Alternative fuel fast start system for gas turbine engines

Abstract

The present application provides an alternative fuel fast start system for a gas turbine engine having a combustor and a compressor. The alternative fuel fast start system may 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, such that release of the alternative liquid fuel from the thermal energy storage tank vaporizes the alternative fuel. Upon starting the gas turbine engine, the thermal energy storage tank supplies vaporized alternative fuel to the combustor until the vaporizer operates. The alternative liquid fuel may be propane, ethanol, or methanol.

Description

[Technical Field]

[0001] TECHNICAL FIELD This application and the resulting patent relate generally to gas turbine engines, and more particularly to an alternative fuel fast start system and method for a gas turbine engine that uses rapid release of hot pressurized alternative fuel from a thermal store. [Background technology]

[0002] Generally speaking, diesel fuel has been considered the traditional liquid fuel for gas turbine-driven power generation systems. Diesel fuel is relatively low cost, easy to store and handle, and has a high energy density (heating value). However, with the increasing use of natural gas and supporting infrastructure, diesel fuel is now commonly used as a backup fuel rather than a primary fuel.

[0003] Current and future decarbonization goals are driving global demand for alternatives to diesel fuel. Hydrogen has become a targeted primary fuel as a carbon-free energy source for next-generation gas turbines. One of the goals in developing hydrogen-enabled combustion systems is to eliminate the use of liquid fuels. The benefits of using only gaseous fuels are significant in reducing complexity, cost, and overall operability constraints.

[0004] Backup fuel for hydrogen-enabled combustion systems must meet several operational requirements. The fuel should be in liquid form so that it can be stored on-site in large quantities in a cost-effective manner. The fuel should have as low a carbon content as possible. Additionally, the fuel should have good vaporization characteristics so that the fuel can be pressurized and vaporized for use in gas turbine engines. With these requirements, the current focus is on liquid propane gas (LPG), ethanol, methanol, and similar fuels.

[0005] Gas turbine engines with simple-cycle configurations are often used for "fast start" service. Such "fast starts" require approximately 10 minutes from a cold start (on notice) to baseload. This fast start capability presents a challenge for currently available vaporizer systems that use propane, ethanol, methanol, etc., because these systems typically require much longer than a few minutes to vaporize and prepare the fuel for injection into the gas turbine engine's combustor. Specifically, current systems may require several hours for the vaporizer equipment to warm up and begin fuel conditioning. [Prior art documents] [Patent documents]

[0006] [Patent Document 1] U.S. Patent Application Publication No. 2021-0189965 A1 Summary of the Invention

[0007] Thus, this application and resultant patent provide an alternative fuel fast start system for a gas turbine engine having a combustor and a compressor. The alternative fuel fast start system may 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, such that release of the alternative liquid fuel from the thermal energy storage tank vaporizes the alternative fuel. Upon starting the gas turbine engine, the thermal energy storage tank supplies vaporized alternative fuel to the combustor until the vaporizer operates.

[0008] The present application and resultant patent further provides a method for fast start-up of a gas turbine engine having a combustor and a compressor. The method may include storing liquid fuel under pressure in a thermal energy storage tank, warming a heat exchange fluid in a heat recovery loop with discharge from the compressor, warming a vaporizer with the heat exchange fluid, vaporizing the liquid fuel by releasing pressure in the thermal energy storage tank, and flowing the vaporized fuel from the thermal energy storage tank to the combustor until the vaporizer reaches a predetermined temperature.

[0009] The present application and resultant patent further provide a fast start system for a gas turbine engine having a combustor and a compressor. The fast start system may include liquid propane fuel, a thermal energy storage tank, and a liquid tank vaporizer. The liquid propane fuel is stored in the thermal energy storage tank under pressure such that releasing the liquid propane fuel from the thermal energy storage tank vaporizes the liquid propane fuel into vaporized propane gas fuel. As a result, during start-up, the thermal energy storage tank supplies vaporized propane gas fuel to the combustor until the liquid tank vaporizer operates.

[0010] These and other features of the present application and the resulting patent will become apparent to those skilled in the art from a review of the following detailed description taken in conjunction with the several drawings and the appended claims. [Brief explanation of the drawings]

[0011] [Figure 1] 1 is a schematic diagram of a gas turbine engine including a compressor, a combustor, a turbine, and an external load. [Figure 2] FIG. 1 is a schematic diagram of an alternative fuel fast start system as may be described herein. [Figure 3] FIG. 3 is a schematic diagram of a liquid tank vaporizer that may be used with the alternative fuel fast start system of FIG. 2. [Figure 4] FIG. 10 is a schematic diagram of a further embodiment of an alternative fuel fast start system as may be described herein. [Figure 5] FIG. 5 is a schematic diagram of a passive superheater that may be used with the alternative fuel fast start system of FIG. 4. DETAILED DESCRIPTION OF THE INVENTION

[0012] Referring now to the drawings, wherein like numerals refer to like elements throughout the several views, FIG. 1 illustrates a schematic diagram of a gas turbine engine 10 that may be used herein. The gas turbine engine 10 may include a compressor 15. The compressor 15 compresses an incoming flow of air 20. The compressor 15 delivers the compressed flow of air 20 to a number of combustor cans 25. The combustor cans 25 mix the compressed flow of air 20 with a flow of pressurized fuel 30 and ignite the mixture to generate a flow of hot combustion gases 35. Although only a single combustor can 25 is shown, the gas turbine engine 10 may include any number of combustor cans 25 arranged, such as in a circumferential array. Alternatively, the combustor 25 may be an annular combustor. The flow of combustion gases 35 is then delivered to a turbine 40. The flow of combustion gases 35 drives the turbine 40 to produce mechanical work. The mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50, such as an electrical generator.

[0013] Gas turbine engine 10 may be any one of several different gas turbine engines offered by General Electric Company of Schenectady, New York, USA, including, but not limited to, a 7 Series or 9 Series heavy-duty gas turbine engine, and may be part of a simple-cycle or combined-cycle power generation system. Gas turbine engine 10 may have a different configuration and may use other types of components. Other types of gas turbine engines may also be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment may also be used together herein.

[0014] 2 and 3 illustrate an alternative fuel fast start system 100 as may be described herein for use with, for example, a gas turbine engine 10. Specifically, in this example, a liquid propane fast start system 105 is shown. The liquid propane fast start system 105 may vaporize a flow of liquid propane 110 into a flow of vaporized propane gas 125 for use in the combustor 25, such as during a fast start of the gas turbine engine 10. Other types of alternative fuels 115 may be used herein.

[0015] The liquid propane fast start system 105 may include a liquid propane storage tank 120. The liquid propane storage tank 120 may contain a quantity of liquid propane 110 therein. The liquid propane storage tank 120 may have any suitable size, shape, or configuration, including a spherical shape. The liquid propane storage tank 120 may be insulated or uninsulated. Depending on the operating requirements, the liquid propane storage tank 120 may have a volume sufficient to fuel the gas turbine engine 10 for approximately 72 hours of backup operation at base load. Other components and configurations may be used herein.

[0016] The liquid propane fast start system 105 may include a thermal energy storage tank 140. When filled, the thermal energy storage tank 140 can store a quantity of heated liquid propane 110 under pressure. The thermal energy storage tank 140 may be of conventional design and may have any suitable size, shape, or configuration. The thermal energy storage tank 140 may be insulated. The thermal energy storage tank 140 may have an inlet port 150 and an outlet port 160. One or more valves 170 may be located on either side of the thermal energy storage tank 140. The valves 170 may be conventional solenoid on-off valves or the like. The thermal energy storage tank 140 may have an electric jug heater 175 or the like for standby heat loss. The heater 175 may be of conventional design. Other types of heating devices may be used herein.

[0017] Inlet ports 150 of liquid propane storage tank 120 and thermal energy storage tank 140 may be in communication via transfer pump 180 and high-pressure pump 190 downstream of transfer pump 180. Transfer pump 180 may be a conventional low net positive suction head (NPSH) pump or the like for providing a substantially laminar flow to the flow of liquid propane 110. Transfer pump 180 may have any suitable capacity. High-pressure pump 190 may likewise be of conventional design and may have any suitable capacity. High-pressure pump 190 pressurizes the flow of liquid propane 110 entering thermal energy storage tank 140. Other components and configurations may be used herein.

[0018] The liquid propane fast start system 105 may include a vaporization circuit 200 and an interconnected heat recovery loop 210. As shown in FIG. 3, the vaporization circuit 200 may include a liquid bath vaporizer 220. The liquid bath vaporizer 220 may be a heat exchanger for exchanging heat between the flow of liquid propane 110 and the heat recovery loop 210. The liquid bath vaporizer 220 may include a liquid propane inlet port 230 and a vaporized propane outlet port 240. Similarly, the liquid bath vaporizer 220 may have a vaporizer liquid heat inlet port 250 and a vaporizer liquid heat outlet port 260. A heat exchange fluid 270 may flow through the vaporizer liquid heat inlet port 250 and the vaporizer liquid heat outlet port 260. The heat exchange fluid 270 may be water, glycol, oil, or the like (including mixtures thereof). A stream of liquid propane 110 is heated and vaporized in liquid bath vaporizer 220 by heat exchange with heat exchange fluid 270 into a stream of vaporized propane gas 125. Other components and configurations may be used herein.

[0019] The heat recovery loop 210 may include an air cooler 280 in communication with the liquid bath vaporizer 220. The air cooler 280 may be a heat exchanger for exchanging heat between the flow of heat exchange fluid 270 and the flow of compressor discharge air 55 from the compressor 15. The air cooler 280 may include a cooler liquid heat inlet port 290 and a cooler liquid heat outlet port 300 for the heat exchange fluid 270. Similarly, the air cooler 280 may have a compressor discharge inlet port 310 and a compressor discharge outlet port 320. The flow of compressor discharge air 55 heats the heat exchange fluid 270 for use in the liquid bath vaporizer 220. Other components and configurations may be used herein.

[0020] The vaporization circuit 200 and the heat recovery loop 210 may have several fuel gas cleanup components 330. The vaporization circuit 200 may include a knock-out drum 340. The knock-out drum 340 may be of conventional design and may remove condensed liquids and the like from the vaporized stream of propane gas 125. In the illustrated embodiment, the knock-out drum 340 is downstream from the liquid tank vaporizer 220. The heat recovery loop 210 may include a scrubber 350 and any number of filters 360, such as a coalescing filter, located upstream of the combustor cans 25. The scrubber 350 and the filter 360 may be of conventional design and may remove impurities and liquid particles from the stream of vaporized propane gas 125.

[0021] The vaporization circuit 200 and the heat recovery loop 210 may meet at a gas / air mixer 370. The gas / air mixer 370 may be of conventional design and may mix the flow of vaporized propane gas 125 with the flow of compressor discharge air 55 before entering the combustor 25. The gas / air mixer 370 may receive the vaporized propane gas 125 from either the thermal energy storage tank 140 or the liquid tank vaporizer 220. One or more booster compressors 380 may likewise be used to boost the flow of compressor discharge air 55. The booster compressors 380 may be of conventional design. Other components and configurations may be used herein.

[0022] In the filled state, thermal energy storage tank 140 may be filled with liquid propane 110 under pressure and heated. For example, liquid propane 110 may be pressurized at approximately 600 psig and heated to a saturation temperature of approximately 210° F. (approximately 98.9° C.) via heater 175, via circulation through liquid tank vaporizer 220 in vaporization circuit 200, or by other means. Thermal energy storage tank 140 may then be isolated with respective valves 170 closed.

[0023] At the beginning of a cold start, the gas turbine engine 10 begins a cold acceleration cycle to part speed, and the liquid bath vaporizer 220 can begin a warm-up cycle. When a "ready to launch" signal is received, the booster compressor 380 provides compressor discharge air 55, and the thermal energy storage tank 140 releases vaporized propane gas 125 from the flash evaporation of the hot liquid, providing the vaporized propane gas 125 to the gas / air mixer 370. After mixing and decompression, the gas mixture may be significantly above its dew point condition.

[0024] When the gas pressure at the top of the thermal energy storage tank 140 drops below the saturation pressure, the latent heat of the liquid propane 110 quickly causes a sufficient amount of evaporation. Because the thermal energy storage tank 140 is still isolated from the liquid propane storage tank 120, the thermal energy storage tank 140 can provide a fuel supply to the gas turbine engine 10 for a significant period of time (15-25 minutes). As the stored liquid propane 110 in the thermal energy storage tank 140 is depleted, the pressure decreases at a steady rate until the pressure is no longer sufficient for the combustor 25. At that point, the valve 170 on the thermal energy storage tank 140 may be closed, and the liquid tank vaporizer 220 begins supplying fuel to the combustor 25. Similarly, the heat recovery loop 210 may be activated when the compressed air flow through the air cooler 280 begins operating. Waste heat from the compressor discharge air 55 flow is transferred to the liquid tank vaporizer 220. This process helps accelerate the warm-up of the liquid bath vaporizer 220 to a predetermined operating temperature while reducing fuel consumption therein.

[0025] Once the liquid bath vaporizer 220 is warmed up and ready to take over the fuel supply, the liquid propane pumps 180, 190 begin flow through the liquid bath vaporizer 220. The inlet valve 170 on the thermal energy storage tank 140 opens to fill the thermal energy storage tank 140, which is at ambient temperature, with liquid propane 110. Once the thermal energy storage tank 140 is full, the inlet valve 170 may close and an electric jug heater 175 inside the thermal energy storage tank 140 can gradually increase the temperature and pressure of the liquid propane 110 to fill the thermal energy storage tank 140.

[0026] Thus, the liquid propane fast start system 105 maintains the liquid propane 110 in the thermal energy storage tank 140 in an over-pressurized and heated state. The pressure in the thermal energy storage tank 140 may be significantly higher than the required gas turbine supply pressure. In this manner, a pressure drop in the thermal energy storage tank 140 causes a rapid, near-instantaneous evaporation of a sufficient amount of the liquid propane 110 for starting, ramping up, and continued operation of the gas turbine engine 10 until the liquid bath vaporizer 220 can safely take over and operate in steady-state mode. Similarly, the heat recovery loop 210 connects the liquid bath vaporizer 220 with an air cooler 280 to reduce fuel consumption in the liquid bath vaporizer 220 and accelerate warm-up in fast start mode.

[0027] Thus, the liquid propane fast start system 105 may be applied to gas turbine engines 10 where a liquid fuel combustor is unavailable or undesirable, liquid backup fuel capability is still needed, and fast start is also a requirement. As described below, the alternative fuel fast start system 100 is described primarily in the context of liquid propane 110, but the system 105 may also be applicable to other liquid fuels that have relatively flat latent heat or phase change curves (i.e., approximately similar bubble and dew points).

[0028] 4 and 5 illustrate an alternative fuel fast start system 100 that may be described herein for use with, for example, a gas turbine engine 10. Specifically, in this example, an ethanol fast start system 400 is shown. The ethanol fast start system 400 may deliver a flow of ethanol 410 in vaporized form to the combustor 25, such as during a fast start of the gas turbine engine 10. The ethanol fast start system 400 and similar systems are also applicable for use with methanol and similar types of fuels having fewer carbon atoms. For simplicity, reference is made to the alternative system 400 as an "ethanol fast start system," although methanol or other similar fuels may be used in place of ethanol.

[0029] The ethanol fast start system 400 may include an ethanol storage tank 420. The ethanol storage tank 420 may contain a quantity of ethanol 410 therein. The ethanol storage tank 420 may have any suitable size, shape, or configuration. The ethanol fast start system 400 may include a thermal energy storage tank 140. As described above, the thermal energy storage tank 140 may store a quantity of heated ethanol 410 under pressure. Similarly, the thermal energy storage tank 140 has an inlet port 150, an outlet port 160, and a number of valves 170. The ethanol storage tank 420 and the inlet port 150 of the thermal energy storage tank 140 may be in communication via a transfer pump 180 and a high-pressure pump 190. Other components and configurations may be used herein.

[0030] The ethanol fast start system 400 may include a vaporization circuit 200 having a liquid bath vaporizer 220. The liquid bath vaporizer 220 may heat a stream of ethanol 410 via heat exchange with the heat recovery loop 210 as described above, or via any other source of heat exchange fluid 270. The vaporization circuit 200 may also include a liquid bath superheater 430. Similar to the liquid bath vaporizer 220, the liquid bath superheater 430 may be a heat exchanger in communication with the heat recovery loop 210 as described above, or any other source of heat exchange fluid 270. The liquid bath superheater 430 further raises the temperature of the stream of ethanol 410 to the required minimum superheat level. Other components and configurations may be used herein.

[0031] The ethanol fast start system 400 may include a passive superheater and buffer 440 disposed between the thermal energy storage tank 140 and the combustor 25. As shown in FIG. 5 , the passive superheater and buffer 440 may include a storage tank 450 and a heat exchanger 460. A recirculation pump 470 may be used to recirculate 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. Similarly, the heat exchanger 460 and the storage tank 450 act as a buffer during the release of vaporized ethanol 410 during start-up, and the heat exchanger 460 exchanges heat between the vapor and liquid streams of ethanol 410. Other components and configurations may be used herein.

[0032] Thus, the ethanol fast start system 400 maintains an over-pressurized state of ethanol 410 in the thermal energy storage tank 140. The pressure in the thermal energy storage tank 140 may be significantly higher than the required gas turbine supply pressure. In this manner, a drop in pressure in the thermal energy storage tank 140 causes a rapid, near-instantaneous evaporation of a sufficient amount of liquid ethanol 410 for start-up, power ramp-up, and continuous operation of the gas turbine engine 10 until the liquid bath vaporizer 220 can safely take over and operate in a steady-state mode.

[0033] It should be apparent that the foregoing relates to only some embodiments of the present application and the resulting patent. Numerous changes and modifications may be made herein by those skilled in the art without departing from the general spirit and scope of the invention as defined by the following claims and their equivalents.

[0034] Further aspects of the invention are provided by the subject matter of the following clauses.

[0035] 1. An alternative fuel fast start system for a gas turbine engine having a combustor and a compressor, comprising: an alternative liquid fuel; a thermal energy storage tank, wherein the alternative liquid fuel is stored in the thermal energy storage tank under pressure such that releasing the alternative liquid fuel from the thermal energy storage tank vaporizes the alternative liquid fuel; and a vaporizer, wherein when the gas turbine engine starts, the thermal energy storage tank supplies vaporized alternative fuel to the combustor until the vaporizer is operational.

[0036] 2. An alternative fuel fast start system as described in clause 1, further comprising an alternative liquid fuel storage tank.

[0037] 3. An alternative fuel fast start system as described in any one of clauses 1 to 2, wherein the thermal energy storage tank and the alternative liquid fuel storage tank are in communication via one or more pumps.

[0038] 4. An alternative fuel fast start system as described in any one of clauses 1 to 3, wherein the vaporizer includes a liquid reservoir vaporizer for transferring heat between the alternative liquid fuel and a heat exchange liquid.

[0039] 5. The alternative fuel fast start system of any one of clauses 1 to 4, further comprising a heat recovery loop in communication with the discharge from the compressor.

[0040] 6. An alternative fuel fast start system as described in any one of clauses 1 to 5, wherein the heat recovery loop includes an air cooler in communication with the vaporizer.

[0041] 7. The alternative fuel fast start system of any one of clauses 1 to 6, further comprising a gas / air mixer in communication with vaporized alternative fuel from the thermal energy storage tank and with an exhaust from the heat recovery loop.

[0042] 8. The alternative fuel fast start system of any one of clauses 1-7, further comprising a fuel gas cleanup component in communication with vaporized alternative fuel from the thermal energy storage tank.

[0043] 9. An alternative fuel fast start system as described in any one of clauses 1 to 8, wherein the alternative fuel comprises propane.

[0044] 10. An alternative fuel fast start system as described in any one of clauses 1 to 9, wherein the alternative fuel comprises ethanol or methanol.

[0045] 11. The alternative fuel fast start system of any one of clauses 1 to 10, further comprising a liquid bath superheater downstream of the vaporizer.

[0046] 12. The alternative fuel fast start system of any one of clauses 1 to 11, further comprising a passive superheater disposed between the thermal energy storage tank and the combustor.

[0047] 13. An alternative fuel fast start system as described in any one of clauses 1 to 12, wherein the passive superheater comprises a storage tank and a heat exchanger.

[0048] 14. The alternative fuel fast start system of any one of clauses 1 to 13, further comprising a recirculation pump disposed between the thermal energy storage tank and the passive superheater.

[0049] 15. A method for fast starting a gas turbine engine having a combustor and a compressor, the method comprising storing liquid fuel under pressure in a thermal energy storage tank, warming a heat exchange fluid in a heat recovery loop with discharge from the compressor, warming a vaporizer with the heat exchange fluid, vaporizing the liquid fuel by releasing pressure in the thermal energy storage tank, and flowing vaporized fuel from the thermal energy storage tank to the combustor until the vaporizer reaches a predetermined temperature.

[0050] 16. A fast start system for a gas turbine engine having a combustor and a compressor, the fast start system comprising: liquid propane fuel; a thermal energy storage tank, wherein the liquid propane fuel is stored in the thermal energy storage tank under pressure such that releasing the liquid propane fuel from the thermal energy storage tank vaporizes the liquid propane fuel into propane gas fuel; and a liquid tank vaporizer, wherein when the gas turbine engine starts, the thermal energy storage tank supplies vaporized propane gas fuel to the combustor until the liquid tank vaporizer is operational.

[0051] 17. The fast start system of clause 16, further comprising a liquid propane fuel storage tank.

[0052] 18. A fast start system as described in any one of clauses 16-17, further comprising a heat recovery loop in communication with the discharge from the compressor.

[0053] 19. A fast start system as described in any one of clauses 16 to 18, wherein the heat recovery loop comprises an air cooler in communication with the liquid bath vaporizer.

[0054] 20. The fast start system of any one of clauses 16-19, further comprising a gas / air mixer in communication with vaporized propane gas fuel from the thermal energy storage tank and with an exhaust from the heat recovery loop. [Explanation of symbols]

[0055] 10. Gas Turbine Engine 15 Compressor 20. Air 25 Combustor can 30 fuel 35 Combustion Gas 40 Turbine 45 shaft 50 External Load 55 Compressor discharge air 100 Alternative Fuel Fast Start System 105 Liquid Propane Fast Start System 110 Liquid Propane 115 Other types of alternative fuels 120 Liquid Propane Storage Tank 125 vaporized propane gas 140 Thermal Energy Storage Tank 150 inlet port 160 Exit Port 170 Valve 175 Electric mug heater 180 Transfer Pump 190 High-pressure pump 200 Vaporization Circuit 210 Heat Recovery Loop 220 Liquid Tank Vaporizer 230 Liquid Propane Inlet Port 240 vaporized propane outlet port 250 Vaporizer Liquid Heat Inlet Port 260 Vaporizer liquid heat outlet port 270 Heat exchange fluid 280 Air Cooler 290 Cooler liquid heat inlet port 300 Cooler liquid heat outlet port 310 Compressor discharge inlet port 320 Compressor discharge outlet port 330 Fuel Gas Purification Components 340 Knockout Drum 350 Cleaner 360 Filter 370 Gas / Air Mixer 380 Booster Compressor 400 Ethanol Fast Start System 410 Ethanol 420 Ethanol Storage Tank 430 Liquid tank superheater 440 Passive Superheaters and Buffers 450 storage tank 460 heat exchanger 470 Recirculation Pump

Claims

1. An alternative fuel fast start system (100, 400) for a gas turbine engine (10) having a combustor (25) and a compressor (15), comprising: an alternative liquid fuel (110, 115, 410); a thermal energy storage tank (140) in which the alternative liquid fuel (110, 115, 410) is stored under pressure such that releasing the alternative liquid fuel (110, 115, 410) from the thermal energy storage tank (140) vaporizes the alternative fuel (110, 115, 410); a vaporizer (220), wherein when the gas turbine engine (10) starts, the thermal energy storage tank (140) supplies the vaporized alternative fuel (125) to the combustor (25) until the vaporizer (220) is operating; An alternative fuel fast start system (100, 400) comprising:

2. The alternative fuel fast start system (100, 400) of claim 1, further comprising an alternative liquid fuel storage tank (120, 420).

3. The alternative fuel fast start system (100, 400) of claim 2, wherein the thermal energy storage tank (140) and the alternative liquid fuel storage tank (120, 420) are in communication via one or more pumps (180, 190).

4. 2. The alternative fuel fast start system of claim 1, wherein the vaporizer comprises a liquid bath vaporizer for transferring heat between the alternative liquid fuel and a heat exchange liquid.

5. The alternative fuel fast start system (100, 400) of claim 1, further comprising a heat recovery loop (210) in communication with a discharge (55) from the compressor (15).

6. The alternative fuel fast start system (100, 400) of claim 5, wherein the heat recovery loop (210) comprises an air cooler (280) in communication with the vaporizer (220).

7. 6. The alternative fuel fast start system (100, 400) of claim 5, further comprising a gas / air mixer (370) in communication with the vaporized alternative fuel (125) from the thermal energy storage tank (140) and the exhaust (55) from a heat recovery loop (210).

8. The alternative fuel fast start system (100, 400) of claim 1, further comprising a fuel gas cleanup component (330) in communication with the vaporized alternative fuel (125) from the thermal energy storage tank (140).

9. The alternative fuel fast start system (100, 400) of claim 1, wherein the alternative liquid fuel (110, 115, 410) comprises propane (110).

10. The alternative fuel fast start system (100, 400) of claim 1, wherein the alternative liquid fuel (110, 115, 410) comprises ethanol (410) or methanol (115).

11. The alternative fuel fast start system (100, 400) of claim 10, further comprising a liquid bath superheater (430) downstream of the vaporizer (220).

12. The alternative fuel fast start system (100, 400) of claim 10, further comprising a passive superheater (440) disposed between the thermal energy storage tank (140) and the combustor (25).

13. The alternative fuel fast start system (100, 400) of claim 12, wherein the passive superheater (440) comprises a storage tank (450) and a heat exchanger (460).

14. The alternative fuel fast start system (100, 400) of claim 12, further comprising a recirculation pump (470) disposed between the thermal energy storage tank (140) and the passive superheater (440).

15. A method for fast starting a gas turbine engine (10) having a combustor (25) and a compressor (15), comprising: Storing liquid fuel (110, 115, 410) under pressure in a thermal energy storage tank (140); warming a heat exchange fluid (270) in a heat recovery loop (210) with the discharge (55) from the compressor (15); warming the vaporizer (220) with the heat exchange fluid (270); vaporizing the liquid fuel (110, 115, 410) by releasing the pressure in the thermal energy storage tank (140); flowing the vaporized fuel (125) from the thermal energy storage tank (140) to the combustor (25) until the vaporizer (220) reaches a predetermined temperature; A method comprising:

16. A fast start system (105) for a gas turbine engine (10) having a combustor (25) and a compressor (15), comprising: liquid propane fuel (110); a thermal energy storage tank (140) in which the liquid propane fuel (110) is stored under pressure such that upon release of the liquid propane fuel (110) from the thermal energy storage tank (140), the liquid propane fuel (110) vaporizes into vaporized propane gas fuel (125); a liquid tank vaporizer (220), wherein when the gas turbine engine (10) starts, the thermal energy storage tank (140) supplies the vaporized propane gas fuel (125) to the combustor (25) until the liquid tank vaporizer (220) is operating; A fast start system (105) comprising:

17. The fast start system (105) of claim 16, further comprising a liquid propane fuel storage tank (120).

18. The fast start system (105) of claim 16, further comprising a heat recovery loop (210) in communication with a discharge (55) from the compressor (15).

19. The fast start system (105) of claim 18, wherein the heat recovery loop (210) comprises an air cooler (280) in communication with the liquid bath vaporizer (220).

20. 20. The fast start system (105) of claim 18, further comprising a gas / air mixer (370) in communication with the vaporized propane gas fuel (125) from the thermal energy storage tank (140) and the exhaust (55) from the heat recovery loop (210).

Images