object of the present invention is to solve the technical problems of the prior art described above, to effectively utilize exhaust heat from a turbine, to prevent wasteful power consumption, and to thereby provide a gas turbine device with improved thermal efficiency. It is to provide.

The present invention includes a plurality of compressors 19, 20, 21 that compress combustion gas containing oxygen, and an intercooler that is interposed between each of these compressors 19, 20, 21 and cools the combustion air. 22,
23, a regenerator 27 for preheating the combustion gas from the final stage compressor 21 among the compressors 19, 20, and 21, and combustion chambers 24 to 2 for performing combustion using the combustion gas.
6 and turbines 16 to 18 to which gas from the combustion chambers 24 to 26 is supplied, respectively, and a plurality of serially connected multi-stage turbines; , 21 and turbines 16-1
8 and a generator 14 are connected to a drive shaft 15, and the exhaust gas discharged from the last stage gas turbine among the plurality of gas turbines is led to the regenerator 27 and is discharged from the last stage compressor 21. The combustion gas is preheated, the exhaust heat of the exhaust gas from the regenerator 27 is used as a heat source in the generator 31, and the heat medium cooled by the evaporator 33 is circulated to the intercoolers 22 and 23. This is a gas turbine apparatus characterized in that it includes an absorption chiller 30 that supplies gas.

Embodiments of the present invention will be described below with reference to the drawings. FIG. 2 is a system diagram showing the entire gas turbine device including the generator 14 according to one embodiment of the present invention. A drive shaft 15 that drives the generator 14 includes a plurality of coaxially arranged multi-stage turbines 16, 17, 18.
and a plurality of multistage compressors 19, 20, 21.
are connected. An intercooler is provided between the first-stage compressor 19 and the second-stage compressor 20 to cool the gas discharged from the first-stage compressor 19 in order to increase the compression efficiency of the second-stage compressor 20. 22 is interposed. An intercooler 23 similar to the intercooler 22 is interposed between the second stage compressor 20 and the final stage compressor 21.

A first combustion chamber 24 is provided between the final stage compressor 21 and the first stage turbine 16. A second combustion chamber 25 and a third combustion chamber 26 are provided between the first stage turbine 16 and the second stage turbine 17 and between the second stage turbine 17 and the final stage turbine 18, respectively. A regenerator 27 is interposed between the final stage compressor 21 and the first combustion chamber 24 to preheat the gas that is brought into a high pressure state by the compressor 21 and discharged.

This regenerator 27 is connected with an exhaust gas pipe 28 through which exhaust gas containing high-temperature exhaust heat flows from the final stage turbine 18 . With this, the regenerator 2
The high-pressure gas supplied to the first combustion chamber 24 in the combustion chamber 7 is preheated to a high temperature by exchanging heat with the exhaust gas. The exhaust gas that has passed through the regenerator 27 is
The exhaust gas is supplied to the generator 31 of the absorption refrigerator 30 through the exhaust gas supply pipe 29 . The absorption refrigerator 30 includes the generator 31, a condenser 32, an evaporator 33,
It includes an absorber 34, a cooling pipe line 36 including a cooling tower 35 for cooling the condenser 32 and the absorber 34, and a transport pipe 37 for transporting the brine cooled by the evaporator 33.

Since the exhaust gas flowing through the exhaust gas supply pipe 29 is in a high temperature state of, for example, 400 to 500°C,
1, the absorbent solution is heated and the refrigerant absorbed in the absorbent solution is evaporated. This evaporated refrigerant is
It is sent to the condenser 32 where it is condensed, and then returned to the evaporator 33 via the valve 38. In the evaporator 33, the refrigerant is evaporated and the evaporated refrigerant is absorbed into an absorbent solution in the absorber 34. At this time, in the evaporator 33, the brine transported by the transport pipe 37 is cooled. This transport pipe 37 is connected to the intercooler 2
Connected to 2 and 23. As a result, the intercoolers 22 and 23 are supplied with cooled brine. The absorbent solution in which the refrigerant has been absorbed in the absorber 34 is pumped to the generator 31 via the heat exchanger 39 . The absorbent solution from which the refrigerant absorbed in the generator 31 has been removed is transferred to the absorber 34 via a heat exchanger 39.
will be returned to.

In driving the generator 14 according to the present invention, each turbine 16 is operated by a starting means (not shown).
~18 is rotated at a constant rate. Accordingly, each compressor 19 to 21 connected to the drive shaft 15 is driven. As a result, the first-stage compressor 19 sucks the oxygen-containing gas 40 and adiabatically compresses it. The pressure-enhanced gas 40 discharged from the compressor 19 is cooled by heat exchange with the brine in the intercooler 22, and is drawn into the second stage compressor 20 where it is adiabatically compressed. At this time, the gas 40 is
Since the air is cooled to about the same temperature as when it is sucked into the first-stage compressor 19, the amount of work of adiabatic compression performed by the second-stage compressor 20 is prevented from increasing, and therefore the compression Efficiency is not reduced. The gas discharged from the second stage compressor 20 is cooled by the brine in the intercooler 23, sucked into the final stage compressor 21, and further compressed to a high pressure to the regenerator 27. is discharged. In this way, the brine cooled by the evaporator 33 of the absorption chiller 30 is supplied to the intercoolers 22 and 23 via the transport pipe 37,
Heat exchange takes place between this brine and the gas 40.

In the regenerator 27, exhaust gas flows from the final stage turbine 18 via an exhaust gas pipe 28. Since this exhaust gas has a high temperature, the gas 40 is preheated and flows into the first combustion chamber 24 . The gas 40 and fuel gas 41 are also introduced into the first combustion chamber 24 . As a result, the fuel gas 41 is combusted and heated in the first combustion chamber 24 and is expanded while being sent to the first-stage turbine 16 to rotationally drive the first-stage turbine 16 . Combustion gas including the gas 40 exhausted from the first stage turbine 16 is sent into the second combustion chamber 25 together with the fuel gas 41. In the second combustion chamber 25, the fuel gas 41 is combusted and heated and expands to the second stage turbine 1.
7 and rotationally drives the second stage turbine 17. In the third combustion chamber 26, combustion gas including the gas 40 exhausted from the second-stage turbine 17 is fed together with the fuel gas 41, and the combustion-heated combustion gas expands to the final-stage turbine 18. The final stage turbine 18
drive the rotation. In this way, each turbine 16~
18 is rotationally driven, the generator 14 and each compressor 19 to 21 are driven via the drive shaft 15. As a result, the generator 14 generates electricity.

The exhaust gas exhausted from the final stage turbine 18 flows through the exhaust gas supply pipe 29 via the regenerator 27 as described above, and is passed through the generator 31 of the absorption refrigerator 30.
given to. In this way, the heat source for operating the absorption refrigerator 30 can mainly utilize the exhaust heat of the exhaust gas discharged from the regenerator 27.
Therefore, the brine cooled by the evaporator 33 of the absorption chiller 30 is supplied to the intercoolers 22, 23 via the transport pipe 37, and thereby the brine is supplied from the compressors 19, 20. The discharged gas 40 can be cooled. Therefore, as described in the prior art, about 20% of the power generated by the generator 1 is consumed and the intercooler 22, 2
3 is avoided according to the invention. Therefore, the power generation efficiency of the generator 14 is improved.

In the embodiment described above, the combustion chamber 2 performs combustion using combustion gas containing oxygen from the regenerator 27.
4 and the turbine 16 constitute one gas turbine. Furthermore, the combustion chamber 25 and the turbine 17 constitute another turbine. Combustion chamber 26 and turbine 18 constitute yet another gas turbine. These three gas turbines are connected in series to form multiple stages.

Exhaust gas discharged from the final stage gas turbine is guided to the regenerator 27 via a pipe 28, thereby preheating the combustion gas from the final stage compressor 21. In the absorption chiller 30, the exhaust heat of the exhaust gas from the regenerator 27 is used as a heat source in the generator 31, and the heat medium cooled by the evaporator 33 is circulated and supplied to the intercoolers 22 and 23. .

Although in the embodiments described above three compressors 19-21 were provided, in further embodiments of the invention two or more compressors are provided,
Intercoolers may be provided depending on the number of compressors.

As described above, according to the present invention, the absorption chiller is operated using the exhaust heat from the gas turbine to cool the intercooler, so the exhaust heat from the gas turbine is effectively utilized. In addition, as described in connection with FIG. 1 above, since the power from the generator 14 is not consumed by the intercoolers 22 and 23, wasteful power consumption is prevented. , thus improving thermal efficiency.

Moreover, in the present invention, the compressors 19, 20, 21 are provided in multiple stages, and the compressors 19, 20, 21 are provided in multiple stages.
Intercoolers 22 and 23 are interposed between the combustion chambers 24 to 26 and the turbine 1.
A plurality of stages of gas turbines are provided in which each stage is configured by combining the gas turbines 6 to 18. In this way, it is possible to increase the amount of work that can be extracted as motive power for the generator 14.

Furthermore, according to the present invention, using the regenerator 27,
The exhaust heat of the exhaust gas from the final stage gas turbine is used to preheat the combustion gas, such as air, from the final stage compressor 21, and the exhaust heat of the exhaust gas from the regenerator 27 is used to perform absorption refrigeration. Since the absorption chiller 30 is operated, there is no problem that too much cold energy is left over for cooling the intercoolers 22 and 23 obtained by the absorption chiller 30, and therefore thermal efficiency is improved. is planned.

If this regenerator 27 is not installed, the exhaust gas from the final stage gas turbine will flow through the pipe 2.
9, the exhaust gas is directly sent to the absorption chiller 30.
If the cold energy obtained by the absorption refrigerator 30 is used as a heat source, the cold energy obtained by the absorption refrigerator 30 will not be used completely in the intercoolers 22 and 23, and a large amount of cold energy will be left over, resulting in a decrease in thermal efficiency. In order to prevent such a decrease in thermal efficiency without using the regenerator 27, if the flow rate of fuel in the combustion chambers 24 to 26 is reduced to reduce the amount of combustion, the generator 14 There is a problem that the amount of work that can be taken out becomes smaller.

In the present invention, the regenerator 27 is used to preheat the combustion gas from the final stage compressor 21 by utilizing the exhaust heat of the final stage gas turbine. Since the exhaust heat of the exhaust gas is used, it is possible to generate appropriate cold heat to cool the combustion gas in the intercoolers 22 and 23, and there is no possibility that too much cold heat will be left over. Moreover, by increasing the power that can be extracted to drive the generator 14, the generator 1
It becomes possible to increase the power generation amount of 4 with high efficiency.

[Brief explanation of drawings]

FIG. 1 is a system diagram of a gas turbine system including a generator 1 according to the prior art, and FIG. 2 is a system diagram showing the entire gas turbine system including a power generator 14 according to an embodiment of the present invention. 14... Generator, 15... Drive shaft, 16-18
... Turbine, 19-21 ... Compressor, 22,2
3... Intercooler, 24-26... Combustion chamber, 27
... Regenerator, 28 ... Exhaust gas pipe, 29 ... Exhaust gas supply pipe, 30 ... Absorption refrigerator, 31 ... Generator, 33 ... Evaporator, 37 ... Transport pipe, 40 ...
Gas containing oxygen, 41...Fuel gas.

Claims (1)

[Claims] 1. A plurality of compressors 19, 20, and 21 that compress combustion gas containing oxygen, and a compressor that is interposed between each of these compressors 19, 20, and 21, and that cools the combustion air. intercooler 22,
23, a regenerator 27 for preheating the combustion gas from the final stage compressor 21 among the compressors 19, 20, and 21, and combustion chambers 24 to 2 for performing combustion using the combustion gas.
6 and turbines 16 to 18 to which gas from the combustion chambers 24 to 26 is supplied, respectively, a plurality of serially connected multi-stage gas turbines; a generator 14; 20, 21 and turbines 16-1
8 and a generator 14 are connected to a drive shaft 15, and the exhaust gas discharged from the last stage gas turbine among the plurality of gas turbines is led to the regenerator 27 and is discharged from the last stage compressor 21. The combustion gas is preheated, the exhaust heat of the exhaust gas from the regenerator 27 is used as a heat source in the generator 31, and the heat medium cooled by the evaporator 33 is circulated to the intercoolers 22 and 23. A gas turbine apparatus characterized in that it includes an absorption chiller 30 that supplies the gas.