GAS TURBINE SYSTEM

Abstract

A pressure vessel bypass valve forms a bypass system for enabling a part of the air compressed by a compressor to directly flow into a combustor while preventing the part of the air from flowing through a humidification tower and a recuperator. A turbine bypass valve forms another bypass system for enabling a part of a humidified air to be discharged to an exhaust duct after a heat exchange between the humidified air and a turbine exhaust gas is performed in the recuperator while preventing the part of the humidified air from flowing through a turbine. A turbine control system controls the bypass valves to be opened and closed in accordance with increase and decrease of the load.

Description

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

FIG. 1 is a view showing a gas turbine system as an embodiment of the invention.

FIG. 2 is a diagram showing a condition adjusted by a compressor inlet guide vane in the gas turbine system of the embodiment of the invention.

FIG. 3 is a diagram showing a relationship between a time proceeding and a generator output obtainable during a change from a partial load operation to a normal load operation in the gas turbine system of the embodiment of the invention.

FIG. 4 is a diagram showing a relationship between a time proceeding and a generator output obtainable during a change from the normal load operation to the partial load operation in the gas turbine system of the embodiment of the invention.

DETAILED DESCRIPTION OF THE INVENTION

Hereafter, with making reference to FIGS. 1-4, a structure and operation of a gas turbine system as an embodiment of the invention is described.

At first, with making reference to FIG. 1, a system structure of a high humidity gas turbine electric generator plant to which the gas turbine system as the embodiment of the invention is applicable, is described.

FIG. 1 is a control system view showing the gas turbine system as the embodiment of the invention.

An air to be used in a combustion for a gas turbine 1 is adjusted by a compressor inlet guide vane 18, subsequently its humidity is increased by an intake air atomizer 10, subsequently the air is compressed by a compressor, subsequently a heat exchange for the air is performed in an air cooler 7, subsequently its humidity is increased by a humidification tower 8, and subsequently the air is heated by a recuperator 11. A thermal energy source of the recuperator 11 is an exhaust gas supplied from the gas turbine 1. The thermal energy is absorbed by the air from the recuperator 11 to obtain the air of high temperature and high humidity for combustion.

The fuel whose flow rate is adjusted by a fuel regulating control valve 5 is combusted in a combustor 3 with the air of high humidity and high temperature for combustion. A combustion gas formed by the fuel and the air with the vapor drives the gas turbine 3, and subsequently discharged as an exhaust gas to an outside of the turbine through an economizer 12 and a gas duct 17. A thermal energy of the exhaust gas discharged to the outside of the turbine is collected by a recuperator 11 to heat the air for combustion.

The humidity included by the combustion exhaust gas is collected by a water recovery system 9. As a system for collecting the water, a water is sprayed in the gas duct 17 to condense the humidity in the gas so that the water drops to be collected. The exhaust gas is discharged into the atmosphere through a stack 16 after collecting the water.

A driving force generated by the gas turbine is transmitted to the compressor 2 and a generator 4 through a shaft 6. A part of the driving force is used to pressurize the air in the compressor. Further, the generator 4 converts the driving force to an electric power.

Incidentally, the water collected by the water recovery system 9 is stored by a water collecting tank and supplied by pumps 13 and 14 to the spray and the water recovery system 9 to be reused as a humidification water for the spray and a sprayed water for the water recovery system 9. The water discharged to the atmosphere through the stack 16 is recovered by a make-up water pump 15.

The gas turbine system as shown in FIG. 1 includes a pressure container bypass valve 19 for enabling a part of the air compressed by the compressor to flow directly to the combustor while preventing the part of the air flowing through the humidification tower 8 and the recuperator 11, a turbine bypass valve 20 for enabling a part of the humidified air to be discharged to an exhaust duct while preventing the part of the humidified air from flowing through the turbine 1 after the heat exchange between the humidified air and the turbine exhaust gas is performed in the recuperator 11, and a turbine control system 21 for controlling operations of the bypass valves 19 and 20 as described below.

With making reference to FIG. 2, a control of the compressor inlet guide vane to be used in a case where the load of the gas turbine system of the embodiment is decreased from the normal load operation, is described.

FIG. 2 is a control explanation view of the compressor inlet guide vane in the gas turbine system of the embodiment of the invention. In FIG. 2, an abscissa corresponds to an air pressure at an outlet of the gas turbine compressor, and an ordinate corresponds to a temperature of the exhaust gas of the gas turbine.

In FIG. 2, a solid line denotes an exhaust gas temperature control characteristic as a control function to be used for a rated load operation. A dot line denotes a compressor inlet guide vane control characteristic as a control function to be used for a partial load operation.

Point A in FIG. 2 is on the control function (solid line) to be used for the rated load operation, and the flow rate of the fuel is controlled at the point A during the rated load operation. When the operational condition changes from the point A to the partial load operation, at first, an opening degree of the compressor inlet guide vane 18 is kept at the same as the opening degree at the A point, and the fuel control valve 5 is throttled to decrease the load so that the operational condition moves to point B on the control function (dot line) for the partial load operation. In this case, since the fuel supply rate is decreased while the flow rate of the air is kept constant, a temperature of the exhaust gas decreases.

When the load is decreased further, the operational condition moves from the point B to a point C, and subsequently to point D. At the point D, the opening degree of the compressor inlet guide vane 18 is minimum, and when the load is further decreased from the point D, the fuel control valve 5 needs to be throttled further so that a setting value of the exhaust temperature decreases simply from the point D to a point E.

By changing the opening degree of the compressor inlet guide vane 18 to adjust the air flow rate as the exhaust temperature is controlled on the control characteristic shown by the dot line, the exhaust temperature is kept high during the partial load operation. Therefore, an heat exchange amount between the exhaust gas and the air for combustion in the recuperator is increased to decrease a fuel consumption in the combustor 3, so that a turbine efficiency is improved and during the partial load operation, an electric power generating efficiency obtainable when the compressor inlet guide vane control is used is improved by 0.5-1.0% in comparison with that obtainable when the compressor inlet guide vane control is not used.

As described above, when the compressor inlet guide vane control is used, an intake air flow rate of the compressor is throttled in the partial load operation. In the high humidity gas turbine system, since the air compressed by the compressor 2 flows into the combustor 3 through the air cooler 7, the humidification tower 8 and the recuperator 11, these pressure chambers acts as the buffers causing the delay in the air response when the air flow rate is increased in accordance with an increase of the load.

Therefore, in this embodiment, when the load increases, the turbine control system opens the pressure vessel bypass valve 19 to enable the part (about 10%) of the air controlled by the compressor inlet guide vane 18 and compressed by the compressor 2 to flow through the bypass valve 19 connecting an outlet of the compressor and an inlet of the combustor into the combustor 3 while being prevented from being humidified. A remainder part (about 90%) of the air flows through the air cooler 7, the humidification tower 8 and the recuperator 11 into the combustor so that a response of the air to an ordered load is delayed. But, the bypassing air causes temporarily an increase of the air flow rate to compensate the response delay of the air. Therefore, a deterioration in responsibility to the ordered load increase as caused by the delay in air flow rate increase is compensated.

The delay in air flow rate response occurs even when the load decreases. When the load decreases, since a thermal capacity of the recuperator 11 is significantly great, the temperature of the air flowing into the combustor 3 is restrained from decreasing to cause a delay in response to the load decrease.

Therefore, in the embodiment, when the load decreases, the turbine control system 21 opens the turbine bypass valve 20 to enable the part (about 10%) of the air flowing toward the combustor 3 from the recuperator 11 to be discharged through the opened turbine bypass valve 20 connecting the outlet of the recuperator and the exhaust duct so that a delay in temperature decrease of the air for combustion is compensated by decreasing temporarily the flow rate of the air flowing into the combustor 3.

With making reference to FIGS. 3 and 4, an operation and effect of the embodiment are described.

FIG. 3 is a time chart of an output power of the generator obtainable when the operational condition is changed from the partial load operation to the rated load operation in the gas turbine system of the embodiment. FIG. 4 is a time chart of the output power of the generator obtainable when the operational condition is changed from the rated load operation to the partial load operation in the gas turbine system of the embodiment.

With making reference to FIG. 3, the operation and effect of the bypass system connecting the outlet of the compressor and the inlet of the combustor to each other when the load increases, are described.

In FIG. 3, MWD denotes an ordered electric power to be generated. A thick solid line denotes the output power of the generator obtainable when the bypass system is used in the embodiment, and a dot line denotes the output power of the generator obtainable when the bypass system is not used in the embodiment.

In this embodiment, when the ordered load is increased, the pressure vessel bypass valve 19 is opened to enable the part (about 10%) of the air discharged from the compressor to bypass the pressure vessels to increase temporarily the flow rate of the air flowing into the combustor so that as shown by the thick solid line in FIG. 3, the response to the load is improved. When the load reaches the vicinity of a desired load, the bypass valve is closed to adjust the flow rate of the air to restrain an overshoot in response to that the load reaches the desired load and decrease a time period for reaching the rated load in comparison with a case where the bypass system is not used.

In FIG. 4, MWD denotes the ordered electric power to be generated. A thick solid line denotes the output power of the generator obtainable when the bypass system is used in the embodiment, and a dot line denotes the output power of the generator obtainable when the bypass system is not used in the embodiment.

In this embodiment, when the ordered load is decreased, the turbine bypass valve 20 is opened to enable the part (about 10%) of the air discharged from the compressor to be discharged to the exhaust duct to decrease temporarily the flow rate of the air flowing into the combustor so that the delay in response to the load caused by the delay in temperature decrease of the air in accordance with excessiveness in thermal capacity of the recuperator is improved, and a time period for reaching the partial load is decreased in comparison with a case where the bypass system is not used.

It should be further understood by those skilled in the art that although the foregoing description has been made on embodiments of the invention, the invention is not limited thereto and various changes and modifications may be made without departing from the spirit of the invention and the scope of the appended claims.

Claims

1. A gas turbine system comprising a compressor for compressing an air, a compressor inlet guide vane for adjusting a flow rate of the air taken into the compressor, a humidification tower for humidifying the air compressed by the compressor, a combustor for combusting a fuel with the air humidified by the humidification tower to generate a combustion gas, a turbine to be driven by the combustion gas, a recuperator for performing a heat exchange between an exhaust gas discharged from the turbine and the humidified air to be supplied from the humidification tower into the combustor, and a controller for controlling an opening degree of the compressor inlet guide vane in accordance with a load of the system to keep a temperature of the exhaust gas high during a partial load operation of the system, wherein the system further comprises an intake bypass system for introducing a part of the air compressed by the compressor directly to the combustor while preventing the part of the air compressed by the compressor from passing through the humidification tower and the recuperator.

2. The gas turbine system according to claim 1, wherein the system further comprises a discharge bypass system for introducing a part of the humidified air into an exhaust duct after the heat exchange between the exhaust gas and the humidified air is performed by the recuperator while preventing the part of the humidified air from passing through the turbine.

3. The gas turbine system according to claim 1, wherein the intake bypass system has a valve and an air flow rate controller for controlling an opening degree of the valve to adjust a flow rate of the part of the air to be introduced directly to the combustor through the intake bypass system.

4. A gas turbine system comprising a compressor for compressing an air, a compressor inlet guide vane for adjusting a flow rate of the air taken into the compressor, a humidification tower for humidifying the air compressed by the compressor, a combustor for combusting a fuel with the air humidified by the humidification tower to generate a combustion gas, a turbine to be driven by the combustion gas, a recuperator for performing a heat exchange between an exhaust gas discharged from the turbine and the humidified air to be supplied from the humidification tower into the combustor, and a controller for controlling an opening degree of the compressor inlet guide vane in accordance with a load of the system to keep a temperature of the exhaust gas high during a partial load operation of the system, wherein the system further comprises a discharge bypass system for introducing a part of the humidified air into an exhaust duct after the heat exchange between the exhaust gas and the humidified air is performed by the recuperator while preventing the part of the humidified air from passing through the turbine.

5. The gas turbine system according to claim 4, wherein the discharge bypass system includes a valve and an air flow rate controller for controlling an opening degree of the valve to adjust a flow rate of a remainder part of the humidified air to be introduced to the combustor.

6. A gas turbine system comprising a compressor for compressing an air, a compressor inlet guide vane for adjusting a flow rate of the air taken into the compressor, a humidification tower for humidifying the air compressed by the compressor, a combustor for combusting a fuel with the air humidified by the humidification tower to generate a combustion gas, a turbine to be driven by the combustion gas, a recuperator for performing a heat exchange between an exhaust gas discharged from the turbine and the humidified air to be supplied from the humidification tower into the combustor, and a controller for controlling an opening degree of the compressor inlet guide vane, wherein the system further comprises at least one of a first bypass path connected fluidly between the compressor and the humidification tower and connected fluidly to the combustor to bypass the humidification tower and the recuperator to enable a part of the air compressed by the compressor to flow to the combustor while the part of the air compressed by the compressor is prevented from passing through the humidification tower and the recuperator, and a second bypass path connected fluidly between the combustor and at least one of the recuperator and the humidification tower and connected fluidly between the turbine and the recuperator to bypass the combustor to enable a part of the humidified air to be mixed with the exhaust gas discharged from the turbine to the recuperator while the part of the humidified air after passing through the at least one of the recuperator and the humidification tower is prevented from passing through the combustor.

7. The gas turbine system according to claim 6, wherein the at least one of the first bypass path and the second bypass path has a valve for controlling a flow rate therethough.