초록 ▼

A gas turbine unit as well as a method for operating a gas turbine with high-pressure turbine and a low-pressure turbine unit are disclosed. A very quick and at the same time easily controllable augmentation or reduction of the shaft power of the gas turbine unit can be achieved by providing at leas

A gas turbine unit as well as a method for operating a gas turbine with high-pressure turbine and a low-pressure turbine unit are disclosed. A very quick and at the same time easily controllable augmentation or reduction of the shaft power of the gas turbine unit can be achieved by providing at least one liquid droplet injection device on the upstream side of said compressor for injecting liquid into the stream of intake air in order to increase the shaft power generated by the gas turbine unit. The amount of water mass flow corresponding to the desired increase or decrease of shaft power output of the gas turbine unit is added or reduced in the form of liquid droplets in a substantially stepless manner and immediately within a time interval that is determined by the design characteristics of the liquid droplet injection device.

대표청구항 ▼

What is claimed is: 1. A process for changing shaft power production from a gas turbine unit that comprises a compressor for compressing a stream of intake air supplied thereto and discharging compressed air, a high-pressure combustion chamber in which fuel is combusted with the compressed air disc

What is claimed is: 1. A process for changing shaft power production from a gas turbine unit that comprises a compressor for compressing a stream of intake air supplied thereto and discharging compressed air, a high-pressure combustion chamber in which fuel is combusted with the compressed air discharged from said compressor, a high-pressure turbine driven by hot combustion air discharged from said high-pressure combustion chamber, a low-pressure combustion chamber in which fuel is combusted with the expanded combustion air discharged from said high-pressure turbine, and a low-pressure turbine driven by the hot combustion air discharged from said low-pressure combustion chamber, the process comprising: operating said compressor with a pressure ratio larger than 15 bar; injecting liquid droplets into the stream of intake air using at least one liquid droplet injection device disposed on an upstream side of said compressor to increase shaft power generated by the gas turbine unit; controlling the at least one liquid droplet injection device so that responsive to a desired increase of shaft power output, the at least one liquid droplet injection device delivers the liquid droplets to reach a discrete rate of mass flow within 60 seconds; and adjusting the fuel mass flow with a fuel control valve in order to maintain firing temperatures of the gas turbine unit, wherein the at least one liquid droplet injection device is operable with an on/off-control signal, and wherein the fuel control valve is controllable as a function of liquid droplet injection using a single feed forward signal synchronized to the on/off-control signal. 2. The process of claim 1, wherein liquid mass flow is substantially injected across the entire cross-section of an intake air guide. 3. The process of claim 1, further comprising cooling components of the gas turbine unit with a cooling system using at least partially compressed air discharged from the compressor, wherein the cooling system comprises a cooling unit that is controlled depending on quality with respect to temperature and pressure of air cooled thereby. 4. The process of claim 1, wherein between 0.5 mass % and 5 mass % of liquid are injected into the intake air to achieve an increase of shaft power of the gas turbine unit of up to 10%. 5. The process of claim 1, wherein the amount of liquid injected into the intake air is decreased by between 0.5 mass % and 5 mass % of liquid to achieve a reduction of shaft power of the gas turbine unit of up to 10%. 6. The process of claim 1, wherein between 1 mass % and 3 mass % of liquid are injected into the intake air to achieve an increase of shaft power of the gas turbine unit of up to 10%. 7. The process of claim 1, wherein the amount of liquid injected into the intake air is decreased by between 1 mass % and 3 mass % of liquid to achieve a reduction of shaft power of the gas turbine unit of up to 10%. 8. The process of claim 1, wherein water is injected at pressure as high as 250 bar water pressure, and the pressure is achieved within 1 second and 60 seconds. 9. The process of claim 8, wherein the pressure is achieved within 10 seconds and 30 seconds. 10. The process of claim 1, wherein water is injected at pressure between 100 bar and 180 bar water pressure, and the pressure is achieved within 1 second and 60 seconds. 11. The process of claim 10, wherein the pressure is achieved within 10 seconds and 30 seconds. 12. The process of claim 1, wherein water is injected at pressure about 140 bar water pressure, and the pressure is achieved within 1 second and 60 seconds. 13. The process of claim 12, wherein the pressure is achieved within 10 seconds and 30 seconds. 14. The process of claim 1, wherein the power output of the gas turbine unit available on a generator coupled to the gas turbine unit is rapidly increased or decreased using an addition or reduction of liquid mass flow. 15. The process of claim 14, wherein the rapid increase or decrease is generated in response to a fast increase or decrease in power demand of an electricity grid coupled to the gas turbine unit, and by an addition or reduction of water a surge margin of the compressor is increased or decreased by cooling a compressor blade section. 16. The process of claim 15, wherein the rapid increase or decrease is generated in response to a drop or rise of frequency of the electricity grid. 17. The process of claim 16, wherein the drop or rise of the frequency of the electricity grid results in a reduction or augmentation of shaft speed of the gas turbine unit. 18. The process of claim 1, wherein the liquid droplets are injected after a delay of between 15 minutes and 45 minutes after starting up the gas turbine to full load. 19. The process of claim 18, wherein the liquid droplets are injected after a delay of about 30 minutes after starting up the gas turbine to full load. 20. The process of claim 18, wherein additional cooling systems are switched on after a delay of between 15 minutes and 45 minutes after starting up the gas turbine to full load. 21. The process of claim 1, wherein the single feed forward signal and the on/off-control signal are synchronized but displaced relative to each other sufficient to account for hysteresis-effects of the gas turbine unit.