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    • 专利摘要:
    gas turbine power complementation systems and heating systems and methods of producing and using them. the present invention relates to electrical energy systems, including generating the capacity of a gas turbine, where additional electrical energy is generated using a separately supplied system during periods of peak electricity demand.
    公开号:BR112015008722B1
    申请号:R112015008722-1
    申请日:2013-10-21
    公开日:2021-03-30
    发明作者:Robert J. Kraft
    申请人:Powerphase Llc；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    [0001] The invention generally relates to electric power systems, which include generating the capacity of a gas turbine and more specifically to energy storage which is useful for providing additional electricity during peak periods of energy demand and supply systems that keep the gas turbine and steam turbine warm and ready to run, thereby reducing start-up time. BACKGROUND OF THE INVENTION
    [0002] Currently, marginal energy is produced mainly in the gas turbine, either in a single cycle or combined cycle configuration. As a result of the load demand profile, gas turbine based systems are accelerated during periods of high demand and delayed or shut down during periods of low demand. This cycle is typically triggered by the Network operator under a program called active network control or AGC. Unfortunately, due to the fact that industrial gas turbines, which represent the majority of the installed base, are designated primarily for base load operation, when they are turned on, a severe penalty is associated with the maintenance cost of that particular unit. . For example, a gas turbine that operates at base load could be serviced once every three years or 24,000 hours at a cost in the range of $ 2-3 million. That same cost could be incurred in a year for a plant that is forced to switch on and off every day.
    [0003] Currently, these gas turbine plants can reject approximately 50% of their nominal capacity. They do this by closing the compressor intake guide blades, which reduces the air flow to the gas turbine, also by decreasing the fuel flow as a constant air-to-fuel ratio is desired in the combustion process. . Keeping compressor operation and emissions safe, typically limits the level of rejection that can be practically achieved. The lower operating limit of the safe compressor is improved in today's gas turbines by introducing hot air into the gas turbine inlet, typically from an intermediate stage bleed extraction from the compressor. Sometimes, this hot air is also introduced at the entrance to prevent freezing. In any case, when this is done, the work that is done in the air by the compressor is sacrificed in the process for the benefit of being able to safely operate the compressor up to a lower flow, thus increasing the rejection capacity. This has an additional negative impact on the effectiveness of the system as the work carried out on the air that is exhausted is lost. In addition, the combustion system also has a limit for the system.
    [0004] The combustion system usually limits the amount that the system can reject because the less fuel is added, the flame temperature decreases, increasing the amount of CO emissions that is produced. The relationship between the flame temperature and CO emissions is exponential with temperature reduction, consequently, as the gas turbine system gets close to the limit, CO emissions rise at a peak, so a healthy margin is maintained that limit. This feature limits the entire gas turbine system to approximately 50% rejection capacity or, for a 100 MW gas turbine, the minimum power that can be achieved is around 50% or 50 MW. As the mass flow of the gas turbine is rejected, the efficiency of the compressor and the turbine also decreases, causing an increase in the heat rate of the machine. Some operators are facing this situation every day and, as a result, as the load demand falls, the gas turbine plants reach their lower operating limit and have to shut down the machines, which costs them a tremendous amount. maintenance cost penalty.
    [0005] Another characteristic of a typical gas turbine is that as the ambient temperature increases, the power output drops proportionally, due to the linear effect of the reduced density as the air temperature decreases. The power output can be low by more than 10% of the number plate during hot days, typically when peak gas turbines must, at most, release power.
    [0006] Another characteristic of typical gas turbines is that the ark is compressed and heated in the compressor section of the gas turbine and is channeled to different portions of the turbine section of the gas turbine where it is used to cool various components. This air is typically called cooling and turbine leakage air (hereinafter "TCLA") a term that is well known in the art with respect to gas turbines. Even though it is heated from the compression process, TCLA air is still significantly cooler than the turbine temperatures and thus is efficient in cooling these components in the turbine downstream of the compressor. Typically 10% to 15% of the air entering the compressor inlet bypasses the combustion and is used for this process. Thus, the TCLA is a significant penalty for the performance of the gas turbine system.
    [0007] Another feature of gas turbines is that it takes 20 to 30 minutes to start elastipically due to thermal loading considerations and the heat recovery steam generator (HRSG) at the combined cycle plant can take an hour or more . This is significant because combined cycle plants are being used more often to balance the intermittency of renewable energy that fluctuates significantly in minutes. SUMMARY OF THE INVENTION
    [0008] The present invention provides several options, depending on the specific plant needs, to improve the upper limit of the gas turbine power output, thereby increasing the regulation capacity and aptitude of a new gas turbine system or an existing one .
    [0009] One aspect of the present invention relates to methods and systems that allow gas turbine systems to more efficiently deliver maximum additional power during periods of peak demand because a separately powered engine is used to drive the system, which eliminates significant parasitic loads typically associated with compressed air injection systems.
    [00010] Another aspect of the present invention relates to an exhaust recirculation system that eliminates the point source of emissions from the separately supplied engine.
    [00011] Another aspect of the present invention relates to improvements in efficiency using the wasted heat associated with the exhaust gas recirculation system.
    [00012] Another aspect of the present invention relates to a fuel-cooled intake cooler system where the wasted heat from the separately supplied engine increases the power output of the steam turbine, thereby maintaining or improving the efficiency of a cycle plant Combined.
    [00013] Another aspect of the present invention relates to an alternative use of a power stimulus system while the power plant is not working where the compressed air is forced through the gas turbine and the exhaust of the separately supplied engine is forced through of the heat recovery steam generator ("HRSG") to keep the entire gas turbine and steam turbine warm, which reduces start-up time.
    [00014] Another aspect of the present invention relates to an alternative use of the power stimulus system while the power plant is not working where the compressed air is forced through the gas turbine and the HRSG to maintain the entire gas turbine and the steam turbine hot, which reduces the start time.
    [00015] Another aspect of the present invention relates to an air injection system with power stimulus that displaces the cooling air normally taken from the intermediate or full stage of compressor discharge of the gas turbine while, at the same time, the exhaust from the separately supplied engine is used in the HRSG to produce additional power. The alternatively supplied cooling air can be similar in temperature and pressure to the moving air, or colder (which results in a reduction in cooling air requirements and improved gas turbine efficiency ("GT")).
    [00016] Another aspect of the present invention relates to the use of relatively cold first stage nozzle cooling air which leads to a reduction in air requirements which translates to improved efficiency.
    [00017] Another aspect of the present invention relates to a power stimulation system that releases relatively cold cooling air and during periods when the combined cycle plant is not working, releasing hot compressed air to keep the turbine section warm while , at the same time, uses the engine exhaust separately supplied in a packaged boiler to have steam passed through the HRSG and the steam turbine to minimize the start time of the complete combined cycle ("CC") plant.
    [00018] Another aspect of the present invention relates to using a separately fueled engine to drive hot compressed air into the combustion exhaust flush while, at the same time, using excess heat of lower quality (ie, lower temperature) engine exhaust separately supplied to preheat GT fuel, thereby improving GT efficiency.
    [00019] One embodiment of the invention relates to a system comprising a complementary compressor, at least one compressor, at least one electric generator, at least one turbine (at least one turbine connected to at least one generator and at least one compressor) and a combustion housing (which is the exhaust manifold for the compressor).
    [00020] Another advantage of another preferred modality is the ability to increase the power output of the gas turbine system quickly with complementary hot compressed air that is released by the separately supplied engine.
    [00021] Another advantage of the preferred modality is the recirculation of some amount or all the exhaust gas from the engine separately supplied, thus minimizing or eliminating emissions from a second source of emissions in the power plant.
    [00022] Another advantage of the preferred modality is the recirculation of some amount or all the exhaust gas from the separately supplied engine, thus minimizing or eliminating the cost associated with cleaning emissions when using the GT emission control system. existing.
    [00023] An advantage of other preferred modalities is the ability to increase the power output while, at the same time, improving the efficiency of the overall system.
    [00024] Another advantage of the modalities of the present invention is the ability to improve the power output and the efficiency of a conventional cooling system.
    [00025] Another advantage of the modalities of the present invention is the ability to keep the gas turbine and steam turbine components warm while the plant is shut down, thereby reducing the required start-up time.
    [00026] Another advantage of some embodiments of the present invention is the ability to improve the efficiency of the integrated power stimulus system by reducing the heat that is otherwise wasted associated with GT's cooled air circuits.
    [00027] Another advantage of some modalities of the present invention is the ability to release cooler cooling air to externally supply the turbine components, resulting in a reduction in the TCLA required for the GT and an improvement in the efficiency of the fuel stimulation system. integrated power.
    [00028] Another advantage of some embodiments of the present invention is the ability to release cooler cooling air to supply the turbine components internally via preferential discharge or direct cooling air collector resulting in a reduction in the required TCLA for GT and an improvement in the efficiency of the integrated power stimulus system.
    [00029] Other advantages, features and characteristics of the present invention, as well as the methods of operation and the functions of the related elements of the structure and the combination of parts will become more evident in consideration of the following detailed description and in the appended claims with reference to the drawings follow-up, all of which form a part of that specification. BRIEF DESCRIPTION OF THE DRAWINGS
    [00030] Figure 1 is a schematic drawing of a modality of the present invention that has a complementary energy system with a recovered fueled engine, with exhaust gas recirculation, activating the complementary compressor where some or all of the exhaust from the recovered engine is released to the GT for additional combustion.
    [00031] Figure 2 is a schematic drawing of a modality of the present invention that has a complementary energy system with a recovered fueled engine, with exhaust gas recirculation and fuel heating, activating the complementary compressor where some or all of the exhaust from the recovered engine is released to the GT for further combustion and the waste heat of inferior quality is additionally used to heat the fuel of the GT.
    [00032] Figure 3 is a schematic drawing of a modality of the present invention that incorporates an input cooling system with complementary energy increase that uses a separately powered engine driven cooler, where the separately powered engine exhaust is integrated with the exhaust. of GT.
    [00033] Figure 4 is a schematic drawing of a modality of the present invention with a heat recovery steam generator heating system that uses the exhaust from the fueled engine, where both the compressed air and the exhaust from the fueled engine is used. to keep the single or combined cycle plant warm while the plant is not running.
    [00034] Figure 5 is a schematic drawing of a modality of the present invention that incorporates a quick start system that uses compressed air, where a mixture of compressed air and compressed exhaust from the fueled engine is used to keep the plant simple or cycle. combined heating while the plant is not running.
    [00035] Figure 6 is a schematic drawing of a modality of the present invention with complementation of cold air for turbine, where cold cooling air is supplied to the high pressure cooling circuit of the gas turbine by the complementary compressor and the engine. fueled and the exhaust from the fueled engine is added to the exhaust from the gas turbine.
    [00036] Figure 7 is a schematic drawing of a modality of the present invention with complementation of cold air cooled in a downstream turbine nozzle, where the cold cooling air is supplied by the complementary compressor and the engine supplied to the cooling circuit of intermediate pressure and the exhaust of the fueled engine is added to the exhaust of the GT.
    [00037] Figure 8 is a schematic drawing of a modality of the present invention with first complementation of cooling air cooled in a turbine nozzle, where the cold cooling air is supplied by the complementary compressor and the engine supplied to the cooling circuit of first stage nozzle of the gas turbine and the exhaust of the fueled engine is added to the exhaust of the GT.
    [00038] Figure 9 is a schematic drawing of a modality of the present invention that begins quickly with injection of air and steam, where the cold cooling air is supplied by the complementary compressor and the motor supplied to the nozzle cooling circuit. first stage, for the high pressure cooling circuit or the intermediate pressure cooling circuit of the gas turbine and the exhaust from the fueled engine is used to produce steam for the increase of energy when the gas turbine is operating and the air Compressed and steam are used to keep the plant warm when the gas turbine is not operational.
    [00039] Figure 10 is a schematic drawing of a modality of the present invention with fuel heating, which has a complementary energy system with a recovered fueled engine that drives the complementary compressor, where some or all of the fueled engine exhaust is used to heat the gas turbine fuel.
    [00040] Figure 11 shows a gas turbine cycle of the type applicable to the present invention in an enthalpy-entropy diagram temperature entropy for SW501FD2 with injection of 551 bs / s (+ 5.5%).
    [00041] Figure 12 shows a comparison of the mass work in pounds required to pump air from atmospheric conditions to high pressure for the SW501FD2 compressor compared to an inter-cooled compressor process. DETAILED DESCRIPTION OF THE INVENTION
    [00042] One aspect of the invention relates to methods and systems that allow gas turbine systems to operate more efficiently under various conditions or modes of operation. In systems such as that discussed in US Patent No. 6,305,158 to Nakhamkin (the "patent 158"), there are three basic modes of operation defined, a normal mode, charge mode and an air injection mode, but it is limited by need for an electrical generator that has the ability to release energy "that exceeds the total rated energy" that the gas turbine system can release. The fact that this patent has been issued for more than 10 years and there are still unknown applications of it at the time of rapidly rising energy costs is proof that it is not addressing market requirements.
    [00043] First, it is very expensive to replace or modernize the electric generator so that it can deliver power "that exceeds the total rated power" that the gas turbine system can currently release.
    [00044] Another disadvantage is that the system cannot be implemented in a combined cycle plant without a significant negative impact on fuel consumption. Most of the outlined implementations use a stove to heat the air in single-cycle operation, which alleviates the issue of increased fuel consumption, however, adds significant cost and complexity. The proposed invention outlined below addresses both the deficiency and the cost as well as that related to the performance of the systems disclosed in the 158 patent.
    [00045] One embodiment of the invention relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine, fluidly connected to each other; (b) pressurize the ambient air using a complementary compressor driven by a fueled motor, whose operation is independent of the electrical network; and (c) injecting the pressurized air into the combustion shell.
    [00046] According to a preferred embodiment, the hot exhaust from the separately supplied engine is used to preheat the fuel that is supplied to the combustion.
    [00047] Preferably, the fueled engine includes a jacket cooling system and the heat removed from the jacket cooling system is used to preheat the fuel that is supplied to the combustion.
    [00048] According to another preferred embodiment, all or a portion of the exhaust from the fueled engine is diverted to provide heat input to a heat recovery steam generator when the gas turbine is not operational.
    [00049] According to another preferred embodiment, the pressurized air produced by the compression process driven by a fueled engine is diverted to provide the heat input for a heat recovery steam generator and / or the turbine when the gas turbine is not operational.
    [00050] Another embodiment of the invention relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion engine and a turbine, fluidly connected to each other; (b) pressurize the ambient air and a portion of the exhaust gases from a fueled engine, using a complementary compressor driven by the fueled engine; and (c) injecting the pressurized air and the exhaust mixture into the combustion casing, in which the operation of the fueled engine is independent of the electrical network.
    [00051] According to a preferred embodiment, the hot exhaust from the separately supplied engine is used to preheat the fuel that is fed to the combustion. Preferably, the fueled engine includes a jacket cooling system and the heat removed from the jacket cooling system is used to preheat the fuel that is supplied to the combustor.
    [00052] According to another preferred embodiment, all or a portion of the exhaust from the fueled engine is diverted to provide heat input for a heat recovery steam generator and / or the turbine when the gas turbine is not operational.
    [00053] According to another preferred embodiment, the pressurized air produced by the powered engine driven compression process is diverted to provide heat input to a heat recovery steam generator and / or the turbine when the gas turbine is not is operational.
    [00054] Yet another embodiment of the invention relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion engine and a turbine, fluidly connected to each other; (b) pressurize the ambient air and all exhaust gases from a fueled engine, using a complementary compressor driven by the fueled engine; and (c) injecting the pressurized air and the exhaust mixture into the combustion shell, in which the operation of the fueled engine is independent of the electrical network.
    [00055] According to a preferred embodiment, the hot exhaust from the separately supplied engine is used to preheat the fuel that is supplied to the combustion. Preferably, the fueled engine includes a jacket cooling system and the heat removed from the jacket cooling system is used to preheat the fuel that is supplied to the combustor.
    [00056] According to another preferred embodiment, all or a portion of the exhaust from the fueled engine is diverted to provide heat input for a heat recovery steam generator and / or the turbine when the gas turbine is not operational .
    [00057] According to another preferred embodiment, the pressurized air produced by the powered engine driven compression process is diverted to provide heat input to a heat recovery steam generator and / or the turbine when the gas turbine is not operational.
    [00058] Yet another embodiment of the invention relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion enclosure, a combustor and a turbine, fluidly connected to each other; (b) pressurize only the exhaust gases from a fueled engine, using a complementary compressor driven by the fueled engine; and (c) injecting the pressurized air and the exhaust mixture into the combustion shell, in which the operation of the fueled engine is independent of the electrical network.
    [00059] According to a preferred embodiment, the hot exhaust from the separately supplied engine is used to preheat the fuel that is supplied to the combustion. Preferably, the fueled engine includes a jacket cooling system and the heat removed from the jacket cooling system is used to preheat the fuel that is supplied to the combustor.
    [00060] According to another preferred embodiment, all or a portion of the exhaust from the fueled engine is diverted to provide heat input to a heat recovery steam generator and / or the turbine when the gas turbine is not operational .
    [00061] According to another preferred embodiment, the pressurized air produced by the powered engine driven compression process is diverted to provide heat input to a heat recovery steam generator and / or the turbine when the gas turbine is not is operational.
    [00062] Yet another modality relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine, fluidly connected to each other; (b) cooling the gas turbine inlet air using a complementary cooling process driven by a fueled engine; and (c) inject the exhaust of the engine separately supplied into the exhaust of the gas turbine, in which the operation of the fueled engine is independent of the electrical network.
    [00063] Yet another modality relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine, fluidly connected to each other; (d) to cool the gas turbine inlet air using a complementary cooling process driven by a fueled engine; and (e) inject the exhaust of the engine separately supplied into the exhaust of the gas turbine, in which the operation of the fueled engine is independent of the electrical network.
    [00064] Yet another modality relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine, fluidly connected to each other; (b) pressurize the ambient air using a complementary compressor driven by a fueled engine; and (c) inject the pressurized air into a rotor cooling air circuit upstream of a rotor air cooler, in which the operation of the fueled engine is independent of the electrical network.
    [00065] Preferably, the exhaust of the alternatively fueled engine is discharged into the exhaust of the turbine.
    [00066] Yet another modality refers to a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine, fluidly connected to each other (b) pressurize the ambient air using a complementary compressor driven by a fueled engine; and (c) inject the pressurized air into a rotor cooling air circuit downstream of a rotor air cooler, in which the operation of the fueled engine is independent of the electrical network.
    [00067] Preferably, the exhaust of the alternatively fueled engine is discharged into the exhaust of the turbine.
    [00068] Another modality relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine , fluidly connected to each other; (b) pressurize the ambient air using a complementary compressor driven by a fueled engine; (c) inject the pressurized air into the intermediate pressure cooling circuit, in which the operation of the fueled engine is independent of the network electrical.
    [00069] Preferably, the exhaust of the alternatively fueled engine is discharged into the exhaust of the turbine.
    [00070] Another modality relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine , fluidly connected to each other; (b) pressurize the ambient air using a complementary compressor driven by a fueled engine; and, (c) inject the pressurized air into the cooling circuit of the first stage nozzle, in which the operation of the fueled motor is independent of the electrical network.
    [00071] Preferably, the exhaust of the alternatively fueled engine is discharged into the exhaust of the turbine.
    [00072] Another embodiment relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine , fluidly connected to each other, (b) pressurize the ambient air using a complementary compressor driven by a fueled engine, (c) inject the pressurized air into a gas turbine cooling circuit; and (d) injecting steam that is produced using the heat from the alternatively fueled engine to the turbine, in which the operation of the fueled engine is independent of the electrical network.
    [00073] Another modality relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine , fluidly connected to each other; (b) pressurize the ambient air using a complementary compressor driven by a fueled engine; (c) inject the pressurized air into the turbine when the gas turbine system is not working, in which the engine operation supplied is independent of the electrical network.
    [00074] Another modality relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine , fluidly connected to each other; and (b) injecting steam, which is produced using the heat from an alternately fueled engine, into a heat recovery steam generator while the gas turbine system is not working.
    [00075] Another embodiment relates to a method of operating a gas turbine energy system comprising: (a) operating a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine , fluidly connected to each other; and (b) inject the exhaust from a separately supplied engine into a heat recovery steam generator while the gas turbine system is not operating.
    [00076] Yet another embodiment of the invention relates to an apparatus configured to carry out the methods according to the invention, including a gas turbine system comprising a compressor, a combustion shell, a combustion and a turbine, fluidly connected between themselves and one or more additional components (for example, a fueled engine) configured to carry out a method according to the invention.
    [00077] The components of an embodiment of the present invention are shown in Figure 1 as they are used with an existing gas turbine system 1. The gas turbine system 1 includes a compressor 10, combustion 12, combustion housing 14, turbine 16 and generator 18. A fueled engine 151, which is either a reciprocating internal combustion engine, a gas turbine or a similar machine that converts fuel into energy through an exothermic reaction such as combustion, is used to drive a complementary multistage multi-stage compressor 116 that compresses the ambient air 115 and / or the cooled exhaust 154 and discharges the compressed air / exhaust 117. As those skilled in the art will readily observe, as the air / exhaust in the complementary compressor from one stage of the compressor to the next, the air is intercooled by the use of a heat exchanger, such as a cooling tower, to reduce the work required to compress the air in the subsequent compressor stage. In doing so, the efficiency of the complementary compressor 116 is increased, which makes it more efficient than the compressor 10 of the gas turbine system 1.
    [00078] This modality additionally includes a stove 144, which is a heat exchanger that receives exhaust gas 152 from the fueled engine 151 and compressed air / exhaust 117 from the complementary compressor 116. In stove 144, the exhaust gas the hot 152 heats the compressed air / exhaust 117 and then exits the stove 144 as it is the substantially cooler exhaust gas 153. At the same time in the stove 144, the compressed air / exhaust 117 absorbs the heat from the exhaust gas 152 and then leaves the stove 144 as compressed air / exhaust 118 substantially hotter than when it enters the stove 144. The compressed air / substantially hot exhaust 118 is then discharged into the combustion housing 14 of the gas turbine system 1 where it becomes an addition to the mass flow through the combustion 12 and the turbine 16.
    [00079] The hot exhaust gas 153 discharged from the stove 144 enters the valve 161 which directs some or all of the hot exhaust gas 153 to the cooling tower 130 for further cooling. Cold exhaust gas 154 enters the inlet of supplementary compressor 116. Additional ambient air 115 can also be added to the inlet of supplementary compressor 116. Any amount of hot exhaust gas 153 that is not diverted to cooling tower 130 through valve 161 it can be discharged to the atmosphere, to a fuel heating system or to the exhaust of GT 22.
    [00080] The partial exhaust recirculation system of the present invention reduces emissions from the separately supplied engine while the 100% of the exhaust recirculation system eliminates the separately supplied engine as an emission source. This can be very useful in allowing reasons as well as reducing costs so that the exhaust cleaning system of the existing gas turbine can be used, thus eliminating the potential cost for the project.
    [00081] It turns out that gasoline, diesel, natural gas or biofuel engines and similar reciprocating engines are relatively insensitive to backpressure, so placing the stove 144 in the fueled engine 151 does not have a significantly measurable effect on the performance of the fueled engine 151. Figure 11 shows the gas turbine cycle connected in a TS or HS diagram (Enthalpy-Entropy temperature entropy). Since the temperature and enthalpy are proportional to each other (Cp), the vertical distance between the ambient pressure of 101.3 kPa (14.7 psi) P10 and the compressor discharge pressure process ("CDP") represents the compressor work required to pump air up to the CDP. The dotted line P11 shows the discharge pressure of the compressor without injection, which is 1,503.7 (218.1 psi), while the dashed line P12 shows the discharge pressure of the compressor with injection, which is 1.589.2 (230.5 psi). The compressor discharge temperature increases from 410 ° C (770F) P13 without compressed air injection, to 423.33 ° C (794F) P14 with compressed air injection due to the increased compression pressure ratio. This additional -4.4 ° C (24F) results in 1% less fuel required to heat the air to the ignition temperature of 1,345.5 ° C (2,454F) and also results in a + 1.3% increase in work of the compressor (compared to the work of the P15 compressor without compressed air injection) or 3.5MW. The temperature rise (and corresponding enthalpy rise) from approximately 398.88 ° C (750F) to the turbine inlet temperature ("TIT") of approximately 1,345.5 ° C (2,454F), the "ignition temperature "P16, which represents the entry of fuel into the British Thermal Units (" BTU "). The vertical distance of CDP P11, P12 up to 101.3 kPa (14.7 psi) P10 on the right side represents the work of the P17 turbine, which is approximately twice the work of the P15 compressor. The exhaust temperature drops with the injection, due to the higher expansion pressure ratio, from 530.5 ° C (987F) P18 to 519.4 ° C (967F) P19, a decrease of 11.1 ° C or +0, 81% more power per pound of air or + 4.7MW at the base flow.
    [00082] Figure 12 shows a comparison of the mass work in pounds required to pump air from atmospheric conditions (101.3 kPa (14.7 psi)) to a pressure slightly higher than CDP (1,585.7 kPa (230 psi) )) so that it can be downloaded in the full CDP. As can be seen, the dashed curve represents a 3-stage intercooled compressor with approximately 2.45 pressure ratios per stage (248.2 kPa (36 psi) after the first stage and 634.31 kPa (92 psi) after the 2nd stage, 1,585.7 kPa (230 psi) after the 3rd stage). The work to compress 1 lbm of air using an inter-cooled (P20) process is significantly less than a non-cooled compressor even considering the similar stage compression efficiency. Realistically, because of the more intercooled pressure losses at each stage and the fact that air, in fact, has to be pumped up to a higher pressure than CDP to effectively inject air into the GT, more work is required than Figure 12 implies. However, on a per pound basis even considering these considerations, the intercooled compressor uses less power to work P21 required by GT to compress air for the turbine cycle.
    [00083] Figure 2 shows the modality of Figure 1 where fuel heating is achieved by using hot exhaust 153 to heat fuel in a fuel heater 201. This further improves the efficiency of the power plant as the Fuel heating reduces the BTU fuel input required to raise the exhaust air from the compressor 10 to the turbine inlet temperature, which results in a reduced amount of fuel 24 that is required by GT.
    [00084] Figure 3 uses an alternative technology, a 401 input cooling system for power increase. Inlet cooling works by providing a cold refrigerant that is used to cool the fluid that is circulated in a radiator 405. The cooled fluid 403 enters the radiator 405 and cools the gas turbine inlet air 20 through the radiator 405 in such a way. way that the cold air (402) is discharged to the GT entrance making the GT cycle more efficient and producing more power. The cooling fluid is then discharged 404 from the radiator 405 hotter than when it enters and the cooling system 401 cools that fluid again. Conventionally, these systems are driven by electric motors, which place a large parasitic load on the plant while the plant is trying to generate additional power, which translates to a significant heat rate penalty. When a separately powered engine is used to drive the cooler, the parasitic charge is eliminated. With the advent, current popularity and advances, of effective natural gas reciprocating engines, the reciprocating engine exhaust can be added to the gas turbine exhaust to produce additional steam in the HRSG for the steam turbine. Some or all of this additional steam can also be extracted and used as a steam injection for increased power, if desired. Both of these features are significant efficiency improvements for a combined cycle plant. In single cycle plants, an auxiliary boiler (not shown) can use the hot exhaust 352 to produce steam that can be used for steam injection into the GT resulting in increased power.
    [00085] Figure 4 shows an alternative embodiment of Figure 1 where a valve 501 is placed on exhaust 152 of the separately supplied engine 151 which diverts exhaust 502 from engine 151 to the HSG 503 of a combined cycle plant where it is used to preheat or keep the system warm for faster start times. When such a system is operated, a hydraulic or mechanical clutch 504 is used to disengage the shaft of the fueled motor 151 from the compressor 116 such that it does not operate.
    [00086] Figure 5 is very similar to Figure 4, however, the clutch for the complementary compressor 116 is eliminated and the compressor 116 supplies compressed air / exhaust mixture 602 to the HRSG 503 and / or compressed air / exhaust mixture 118 for the gas turbine via recuperator 114. This can be advantageous over the low pressure exhaust, as shown in Figure 4, because the pressurized air / exhaust mixture can be more easily directed to the flow to areas than the exhaust air. relatively low pressure / exhaust mixture. In addition, the separately supplied engine 151 will produce warmer exhaust temperatures that may be desired for heating purposes. This setting can be changed in such a way that the exhaust with low pressure, but very high temperature (not shown) can be used to preheat areas of the HRSG 503 and GT that can use the air with warmer temperature and compressed air / pressure exhaust low can be used in the areas of the HRSG 503 and the turbine can use the cooler temperature air.
    [00087] Figure 6 is a simplified approach to inject compressed air into the gas turbine system 1 because compressed air 117 is not required to be heated because air is used to replace the cooled cooling air 602 that is normally supplied by gas turbine 601 and cooled by air or steam in the air cooling system of rotor 155. Under normal operation of the Siemens Westinghouse 501F, 501D5 and 501B6 engine, for example, approximately 6.5% of the compressed air through compressor 10 is drained 601 of the compressor discharge plenum 14 through a single wide pipe, approximately 50.8 cm (20 inches) in diameter. The exhaust air 601 is approximately 1,378.9 to 1,723.6 kPa (200 to 250 psi) and 343.3 to 398.8 ° C (650 to 750F). this hot air enters the rotor air cooling system 155 where air or steam is used to cool the drained air 601. The heat is discharged into the atmosphere 603 and spent when the air is used to cool the drained air 601. However, if the steam is used as the refrigerant to cool the drained air 601, the heat is transferred from the drained air 601 to the steam, thereby increasing the enthalpy of the steam and the steam can then be used in the cooling cycle. steam. In both cases, there is an improvement in the efficiency of the gas GT 1 cycle if no amount of heat is discharged. By injecting cold pressurized air 117 upstream 601 or downstream 602 of the rotor air cooler 155, the rejected heat 603 is minimized or eliminated, thereby improving the cycle efficiency of GT 1 while at the same time increasing efficiently , the mass air flow through the combustion section 12 and turbine section 16. Most gas turbines have dedicated 701 intermediate pressure compressor bleeds that are used to cool the later stages of the turbine where the reduced pressures are required, as shown in Figure 7. Also, all gas turbines provide the first blade cooling circuit with the highest available pressure, which is in the compressor discharge wrap 14 (or combustion wrapper), as shown in Figure 8 Depending on the injection location, the rotor cooling air, as shown in Figure 6, the intermediate pressure cooling, as shown in Figure 7, or the first blade cooling, with As shown in Figure 8, different pressures are required. These pressures can be provided by the output of the intercooled complementary compressor 116 or from previous stages of the intercooled complementary compressor 116 for lower pressure applications. In all cases, since this type of injection uses little (not shown) or no recovery to heat the air, the exhaust 152 of the separately supplied engine can be added to the gas turbine exhaust 22, as shown, to increase the exhaust energy for a combined cycle plant. If the power boost system of the present invention is located in a single cycle plant, hot exhaust 152 can be used in a packaged boiler 901 to produce steam for injection into the gas turbine 903, as shown in Figure 9. Since the TurboPHASE packages (as the present invention is called) are intended to be modular, it may be advantageous to incorporate the packaged boiler 901 into at least one of the units in such a way that during the off-peak times the TurboPHASE modular package can be run to keep the gas turbine heated with pressurized hot air circulation 117 and keep the steam turbine / HPvSG 503 heated with steam circulation to reduce the start time requirement.
    [00088] There are further improvements in efficiency that can be achieved by incorporating low quality heat. For example, in Figure 10, the fuel inlet of the gas turbine 24 can be preheated 1023 with heat from the fueled engine jacket cooling system 1011 and 1012. By doing so, the plant cooling requirements can be reduced and the fuel from the gas turbine will be preheated 1023 before entering the fuel heater 201, thus requiring less heat input to reach the desired fuel temperature or to be able to reach a higher fuel temperature. Figure 10 also shows an alternative embodiment where exhaust 153 from stove 144 is used to add the final heat to the gas turbine fuel 1024 before injection into the GT. In that case, the exhaust gas 153 from the alternatively supplied engine 151, after flowing through the fuel heater 201 and being discharged 1002 is relatively cold.
    [00089] Although the systems, components, methods and devices in particular described in this document and described in detail are fully capable of achieving the objects and advantages of the invention described above, it must be understood that these are the presently preferred modalities of invention and are, therefore, representative of the matter that is widely contemplated by the present invention, that the scope of the present invention completely encompasses other modalities that may become obvious to those skilled in the art and that the scope of the present invention should be, therefore. in this way, limited by nothing but the appended claims, in which the reference to an element in the singular means "one or more" and not "one and only one", unless otherwise stated in the claim.
    [00090] It will be noted that the modifications and variations of the invention are covered by the above teachings and are within the scope of the appended claims without departing from the intended spirit and scope of the invention.
    权利要求:
    Claims (2)
    [0001]
    1. Method of operation of a gas turbine energy system (1), characterized by the fact that it comprises: (a) operating a gas turbine system (1) comprising a compressor (10), a combustion enclosure (14), a combustor (12) and a turbine (16), fluidly connected to each other; (b) pressurize the ambient air using a complementary compressor (10) driven by a fueled engine (151), the operation of which is independent of the electrical network; (c) injecting said pressurized air into a rotor cooling air circuit upstream of a rotor air cooler (155); and (d) adding exhaust from the fueled engine (151) to the exhaust of the turbine (16).
    [0002]
    2. Method of operation of a gas turbine energy system, characterized by the fact that it comprises: (a) operating a gas turbine system (1) comprising a compressor (10), a combustion enclosure (14) , a combustor (12) and a turbine (16), fluidly connected to each other; (b) pressurize the ambient air with the use of a complementary compressor (10) driven by said fueled engine (151) to form pressurized air; (c ) mixing said pressurized air and the exhaust from said fueled engine (151) in a stove (144) to form pressurized hot air; (d) injecting said pressurized hot air into said combustion shell (14), in which the operation the said fueled motor (151) is independent of the electrical network.
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    KR20150076145A|2015-07-06|
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    法律状态:
    2018-11-21| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2020-03-24| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-01-19| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-03-30| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 21/10/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US201261795836P| true| 2012-10-26|2012-10-26|
    US61/795,836|2012-10-26|
    PCT/US2013/065998|WO2014066276A2|2012-10-26|2013-10-21|Gas turbine energy supplementing systems and heating systems, and methods of making and using the same|
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