QUICK START SYSTEMS FOR ALTERNATIVE FUELS FOR GAS TURBINE DRIVES

Abstract

The present application provides a rapid start system for alternative fuels for a gas turbine engine comprising a combustion chamber and a compressor. The rapid start system for alternative fuels can include an alternative liquid fuel, a thermal energy storage tank, and a vaporizer. The alternative liquid fuel is stored under pressure in the thermal energy storage tank, so that releasing the alternative liquid fuel from the thermal energy storage tank causes it to vaporize. Upon starting the gas turbine engine, the thermal energy storage tank delivers the vaporized alternative fuel to the combustion chamber until the vaporizer is ready for operation. The alternative liquid fuel can be propane, ethanol, or methanol.

Description

TECHNICAL AREA

[0001] The present application and the resulting patent relate generally to gas turbine engines and in particular to rapid start systems and methods for alternative fuels for gas turbine engines, which utilize a rapid release of hot, pressurized alternative fuels from thermal storage. STATE OF THE ART

[0002] Diesel fuel is generally considered the traditional liquid fuel for gas turbine-driven power generation systems. It is relatively inexpensive, easy to store and handle, and has a high energy concentration (heating value). However, with the increasing use of natural gas and the supporting infrastructure, diesel fuel is now typically used as a reserve fuel rather than the primary fuel.

[0003] Given current and future decarbonization targets, there is a growing global need for alternatives to diesel fuel. As a carbon-free energy source, hydrogen has become the primary fuel of choice for the next generation of gas turbines. One of the goals in developing hydrogen-capable combustion systems is to eliminate the use of liquid fuel. The exclusive use of gaseous fuels offers significant advantages in terms of reducing complexity, costs, and general operational limitations.

[0004] The reserve fuel for hydrogen-capable combustion systems must meet several operational requirements. The fuel should be in liquid form so that it can be stored cost-effectively in large quantities on-site. The fuel should have the lowest possible carbon content. Furthermore, the fuel should have favorable vaporization properties so that it can be pressurized and vaporized for use in a gas turbine engine. Currently, the focus of these requirements is on liquid propane gas (LPG), ethanol, methanol, and similar fuels.

[0005] Gas turbine engines in a single-cycle configuration are frequently used for "quick start" operation. Such a "quick start" takes approximately ten minutes from cold start (announcement) to base load. This quick start capability poses a challenge for currently available vaporizer systems using propane, ethanol, methanol, and the like, as these systems generally require much longer than a few minutes for the fuel to vaporize and be injected into the gas turbine engine's combustion chamber. In particular, with current systems, it can take several hours for the vaporizer system to warm up and begin fuel conditioning. SUMMARY

[0006] The present application and the resulting patent thus provide a rapid start system for alternative fuels for a gas turbine engine with a combustion chamber and a compressor. The rapid start system for alternative fuels can include an alternative liquid fuel, a thermal energy storage tank, and a vaporizer. The alternative liquid fuel is stored under pressure in the thermal energy storage tank, so that releasing the alternative liquid fuel from the thermal energy storage tank causes it to vaporize. When the gas turbine engine is started, the thermal energy storage tank delivers the vaporized alternative fuel to the combustion chamber until the vaporizer is ready for operation.

[0007] The present application and the resulting patent further provide a rapid start-up method for a gas turbine engine comprising a combustion chamber and a compressor. The method may include the following steps: storing a liquid fuel under pressure in a thermal energy storage tank, heating a heat exchanger fluid in a heat recovery circuit with an outlet from the compressor, heating an evaporator with the heat exchanger fluid, evaporating the liquid fuel by releasing the pressure from the thermal energy storage tank, and allowing the evaporated fuel to flow from the thermal energy storage tank to the combustion chamber until the evaporator reaches a predetermined temperature.

[0008] The present application and the resulting patent further provide a rapid start system for a gas turbine engine comprising a combustion chamber and a compressor. The rapid start system can include liquid propane fuel, a thermal energy storage tank, and a liquid bath vaporizer. The liquid propane fuel is stored under pressure in the thermal energy storage tank, so that upon release of the liquid propane fuel from the thermal energy storage tank, it vaporizes into vaporized propane fuel. During start-up, the thermal energy storage tank then supplies the vaporized propane fuel to the combustion chamber until the liquid bath vaporizer is operational.

[0009] These and other features and improvements of this application and the resulting patent will be obvious to a person skilled in the art after reviewing the following detailed description in conjunction with the various drawings and the attached claims. BRIEF DESCRIPTION OF THE DRAWINGS Fig. Figure 1 is a schematic representation of a gas turbine engine, including a compressor, a combustion chamber, a turbine and an external load. Fig. Figure 2 is a schematic representation of a rapid start system for alternative fuels, as can be described here. Fig. Figure 3 is a schematic representation of a liquid bath evaporator equipped with the quick-start system for alternative fuels. Fig. 2 can be used. Fig. Figure 4 is a schematic representation of another embodiment of a rapid start system for alternative fuels, as can be described here. Fig. Figure 5 is a schematic representation of a passive superheater, which is used with the quick-start system for alternative fuels. Fig. 4 can be used. DETAILED DESCRIPTION

[0010] Referring to the drawings in which the same reference symbols refer to the same elements in the different views, shows Fig. Figure 1 is a schematic representation of a gas turbine engine 10 as it may be used herein. The gas turbine engine 10 may include a compressor 15. The compressor 15 compresses an incoming air stream 20. The compressor 15 feeds the compressed air stream 20 to a number of combustion chamber tubes 25. Each combustion chamber tube 25 mixes the stream of compressed air 20 with a pressurized fuel stream 30 and ignites the mixture to produce a stream of hot combustion gases 35. Although only a single combustion chamber tube 25 is shown, the gas turbine engine 10 may include any number of combustion chamber tubes 25 arranged in a circumferential configuration and the like. Alternatively, the combustion chamber 25 may be an annular combustion chamber. The stream of combustion gases 35 is then fed to a turbine 40. The flow of combustion gases 35 drives the turbine 40 to perform mechanical work.The mechanical work generated in the turbine 40 drives the compressor 15 via a rotor shaft 45 and an external load 50 such as an electric generator and the like.

[0011] The Gas Turbine Engine 10 can be any of a number of different gas turbine engines offered by the General Electric Company in Schenectady, New York, including, but not limited to, those such as a heavy-duty gas turbine engine of the 7 or 9 series and the like. The Gas Turbine Engine 10 can have different configurations and can use different types of components. Other types of gas turbine engines can also be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment can also be used together herein.

[0012] The Fig. 2 and Fig. Figure 3 shows a quick-start system 100 for alternative fuels, as described here for use with the gas turbine engine 10 and the like. In particular, a liquid propane quick-start system 105 is shown in this example. The liquid propane quick-start system 105 can vaporize a stream of liquid propane 110 into a stream of vaporized propane gas 125 for use in the combustion chamber 25 during quick starts and the like of the gas turbine engine 10. Other types of alternative fuels 115 can be used herein.

[0013] The liquid propane rapid start system 105 can include a liquid propane storage tank 120. The liquid propane storage tank 120 can contain a volume of liquid propane 110. The liquid propane storage tank 120 can have any suitable size, shape, or configuration, including a spherical shape. The liquid propane storage tank 120 can be insulated or uninsulated. Depending on the operational requirements, the liquid propane storage tank 120 can have a sufficient volume to supply the gas turbine engine 10 with fuel for approximately 72 hours of emergency operation at base load. Other components and configurations can be used here.

[0014] The liquid propane quick-start system 105 can include a thermal energy storage tank 140. When charged, the thermal energy storage tank 140 can store a heated volume of liquid propane 110 under pressure. The thermal energy storage tank 140 can be of a conventional design and any suitable size, shape, or configuration. The thermal energy storage tank 140 can be insulated. The thermal energy storage tank 140 can have an inlet port 150 and an outlet port 160. One or more valves 170 can be arranged on either side of the thermal energy storage tank 140. The valves 170 can be conventional solenoid valves for switching on and off, and the like. The thermal energy storage tank 140 can be equipped with an electric jockey heater 175, and the like, to compensate for heat losses in the standby state. The heater 175 can be of a conventional design.Other types of heating devices can be used here.

[0015] The liquid propane storage tank 120 and the inlet port 150 of the thermal energy storage tank 140 can be connected via a feed pump 180 and a high-pressure pump 190 downstream of the feed pump 180. The feed pump 180 can be a conventional low positive suction head (NPSH) pump or the like to provide substantially laminar flow for the liquid propane 110 stream. The feed pump 180 can have any suitable capacity. The high-pressure pump 190 can also be of a conventional design and have any suitable capacity. The high-pressure pump 190 pressurizes the stream of liquid propane 110 entering the thermal energy storage tank 140. Other components and configurations may be used herein.

[0016] The liquid propane rapid start system 105 can include an evaporation circuit 200 and an associated heat recovery circuit 210. As shown in Fig. As shown in Figure 3, the evaporation circuit 200 can include a liquid bath evaporator 220. The liquid bath evaporator 220 can be a heat exchanger for exchanging heat between the liquid propane stream 110 and the heat recovery circuit 210. The liquid bath evaporator 220 can include an inlet port 230 for liquid propane and an outlet port 240 for vaporized propane. Likewise, the liquid bath evaporator 220 can have an evaporator liquid heat inlet port 250 and an evaporator liquid heat outlet port 260. A heat exchange fluid 270 can flow through the evaporator liquid heat inlet port 250 and the evaporator liquid heat outlet port 260. The heat exchange fluid 270 can be water, glycol, oils, and the like (including mixtures thereof).The stream of liquid propane 110 is heated and evaporated in the liquid bath evaporator 220 by heat exchange with the heat exchange fluid 270, resulting in a stream of vaporized propane gas 125. Other components and configurations can be used in this system.

[0017] The heat recovery circuit 210 can include an air cooler 280 connected to the liquid bath evaporator 220. The air cooler 280 can be a heat exchanger for exchanging heat between the flow of heat exchange fluid 270 and a flow of compressor outlet air 55 from the compressor 15. The air cooler 280 can include a coolant heat inlet 290 and a coolant heat outlet 300 for the heat exchange fluid 270. Likewise, the air cooler 280 can have a compressor outlet inlet 310 and a compressor outlet outlet 320. The flow of compressor outlet air 55 heats the heat exchange fluid 270 for use in the liquid bath evaporator 220. Other components and configurations can be used herein.

[0018] The evaporation circuit 200 and the heat recovery circuit 210 can include a number of fuel gas cleaning components 330. The evaporation circuit 200 can include a separator drum 340. The separator drum 340 can be of conventional design and can remove condensed liquids and the like from the evaporated stream of propane gas 125. In the illustrated embodiment, the separator drum 340 is located downstream of the liquid bath evaporator 220. The heat recovery circuit 210 can include a scrubber 350 and any number of filters 360, such as coalescing filters and the like, located upstream of the combustion chamber tubes 25. The scrubber 350 and the filters 360 can be of conventional design and can remove impurities and liquid droplets from the stream of evaporated propane gas 125.

[0019] The evaporation circuit 200 and the heat recovery circuit 210 can meet at a gas / air mixer 370. The gas / air mixer 370 can be of conventional design and mixes the flow of vaporized propane 125 and the flow of compressor outlet air 55 before they enter the combustion chamber 25. The gas / air mixer 370 can obtain the vaporized propane 125 either from the heat energy storage tank 140 or from the liquid bath evaporator 220. One or more booster compressors 380 can also be used to increase the flow of compressor outlet air 55. The booster compressors 380 can be of conventional design. Other components and configurations can be used.

[0020] In its charged state, the thermal energy storage tank 140 can be filled with liquid propane 110 under pressure and heated. For example, the liquid propane 110 can be pressurized to approximately 600 psig and heated to a saturation temperature of approximately 210° Fahrenheit (approximately 98.9° Celsius) via the heater 175, by circulation through the liquid bath evaporator 220 in the evaporation circuit 200, or by other means. The thermal energy storage tank 140 can then be insulated with the respective valves 170 closed.

[0021] At the start of the cold start, the gas turbine engine 10 begins a cold acceleration cycle up to a partial speed, and the liquid bath evaporator 220 can initiate a warm-up cycle. As soon as the "ready to ignite" signal is received, the booster compressor 380 supplies the compressor outlet air 55, and the thermal energy storage tank 140 releases the vaporized propane gas 125 by immediately evaporating the hot liquid and delivers the vaporized propane gas 125 to the gas / air mixer 370. After mixing and pressure reduction, the gas mixture can be significantly above its dew point.

[0022] When the pressure of the gas at the top of the thermal energy storage tank 140 falls below the saturation pressure, the latent heat of the liquid propane 110 quickly causes sufficient quantities to evaporate. The thermal energy storage tank 140 is still insulated from the liquid propane storage tank 120, so the thermal energy storage tank 140 can ensure the fuel supply for the gas turbine engine 10 for a considerable period of time (15 to 25 minutes). When the stored liquid propane 110 in the thermal energy storage tank 140 is depleted, the pressure drops at a certain rate until it is no longer sufficient for the combustion chamber 25. At this point, the valves 170 on the thermal energy storage tank 140 can be closed, and the liquid bath evaporator 220 begins to supply fuel to the combustion chamber 25. Once the compressed air flow through the air cooler 280 is initiated, the heat recovery circuit 210 can be activated.The heat released from the compressor outlet air stream 55 is transferred to the liquid bath evaporator 220. This process helps to accelerate the heating of the liquid bath evaporator 220 to the specified operating temperature and to reduce the associated fuel consumption.

[0023] Once the liquid bath evaporator 220 is warmed up and ready to receive the fuel supply, the liquid propane pumps 180 and 190 begin the flow through the liquid bath evaporator 220. The inlet valves 170 on the thermal energy storage tank 140 open to fill the thermal energy storage tank 140 with liquid propane 110 at ambient temperature. Once the thermal energy storage tank 140 is filled, the inlet valves 170 can be closed, and the electric jockey heaters 175 inside the thermal energy storage tank 140 can gradually increase the temperature and pressure of the liquid propane 110 to charge the thermal energy storage tank 140.

[0024] The liquid propane quick-start system 100 thus maintains the liquid propane 110 in the thermal energy storage tank 140 in a pressurized, heated state. The pressure in the thermal energy storage tank 140 can be considerably higher than the required gas turbine supply pressure. Under these circumstances, the pressure drop in the thermal energy storage tank 140 leads to a rapid, almost instantaneous evaporation of the liquid propane 110 in quantities sufficient for starting, warm-up, and continuous operation of the gas turbine engine 10, until the liquid bath evaporator 220 can reliably take over and operate in continuous mode. Likewise, the heat recovery circuit 210 connects the liquid bath evaporator 220 and the air cooler 280 to reduce the fuel consumption of the liquid bath evaporator 220 and accelerate warm-up in quick-start mode.

[0025] The liquid propane quick-start system 100 can thus be used in gas turbine engines 10 where liquid fuel combustion chambers are not available or desired, but where the possibility of a liquid reserve fuel is still required and where a quick start is also necessary. As described below, the system 105 can also be used for other liquid fuels with relatively flat latent heat or phase change curves (i.e., with approximately similar bubble and dew points), although the quick-start system 100 has been described for alternative fuels mainly in connection with liquid propane 110.

[0026] For example, they show Fig. 4 and Fig. 5 A quick-start system 100 for alternative fuels, as described here for use with the gas turbine engine 10 and the like. In particular, an ethanol quick-start system 400 is shown in this example. The ethanol quick-start system 400 can supply a stream of ethanol 410 in vaporized form to the combustion chamber 25 during quick starts and the like of the gas turbine engine 10. The ethanol quick-start system 400 and similar systems are also suitable for use with methanol and similar fuels with a low number of carbon atoms. For simplicity, the alternative system 400 is referred to as the "ethanol quick-start system," but methanol or other similar fuels can also be used instead of ethanol.

[0027] The ethanol quick-start system 400 can include an ethanol storage tank 420. The ethanol storage tank 420 can hold a volume of ethanol 410. The ethanol storage tank 420 can be of any suitable size, shape, or configuration. The ethanol quick-start system 400 can also include the thermal energy storage tank 140. As described above, the thermal energy storage tank 140 can store a heated volume of ethanol 410 under pressure. The thermal energy storage tank 140 also has an inlet port 150, an outlet port 160, and several valves 170. The ethanol storage tank 420 and the inlet port 150 of the thermal energy storage tank 140 can be connected via the feed pump 180 and the high-pressure pump 190. Other components and configurations can be used in this system.

[0028] The ethanol quick-start system 400 can include the evaporation circuit 200 with the liquid bath evaporator 220. The liquid bath evaporator 220 can heat the ethanol stream 410 by heat exchange with the heat recovery circuit 210 as described above, or via another source of heat exchange fluid 270. The evaporation circuit 200 can also include a liquid bath superheater 430. Similar to the liquid bath evaporator 220, the liquid bath superheater 430 can be a heat exchanger connected to the heat recovery circuit 210 or another source of heat exchange fluid 270, as described above. The liquid bath superheater 430 further increases the temperature of the ethanol stream 410 to the minimum required superheat level. Other components and configurations can be used herein.

[0029] The ethanol quick-start system 400 can include a passive superheater and buffer 440, positioned between the heat energy storage tank 140 and the combustion chamber 25. As shown in Fig. As shown in Figure 5, the passive superheater and buffer 440 can include a storage tank 450 and a heat exchanger 460. A circulation pump 470 can be used to circulate the liquid ethanol 410 at the bottom of the thermal energy storage tank 140 through the heat exchanger 460 and the storage tank 450 of the passive superheater and buffer 440. Likewise, the heat exchanger 460 and the storage tank 450 act as a buffer during the release of the vaporized ethanol 410 at startup, with the heat exchanger 460 exchanging heat between the vapor and liquid streams of the ethanol 410. Other components and configurations can be used herein.

[0030] The ethanol rapid start system 400 thus maintains the ethanol 410 in the thermal energy storage tank 140 under positive pressure. The pressure in the thermal energy storage tank 140 can be considerably higher than the required gas turbine supply pressure. Under these circumstances, the pressure drop in the thermal energy storage tank 140 leads to a rapid, almost instantaneous evaporation of the ethanol 410 in quantities sufficient for starting, ramping up, and continuous operation of the gas turbine engine 10, until the liquid bath evaporator 220 can reliably take over and operate in continuous mode.

[0031] It should be obvious that the foregoing relates only to certain embodiments of this application and the resulting patent. Numerous changes and modifications may be made herein by a person skilled in the art without departing from the general concept and scope of protection of the invention as defined by the following claims and their equivalents.

[0032] Further aspects of the invention are provided by the subject matter of the following paragraphs: 1. A quick-start alternative fuel system for a gas turbine engine with a combustion chamber and a compressor, comprising an alternative liquid fuel; a thermal energy storage tank; wherein the alternative liquid fuel is stored under pressure in the thermal energy storage tank such that the release of the alternative liquid fuel from the thermal energy storage tank causes the alternative liquid fuel to vaporize; and an evaporator; wherein, upon starting the gas turbine engine, the thermal energy storage tank supplies the vaporized alternative fuel to the combustion chamber until the evaporator is ready for operation. 2. The rapid start system for alternative fuels according to clause 1, further comprising a storage tank for alternative liquid fuel. 3. The rapid start system for alternative fuels according to one of the preceding clauses, wherein the thermal energy storage tank and the storage tank for alternative liquid fuels are connected to each other via one or more pumps. 4. The quick-start system for alternative fuels according to any of the preceding clauses, wherein the evaporator comprises a liquid bath evaporator for transferring heat between the alternative liquid fuel and a heat exchange fluid. 5. The quick-start system for alternative fuels according to one of the preceding clauses, further comprising a heat recovery circuit connected to an outlet from the compressor. 6. The quick-start system for alternative fuels according to any of the preceding clauses, wherein the heat recovery circuit includes an air cooler connected to the evaporator. 7. The quick-start system for alternative fuels according to any of the preceding clauses, further comprising a gas / air mixer connected to the vaporized alternative fuel from the thermal energy storage tank and the outlet from the heat recovery circuit. 8. The quick-start system for alternative fuels according to one of the preceding clauses, further comprising components for fuel gas purification that are connected to the vaporized alternative fuel from the thermal energy storage tank. 9. The quick-start system for alternative fuels according to any of the preceding clauses, wherein the alternative fuel includes propane. 10. The quick-start system for alternative fuels according to any of the preceding clauses, wherein the alternative fuel comprises ethanol or methanol. 11. The quick-start system for alternative fuels according to one of the preceding clauses, further comprising a liquid bath superheater located downstream of the evaporator. 12. The quick-start system for alternative fuels according to one of the preceding clauses, further comprising a passive superheater positioned between the heat energy storage tank and the combustion chamber. 13. The quick-start system for alternative fuels according to any of the preceding clauses, wherein the passive superheater comprises a storage tank and a heat exchanger. 14. The quick-start system for alternative fuels according to one of the preceding clauses, further comprising a circulation pump positioned between the heat energy storage tank and the passive superheater. 15. A rapid start procedure for a gas turbine engine comprising a combustion chamber and a compressor, comprising: storing a liquid fuel under pressure in a thermal energy storage tank; heating a heat exchanger fluid in a heat recovery circuit with an outlet from the compressor; heating an evaporator with the heat exchanger fluid; evaporating the liquid fuel by depressurizing the thermal energy storage tank; and allowing the evaporated fuel to flow from the thermal energy storage tank to the combustion chamber until the evaporator reaches a predetermined temperature. 16. A quick-start system for a gas turbine engine with a combustion chamber and a compressor, comprising: a liquid propane fuel; a thermal energy storage tank; wherein the liquid propane fuel is stored under pressure in the thermal energy storage tank, such that the release of the liquid propane fuel from the thermal energy storage tank causes the liquid propane fuel to vaporize into propane gas fuel; and a liquid bath vaporizer; wherein, upon starting the gas turbine engine, the thermal energy storage tank supplies the vaporized propane gas fuel to the combustion chamber until the liquid bath vaporizer is ready for operation. 17. The rapid start system according to one of the preceding clauses, further comprising a storage tank for liquid propane fuel. 18. The quick-start system according to one of the preceding clauses, further comprising a heat recovery circuit connected to an outlet from the compressor. 19. The quick-start system according to any of the preceding clauses, wherein the heat recovery circuit includes an air cooler connected to the liquid bath evaporator. 20. The quick-start system according to one of the preceding clauses, further comprising a gas / air mixer which is connected to the vaporized propane fuel from the thermal energy storage tank and the outlet from the heat recovery circuit.

Claims

[1] Rapid start system for alternative fuels for a gas turbine engine with a combustion chamber and a compressor, comprising: an alternative liquid fuel; a thermal energy storage tank; wherein the alternative liquid fuel is stored under pressure in the thermal energy storage tank, so that the alternative fuel evaporates when the alternative liquid fuel is released from the thermal energy storage tank; and an evaporator; where, when the gas turbine engine is started, the thermal energy storage tank supplies the vaporized alternative fuel to the combustion chamber until the vaporizer is ready for operation. [2] Rapid start system for alternative fuels according to claim 1, further comprising a storage tank for alternative liquid fuel. [3] Rapid start system for alternative fuels according to claim 2, wherein the thermal energy storage tank and the storage tank for alternative liquid fuels are connected to each other via one or more pumps. [4] Rapid start system for alternative fuels according to claim 1, wherein the evaporator comprises a liquid bath evaporator for transferring heat between the alternative liquid fuel and a heat exchange fluid. [5] Rapid start system for alternative fuels according to claim 1, further comprising a heat recovery circuit connected to an outlet from the compressor. [6] Rapid start system for alternative fuels according to claim 5, wherein the heat recovery circuit comprises an air cooler connected to the evaporator. [7] Rapid start system for alternative fuels according to claim 5, further comprising a gas / air mixer which is connected to the vaporized alternative fuel from the thermal energy storage tank and the outlet from the heat recovery circuit. [8] Rapid start system for alternative fuels according to claim 1, further comprising components for fuel gas purification which are connected to the vaporized alternative fuel from the thermal energy storage tank. [9] Rapid start system for alternative fuels according to claim 1, wherein the alternative liquid fuel comprises propane. [10] Rapid start system for alternative fuels according to claim 1, wherein the alternative liquid fuel comprises ethanol or methanol. [11] Rapid start system for alternative fuels according to claim 10, further comprising a liquid bath superheater located downstream of the evaporator. [12] Rapid start system for alternative fuels according to claim 10, further comprising a passive superheater arranged between the heat energy storage tank and the combustion chamber. [13] Rapid start system for alternative fuels according to claim 12, wherein the passive superheater comprises a storage tank and a heat exchanger. [14] Rapid start system for alternative fuels according to claim 12, further comprising a circulation pump positioned between the heat energy storage tank and the passive superheater. [15] Method for the rapid starting of a gas turbine engine with a combustion chamber and a compressor, comprising: Storing a liquid fuel under pressure in a thermal energy storage tank; Heating a heat exchange fluid in a heat recovery circuit with an outlet from the compressor; Heating an evaporator with the heat exchange fluid; Evaporation of the liquid fuel by pressure relief of the thermal energy storage tank; and Flowing the vaporized fuel from the heat energy storage tank to the combustion chamber until the vaporizer reaches a predetermined temperature. [16] Quick start system for a gas turbine engine with a combustion chamber and a compressor, comprising: a liquid propane fuel; a thermal energy storage tank; wherein the liquid propane fuel is stored under pressure in the thermal energy storage tank, so that upon release of the liquid propane fuel from the thermal energy storage tank, the liquid propane fuel evaporates into vaporized propane gas fuel; and a liquid bath evaporator; where, when the gas turbine engine is started, the thermal energy storage tank supplies the vaporized propane fuel to the combustion chamber until the liquid bath evaporator is ready for operation. [17] Rapid start system according to claim 16, further comprising a storage tank for liquid propane fuel. [18] Quick start system according to claim 16, further comprising a heat recovery circuit connected to an outlet from the compressor. [19] Quick start system according to claim 18, wherein the heat recovery circuit comprises an air cooler connected to the liquid bath evaporator. [20] Quick start system according to claim 18, further comprising a gas / air mixer which is connected to the vaporized propane gas fuel from the heat energy storage tank and the outlet from the heat recovery circuit.

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