CA2247197A1 - Hydrogen fueled power plant with recuperation - Google Patents
Hydrogen fueled power plant with recuperation Download PDFInfo
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- CA2247197A1 CA2247197A1 CA002247197A CA2247197A CA2247197A1 CA 2247197 A1 CA2247197 A1 CA 2247197A1 CA 002247197 A CA002247197 A CA 002247197A CA 2247197 A CA2247197 A CA 2247197A CA 2247197 A1 CA2247197 A1 CA 2247197A1
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- Prior art keywords
- steam
- oxygen
- pressurized
- hydrogen
- flow
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/003—Gas-turbine plants with heaters between turbine stages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
- F01K25/005—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for the working fluid being steam, created by combustion of hydrogen with oxygen
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Hydrogen (2) is used as the fuel source in a power plant. The hydrogen (2) is combusted (8) in pure oxygen (1) to produce steam (71), which is then expanded in one or more power turbines (24, 26, 28), with the steam being reheated by further combustion of hydrogen with oxygen between each successive turbine (10, 12). Heat available in the steam discharged from turbines (76) is recuperated (6) by transferring it to the hydrogen and oxygen prior to combustion. Since no hydrocarbon fuel or atmospheric air is used for combustion, Nox generation is eliminated so that the only emission (77) from the power plant is water.
Description
W O 97131184 PCT/U~7,'a2S14 HYDROGEN FlnELED POWER PL~NT WITH ~E ~ PEFi~TION
BACK~ROUnn~ OF THE lNV~l'lON
The present invention relates to a method of burning hydrogen in a turbine power plant. More specifically, the present invention relates to a power plant in which hydrogen is burned in oxygen and in which exhaust heat is recovered by recuperation.
In conventional power plants, a hydrocarbon fuel, such as natural gas or distillate oil, is burned in air to produce a hot gas. In a gas turbine power plant, the hot gas, which is typically pressurized to about lO00-1500 kPa tl50-200 psia), is then expanded in a turbine to produce sha~t power. In a steam turbine power plant, the hot gas transfers heat to feed water so as to generate steam, which is then expanded in a steam turbine to produce shaft power.
In either case, the turbine drives a load, such as an electrical generator or compressor, so as to deliver useful shaft power.
Unfortunately, the combus~ion of hydrocarbon fuel in air results in the formation of oxides of nitrogen ("NOx~), considered an atmospheric pollutant. During combustion, NOx is generated primarily from three sources -- (i) the conversion of atmospheric nitrogen in the combustion air to NOx, typically referred to as "thermal NOx" ~ii) the conversion of organically bound nitrogen compounds, such as HN3 (ammonia) and HCN, in the fuel to NOx, and (iii) the reaction between atmospheric nitrogen and hydrocarbon fragments formed from the breakdown of WO 97~1184 PCT/U~7/~2~14 hydrocarbons in the fuel, typically referred to as "prompt NOx".
Burning hydrogen fuel in pure oxygen would eliminate Nox entirely since there would be no hydrocarbons to create prompt and fuel bound NOx and no atmospheric nitrogen. Combustors for rocket engines have traditionally operated by combusting li~uid hydrogen in liquid oxygen.
However, unlike rocket engines, power plant turbines must operate for extended periods of time without deterioration }O and must make as efficient use as possible of the energy available in the fuel.
It is therefore desirable to provide an efficient method of burning hydrogen fuel in oxygen in a tur~ine power plant, thereby producing shaft power without generating NOx.
SUMMARY OF T~ INVENTION
Accordingly, it is the general object of the current invention to provide an efficient method of burning hydrogen fuel in oxygen in a turbine power plant, thereby producing shaft power without generating NOx.
Briefly, this o~ect, as well as other objects of the current invention, is accomplished in a method of generating rotating shaft power, comprising the steps of:
(i) combusting a flow of pressurized hydrogen in a flow of pressurized oxygen in a combustor, thereby consuming at least a portion ~f the flow of pressurized oxygen and producing a flow of hot pressurized steam, (ii) expanding the flow of hot pressurized steam so as to produce a ~low of at least partially expanded steam, at least a portion o~
the ~r~n~ion being accomplished in a tur~ine, thereby producing shaft power, and (iii) transferring heat from the flow of at least partially expanded steam to at least one of the flows of pressurized hydrogen and pressurized oxygen prior to the combustion thereof.
3~ ~n a preferred embodiment of the invention, the flows of hydrogen and oxygen are pressurized above their critical pressures prior to the combustion thereof, and the W O 97131184 PCTrUS97~02814 step of transferring heat from the flow of expanded steam comprises transferring heat to both the flows of pressurized hydrogen and oxygen.
BRIEF DESCRIPTION OF THE ~RAWINGS
Figure l is a schematic diagram of a first embodiment of the turbine power plant according to the current invention, in which all of the oxygen for combustion of the hydrogen fuel is supplied to the first combustor, after the oxygen has been passed through one or more cooling flow paths.
Figure 2 is a schematic diagram of a second ~mhn~im~nt of the turbine power plant according to the current in~ention, in which only the oxygen necessary for stoichiometric combustion of the hydrogen fuel is supplied to each combustor.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to the drawings, wherein like numerals indicate like elements, there is shown in Figure 1 a schematic diagram of a first embodiment of the hydrogen fueled power plant of the current invention. The primary ~,/.~o~lents of the power plant are an oxygen source l, a hyd~oyen source 2, a recuperator 6, primary, secondary and tertiary combustors 8, 10, and 12, respectively, and high, intermediate and low pressure power turbines 14, 16, and 18, respectively, each of which drives a load (not shown) such as an electric l generator. The turbines are preferably of the conventional type and comprised of a plurality of alternating rows of stationary vanes and rotating blades. The stationary vanes are af~ixed to a cylinder and the rotating blades are affixed to a centrally disposed rotating shaft. The combustors may be of the conventional type u~ed in gas turbines or may be of special design.
Preferably, the oxygen 30 from the oxygen source 1 is at a temperature of approximately 143~K (258~R) or colder so that it is a cryogenic liquid. Preferably, a boost compressor 3 raises the pressure of the oxygen 30 W O 97131184 PCT/U~97/~2~14 above its supercritical pressure, which for oxygen in approximately 4970 kPa (720 psia) and, most preferably to about 34,500 kPa (5000 psia). The pressurized oxygen 32 then flows through the recuperator 6, where it is heated, S preferably to about 540~C (1000~F). Since the oxygen 32 is preferably pressurized above its critical pressure, no change in state accompanies this heating so that the heated oxygen 34 discharged from the recuperator remains in e~sentially the liquid state. ~owever, if sub-critical pressure oxygen, including gaseous oxygen, i~ supplied to the recuperator 6, the heated oxygen 34 will be in the gaseous state.
The recuperator has heat transfer surfaces ~ormed therein that allow heat to flow from low pressure steam 76, discussed further below, to the pressurized oxygen 32 without contact between the oxygen and the steam. The recuperator 6 may be of the shell and tube type, with the pressurized oxygen 32 flowing through finned tubes and the low pressure steam 76 flowing over the tubes.
From the recuperator 6, the heated pre~surized oxygen 34 is divided into three streams 38, 40 and 42.
Oxygen stream 38 flows through a cooling flow path 24 ~ormed in the high pressure turbine 14, where it is used to cool the turbine co...yo~ents so that they are not excessively heated by the hot pressurized steam/oxygen m~xture 71 that f low8 through the high pressure turbine 14.
The turbine components through which the cooling flow path 24 extends may include the rotating blade~ and stationary vanes. Using principleq well known in the art, the blades and vanes have cooling fluid passages ~ormed within ~hem that allow heat transferred to the blades and vanes ~rom the hot steam/oxygen mixture 71 to be subsequently transferred to the oxygen 38 flowing through the cooling path 24, thereby heating the oxygen 38 and cooling the blade~ and vanes. The further heated oxygen 39, which has now been preferably heated to approximately 650~C (1200~~), i~ then diccharged from the cooling flow path 24 and exits W O 97/31184 PCTnUS97/02814 the turbine Similarly, oxygen streams 40 and 42 flow through cooling flow paths 26 and 28 formed in the intermediate and low pressure turbines 16 and 18, respectively.
Preferably, the cooling flow paths 24, 26 and 28 are of the closed loop type so that all of the oxygen 38, 40 and 42 that enters the cooling flow paths is discharged from the turbines 14, 16 and 18. Alternatively, if desired to aid in effective cooling, a certain amount of the oxygen 38, 40 and 42 can be bled from the cooling flow paths 24, 26, and 28 into the steam/oxygen mixtures 71-76 flowing through the tur~ines.
Although in the preferred embodiment, the pressurized oxygen 34 is used as the cooling fluid for the turbine components, the turbine could also be cooled by the pressurized hydrogen 54, either exclusively, or in combination with the oxygen by employing separate oxygen and hy~oyen cooling flow paths through selected turbine components. Alternatively, such cooling may be accomplished by recirculating steam from the recuperator, as discussed hereinafter.
Returning to Figure 1, the streams of further heated pressurized oxygen 39, 41 and 43 discharged from the turbines 14-18 are combined into a flow of oxygen 44, which is then directed to the primary combustor 8.
Preferably, the hydrogen 50 from the hydrogen source 1 is at a temperature of 17~K (30~R) or less so that it is also a cryogenic liquid. Preferably, a boost compressor 4 raises the pressure of the hydrogen 50 above the supercritical pressure, which for hydrogen in approximately 1280 kPa (185 psia) and, most preferably to about 34,500 kPa (5000 psia). The pressurized hydrogen 52 then flows through the recuperator 6 in which it is heated, preferably to about 540~C (1000~F), in a manner similar to the pressurized oxygen 32. Since the hydrogen 32 is preferably press~rized above its critical pressure, no change in state accompanies this heating so that the heated W O 97/31184 PCTrUS97~02814 hydrogen 54 di~charged from the recuperator remains in essentially the liquid state. However, if sub-critical pressure hydrogen, including gaseous hydrogen, is supplied to the recuperator 6, the heated hydrogen 54 will be in the gaseous state.
As in the case of the oxygen 32, the recuperator has heat transfer surfaces formed therein that allow heat to flow from the low pressure steam 76 to the pressurized hydrogen 52 without contact between the hydrogen and the steam.
From the recuperator 6, the heated pressurized hydrogen 54 is divided into three streams 56, 58 and 60, which are directed to the primary, secondary and tertiary combustors 8, lO, and 12, respectively. As discussed below, the pressure of the steam/oxygen mixtures 73-76 flowing through the intermediate and low pressure tur~ines 16 and 18, respectively, is less than that flowing through the high pressure tur~ine 14. Therefore, in the preferred ~mho~;m~nt of the invention, the hydrogen streams 58 and 60 are partially ~Yp~n~ in small power turbines 20 and 22, respectlvely, prior to their introduction into the s~co~y and tertiary combustors 10 and 12. This allows a portion of the energy expended to compress the hydrogen 52 to be recovered as useful work.
In the em~odiment of the invention shown in Figure 1, all of the oxygen 44 necessary for combustion of the three hydrogen steams 56, 58 and 60 in each of the three combustors 8, 10 and 12 is introduced into the primary combustor 8. Consequently, in the primary combustor 8, all of the ~irst portion 56 of the hydrogen fuel is combusted with a portion of the oxygen 44 so that the combustion in the primary combustor 8 may be characterized as oxygen rich/fuel lean. Such combustion prevents the temperature from becoming excessively high, such as might occur if the hydrogen were combusted stoichiometrically.
W O 97131184 PCT/U~97~'~2814 The products of the combustion of the hydrogen and oxygen in the primary combustor 8 are pure water in the form of supercritical steam. Consequently, the primary combustor 8 discharges a hot pressurized gas 71 comprised of a mixture of supercritical steam and oxygen.
Preferably, sufficient hydrogen 56 is combusted in the primary combustor 8 to heat the high pressure steam/oxygen mixture 71 to approximately 1650~C (3000~F).
From the primary combustor 8, the high pressure steam/oxygen mixture 71 is partially expanded to an intermediate pressure in the high pressure turbine 14 so as to produce useful shaft power. In so doing, the temperature of the steam/oxygen mixture 72 is reduced, preferably to about 810~C (1500~F). The intermediate pressure steam/oxygen mixture 72 discharged ~rom the high pressure turbine 14 is then reheated in the secondary combustor 10, in which the second portion 59 of the hydrogen fuel is combusted with a portion of the oxygen in the steam/oxygen mixture 72. Since not all of the r~m~;ning oxygen is consumed in the second combustor lO, the combustion may again be characterized as oxygen rich/fuel lean. The combustion in the secondary combustor lO preferably raising the temperature of the intermediate pressure steam/oxygen mixture back to approximately 1650~C
(3000~F).
The reheated intermediate steam/oxygen mixture 73 from the secondary combustor 10 is then further e~r~n~d to a low pressure in the intermediate pressure turbine 16, thereby producing additional shaft power. In 50 doing, its temperature is again reduced, preferably to about 810~C
~1500~F). The low pressure steam/oxygen mixture 74 discharged from the intermediate pressure turbine 16 is then reheated in the tertiary combustor 12, in which the third portion 57 o~ the hydrogen fuel i5 combusted with the r~m~;ning portion of the oxygen in the steam/oxygen mixture 74, preferably raising the temperature of the low pressure steam/oxygen mixture back to approximately 1650~C (3000~F) W 097/31184 PCTIU~Y7;~2814 Since the oxygen is pre~erably depleted by the combustion in the tertiary combustor 12, this combustion may ~e characterized as stoichiometric and the fluid discharged by the tertiary combustor is essentlally pure steam.
The reheated low pressure steam 75 ~rom the tertiary combustor 12 is then ~urther expanded in the low pressure turbine 18, where its temperature is again reduced, preferably to about 810~C (lS00~F). Thus, the low pressure turbine 18 produces yet more shaft power.
Preferably, the pressure of the ~ n~ed steam 76 discharged ~rom the low pressure turbine 18 i8 at sub-atmospheric pressure, for example, about 7 kPa (1 psia).
Preferably, the total pressure drop experienced by the fluid from the primary combustor 8 to the recuperator 6 is approximately evenly divided among the high, intermediate and low pressure turbines 14, 16 and 18, respectively, so that the expansion ratio in each turbine is the cube root of 3.
Although in the pre~erred embs~;m~nt, the combustion in the tertiary combustor 12 consumes all of the r~m~ i n; ng oxygen, it may be desirable in some circumstance to employ lean combustion in the tertiary combustor 12 as well, so that the fluid discharged from the tertiary combustor will contain some excess oxygen. Moreover, although the emho~;m~t shown in Figure 1 employs three turbines 24, 16 and 18, a greater or lesser number of turbines could also be utilized in order to optimize thermodynamic efficiency and cost.
The steam 76 discharged from low pressure turbine 18 is directed to the recuperator 6, where its temperature is further reduced by transferring heat to the incomi ng flows of cryogenic oxygen and hydrogen 32 and 52, respecti~ely. By transferring heat ~rom the steam exhausting from the low pressure turbine 16 to the oxygen 32 and hydrogen 52 fuel, optimum use is made of the energy input into the cycle, thereby m~ximizing thermal ef~iciency. The temperature of the steam 77 dischar~ed CA 02247l97 l998-08-2l W 097/31184 PCT/US97~al4 from the recuperator 6 will be a function of the temperature and mass flow rate of the incoming steam 76 as well as the inlet and outlet temperatures and flow rates o~
the oxygen and hydrogen. Preferably, the steam 77 will be S sufficiently cooled in the recuperator 6 so that it is condensed. The condensate 77 is then discharged for use as process water or discharged to the environment.
Alternately, the recuperator 6 may only partially cool the steam 76, in which case the partially cooled expanded steam discharged from the recuperator will then be directed to a ~ncer (not shown~.
Thus, according to the current invention, rotating shaft power is efficiently produced without the generation of NOx. Indeed, the only emission from the power plant is pure water, which can be safely discharged to the environment after, at most, a slight cooling.
Figure 2 shows a second embodiment of the current invention. ln this embodiment, oxygen 132 and hydrogen 152 ~ are supplied by oxygen and hydrogen sources 101 and 102, respectively. Prefera~ly, the oxygen 132 and hydrogen 152 are pressurized above their critical pressures but are not cryogenic -- e.g., ambient temperature and approximately 20,500 kPa ~3000 psia). The oxygen 132 and hydrogen 152 are heated in a recuperator 106 by the transfer of heat ~rom the low ~ressure steam 176, as before. In this embodiment, the oxygen 134 and hydrogen 154 are preferably heated to approximately 260-540~C (500-1000~F).
From the recuperator 6, the heated oxygen 134 and heated hydrogen 154 are each divided into three streams.
The first portion 144 of the oxygen and the first portion of the hydrogen 160 are com~usted in a primary combustor 108. However, in this em~odiment, the combustion is carried out essentially stoichiometrically so that essentially all of the oxygen 144 is consumed in combusting all of the hyd-oyen 160. As a result, the primary combustor 108 discharges a ~low o~ high pressure ~upercritical essentially pure steam 171 -- i.e., steam at W O 97f31184 PCT/U~7/~2814 a pressure greater than the supercritical pressure of steam, which is approximately 21,840 kPa (3168 psia).
Despite the stoichiometric nature of the combustion, the temperature is prevented from becoming excessive by the introduction of flows of supercritical steam 181 and 188 into the primary combustor 108, as discussed below, that moderate the combustion temperature.
Consequently, the high pressure supercritical steam 171 discharged from the primary combustor 108 is comprised of the steam formed by the combustion of the oxygen 144 and hydrogen 160, as well as the injection of steam 181 and 188. Preferably, the supercritical steam 171 discharged by the primary combustor 108 is at a pressure and temperature of approximately 20,500 kPa (3000 psia) and 1650~C
(3000~F), respectively.
From the primary combustor 108, the high pressure supercritical steam 171 is partially expanded to an intermediate pressure in the high pressure turbine 114 so as to produce useful sha~t power. In so doing, the temperature of the steam is reduced, preferably to a~out 810~C (lSQ0~F). The intermediate pressure steam 172 discharged from the high pressure turbine 114 is then reheated in the secondary combustor 110, in which the second portion 159 of the hydrogen fuel is combusted with the second portion 136 of the oxygen. Again, the combustion in the ~econdary combustor 110 is preferably carried out under essentially stoichiometric conditions 80 that essentially pure intermediate pressure steam 173 is produced. The combustion in the secondary combustor llo preferably raises the temperature of the intermediate pressure steam 173 back to approximately 1650~C (3000~F).
The reheated intermediate pressure steam 173 ~rom the secondary combustor 110 is then ~urther expanded to a low pressure in the intermediate pressure turbine 116, thereby producing additional shaft power. In so doing, its temperature is again reduced, preferably to about 810~C
(1500~F). The low pressure steam 174 discharged from the W O 97131184 PCT~US97/02814 intermediate pressure turbine 116 is then reheated in the tertiary combustor 112, in which the third portion 157 of the hydrogen fuel is combusted with the third portion 135 of the oxygen. Again, the combustion in the tertiary combustor 112 5 is preferably carried out under essentially stoichiometric conditions so that essentially pure low pressure steam 175 is produced. The combustion in the tertiary combustor 112 preferably raises the temperature of the low pressure steam 175 back to approximately 1650~C (3000~F).
The reheated low pres~ure steam 175 from the tertiary combustor 112 is then further expanded in the low pressure turbine 18, where its temperature is again reduced, preferably to about 810~C (1500~F). Thus, the low pressure turbine 118 produces yet more shaft power.
15 Preferably, the pressure of the expanded steam 176 discharged from the low pressure turbine 118 is at sub-atmospheric pressure as before, with the total pressure drop experienced by the fluid being approximately evenly divided among the high, intermediate and low pressure 20 turbines 114, 116 and 118, respectively. Moreover, although the embodiment shown in Figure 2 employs three turbines 14, 16 and 18, a greater or lesser number of turbines could also be utilized, as previously discussed.
The steam 176 discharged from the low pressure 25 turbine 118 is directed to the recuperator 106, where its temperature is further reduced by transferring heat to the incoming flows of oxygen 132 and hydrogen 152, respectively, as before, but also to pressurized water 179, as discussed below. The cooled steam 177 is then directed 30 to a condenser 198. The condensate from the condenser 198 is divided into two steams 178 and 199. The stream 199 is discharged for other uses or to the environment.
The co~n~ate stream 178 is pressurized by a pump 200 to a pressure greater than its critical pressure, 35 and preferably to approximately 20,500 kPa (3000 psia).
Although the pressurized water 179 could be injected W 097/31184 PCT/U~57/~2~14 directly into the primary combustor 108 in order to control the combustion temperature, the pressurized water 179 preferably first flows through the recuperator 106 where its temperature is raised by the transfer of heat from the expanded steam 176. Within the recuperator 106, the water 179 is divided into two streams 180 and 181.
The first stream 180 is discharged from the recuperator 6 as a flow of supercritical steam after having flowed through only a portion of the heat transfer apparatus. Preferably its temperature is raised to approximately 260~C (500~F). The steam 180 discharged from the recuperator 106 is then divided into three streams 182, 184 and 186, each of which flows through one of the cooling flow path~ 124, 126 and 128 formed in the components of the high, intermediate and low pressure turbines 114, 116 and 118, as previously discus9ed. In each of the cooling flow paths, heat is transferred to the steam, preferably raising its temperature to approximately 540~C (1000~F). The streams of heated supercritical steam 183, 185, and 187 discharged from the turbines is then introduced into the primary combustor 108 in order to control the combustion temperature, as previously discussed. Although Figure 2 shows a clo~ed loop turbine steam cooling arrangement, all or a portion of the steam directed to the cooling flow 2S paths 124, 126 and 128 could be discharged directly into the steam flowing through its respective turbine.
The second stream of supercritical steam 181 from the recuperator 106 is discharged after having flowed through the entirety of the heat transfer apparatus so that its temperature is raised beyond that of the steam 180, and preferably to approximately the same temperature as the steam flows 183, 185 and 187 discharged from the tur~ine cooling flow paths 124, 126 and 128 -- i.e., to approximately 540~C (1000~F). From the recuperator 106, the second flow of heated supercritical steam is directed directly to the primary combustor 108.
W O 97131184 PCT~US97~02814 Although in the embodiment shown in Figure 2, the recuperator 106 is located downstream of the low pressure turbine 118, the recuperator could also be advantageously located ups~ream of the low pressure turbine. This would reduce the pressure differential between the flows of pressurized oxygen 132, hydrogen 152 and water 179 flowing through the recuperator 106 on the one hand and the steam 176 flowing through the recuperator on the other hand, thereby reducing the stresses imposed on the heat transfer components. In such an embodiment, the low pressure turbine 118 may be of the condensing type, and the low pressure combustor may be eliminated.
As the foregoing indicates, the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereo~ and, accordingly, reference should be made to the appended claims, rather than to the foregoing specification, as indicating the scope of the invention.
:3~ t~
BACK~ROUnn~ OF THE lNV~l'lON
The present invention relates to a method of burning hydrogen in a turbine power plant. More specifically, the present invention relates to a power plant in which hydrogen is burned in oxygen and in which exhaust heat is recovered by recuperation.
In conventional power plants, a hydrocarbon fuel, such as natural gas or distillate oil, is burned in air to produce a hot gas. In a gas turbine power plant, the hot gas, which is typically pressurized to about lO00-1500 kPa tl50-200 psia), is then expanded in a turbine to produce sha~t power. In a steam turbine power plant, the hot gas transfers heat to feed water so as to generate steam, which is then expanded in a steam turbine to produce shaft power.
In either case, the turbine drives a load, such as an electrical generator or compressor, so as to deliver useful shaft power.
Unfortunately, the combus~ion of hydrocarbon fuel in air results in the formation of oxides of nitrogen ("NOx~), considered an atmospheric pollutant. During combustion, NOx is generated primarily from three sources -- (i) the conversion of atmospheric nitrogen in the combustion air to NOx, typically referred to as "thermal NOx" ~ii) the conversion of organically bound nitrogen compounds, such as HN3 (ammonia) and HCN, in the fuel to NOx, and (iii) the reaction between atmospheric nitrogen and hydrocarbon fragments formed from the breakdown of WO 97~1184 PCT/U~7/~2~14 hydrocarbons in the fuel, typically referred to as "prompt NOx".
Burning hydrogen fuel in pure oxygen would eliminate Nox entirely since there would be no hydrocarbons to create prompt and fuel bound NOx and no atmospheric nitrogen. Combustors for rocket engines have traditionally operated by combusting li~uid hydrogen in liquid oxygen.
However, unlike rocket engines, power plant turbines must operate for extended periods of time without deterioration }O and must make as efficient use as possible of the energy available in the fuel.
It is therefore desirable to provide an efficient method of burning hydrogen fuel in oxygen in a tur~ine power plant, thereby producing shaft power without generating NOx.
SUMMARY OF T~ INVENTION
Accordingly, it is the general object of the current invention to provide an efficient method of burning hydrogen fuel in oxygen in a turbine power plant, thereby producing shaft power without generating NOx.
Briefly, this o~ect, as well as other objects of the current invention, is accomplished in a method of generating rotating shaft power, comprising the steps of:
(i) combusting a flow of pressurized hydrogen in a flow of pressurized oxygen in a combustor, thereby consuming at least a portion ~f the flow of pressurized oxygen and producing a flow of hot pressurized steam, (ii) expanding the flow of hot pressurized steam so as to produce a ~low of at least partially expanded steam, at least a portion o~
the ~r~n~ion being accomplished in a tur~ine, thereby producing shaft power, and (iii) transferring heat from the flow of at least partially expanded steam to at least one of the flows of pressurized hydrogen and pressurized oxygen prior to the combustion thereof.
3~ ~n a preferred embodiment of the invention, the flows of hydrogen and oxygen are pressurized above their critical pressures prior to the combustion thereof, and the W O 97131184 PCTrUS97~02814 step of transferring heat from the flow of expanded steam comprises transferring heat to both the flows of pressurized hydrogen and oxygen.
BRIEF DESCRIPTION OF THE ~RAWINGS
Figure l is a schematic diagram of a first embodiment of the turbine power plant according to the current invention, in which all of the oxygen for combustion of the hydrogen fuel is supplied to the first combustor, after the oxygen has been passed through one or more cooling flow paths.
Figure 2 is a schematic diagram of a second ~mhn~im~nt of the turbine power plant according to the current in~ention, in which only the oxygen necessary for stoichiometric combustion of the hydrogen fuel is supplied to each combustor.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to the drawings, wherein like numerals indicate like elements, there is shown in Figure 1 a schematic diagram of a first embodiment of the hydrogen fueled power plant of the current invention. The primary ~,/.~o~lents of the power plant are an oxygen source l, a hyd~oyen source 2, a recuperator 6, primary, secondary and tertiary combustors 8, 10, and 12, respectively, and high, intermediate and low pressure power turbines 14, 16, and 18, respectively, each of which drives a load (not shown) such as an electric l generator. The turbines are preferably of the conventional type and comprised of a plurality of alternating rows of stationary vanes and rotating blades. The stationary vanes are af~ixed to a cylinder and the rotating blades are affixed to a centrally disposed rotating shaft. The combustors may be of the conventional type u~ed in gas turbines or may be of special design.
Preferably, the oxygen 30 from the oxygen source 1 is at a temperature of approximately 143~K (258~R) or colder so that it is a cryogenic liquid. Preferably, a boost compressor 3 raises the pressure of the oxygen 30 W O 97131184 PCT/U~97/~2~14 above its supercritical pressure, which for oxygen in approximately 4970 kPa (720 psia) and, most preferably to about 34,500 kPa (5000 psia). The pressurized oxygen 32 then flows through the recuperator 6, where it is heated, S preferably to about 540~C (1000~F). Since the oxygen 32 is preferably pressurized above its critical pressure, no change in state accompanies this heating so that the heated oxygen 34 discharged from the recuperator remains in e~sentially the liquid state. ~owever, if sub-critical pressure oxygen, including gaseous oxygen, i~ supplied to the recuperator 6, the heated oxygen 34 will be in the gaseous state.
The recuperator has heat transfer surfaces ~ormed therein that allow heat to flow from low pressure steam 76, discussed further below, to the pressurized oxygen 32 without contact between the oxygen and the steam. The recuperator 6 may be of the shell and tube type, with the pressurized oxygen 32 flowing through finned tubes and the low pressure steam 76 flowing over the tubes.
From the recuperator 6, the heated pre~surized oxygen 34 is divided into three streams 38, 40 and 42.
Oxygen stream 38 flows through a cooling flow path 24 ~ormed in the high pressure turbine 14, where it is used to cool the turbine co...yo~ents so that they are not excessively heated by the hot pressurized steam/oxygen m~xture 71 that f low8 through the high pressure turbine 14.
The turbine components through which the cooling flow path 24 extends may include the rotating blade~ and stationary vanes. Using principleq well known in the art, the blades and vanes have cooling fluid passages ~ormed within ~hem that allow heat transferred to the blades and vanes ~rom the hot steam/oxygen mixture 71 to be subsequently transferred to the oxygen 38 flowing through the cooling path 24, thereby heating the oxygen 38 and cooling the blade~ and vanes. The further heated oxygen 39, which has now been preferably heated to approximately 650~C (1200~~), i~ then diccharged from the cooling flow path 24 and exits W O 97/31184 PCTnUS97/02814 the turbine Similarly, oxygen streams 40 and 42 flow through cooling flow paths 26 and 28 formed in the intermediate and low pressure turbines 16 and 18, respectively.
Preferably, the cooling flow paths 24, 26 and 28 are of the closed loop type so that all of the oxygen 38, 40 and 42 that enters the cooling flow paths is discharged from the turbines 14, 16 and 18. Alternatively, if desired to aid in effective cooling, a certain amount of the oxygen 38, 40 and 42 can be bled from the cooling flow paths 24, 26, and 28 into the steam/oxygen mixtures 71-76 flowing through the tur~ines.
Although in the preferred embodiment, the pressurized oxygen 34 is used as the cooling fluid for the turbine components, the turbine could also be cooled by the pressurized hydrogen 54, either exclusively, or in combination with the oxygen by employing separate oxygen and hy~oyen cooling flow paths through selected turbine components. Alternatively, such cooling may be accomplished by recirculating steam from the recuperator, as discussed hereinafter.
Returning to Figure 1, the streams of further heated pressurized oxygen 39, 41 and 43 discharged from the turbines 14-18 are combined into a flow of oxygen 44, which is then directed to the primary combustor 8.
Preferably, the hydrogen 50 from the hydrogen source 1 is at a temperature of 17~K (30~R) or less so that it is also a cryogenic liquid. Preferably, a boost compressor 4 raises the pressure of the hydrogen 50 above the supercritical pressure, which for hydrogen in approximately 1280 kPa (185 psia) and, most preferably to about 34,500 kPa (5000 psia). The pressurized hydrogen 52 then flows through the recuperator 6 in which it is heated, preferably to about 540~C (1000~F), in a manner similar to the pressurized oxygen 32. Since the hydrogen 32 is preferably press~rized above its critical pressure, no change in state accompanies this heating so that the heated W O 97/31184 PCTrUS97~02814 hydrogen 54 di~charged from the recuperator remains in essentially the liquid state. However, if sub-critical pressure hydrogen, including gaseous hydrogen, is supplied to the recuperator 6, the heated hydrogen 54 will be in the gaseous state.
As in the case of the oxygen 32, the recuperator has heat transfer surfaces formed therein that allow heat to flow from the low pressure steam 76 to the pressurized hydrogen 52 without contact between the hydrogen and the steam.
From the recuperator 6, the heated pressurized hydrogen 54 is divided into three streams 56, 58 and 60, which are directed to the primary, secondary and tertiary combustors 8, lO, and 12, respectively. As discussed below, the pressure of the steam/oxygen mixtures 73-76 flowing through the intermediate and low pressure tur~ines 16 and 18, respectively, is less than that flowing through the high pressure tur~ine 14. Therefore, in the preferred ~mho~;m~nt of the invention, the hydrogen streams 58 and 60 are partially ~Yp~n~ in small power turbines 20 and 22, respectlvely, prior to their introduction into the s~co~y and tertiary combustors 10 and 12. This allows a portion of the energy expended to compress the hydrogen 52 to be recovered as useful work.
In the em~odiment of the invention shown in Figure 1, all of the oxygen 44 necessary for combustion of the three hydrogen steams 56, 58 and 60 in each of the three combustors 8, 10 and 12 is introduced into the primary combustor 8. Consequently, in the primary combustor 8, all of the ~irst portion 56 of the hydrogen fuel is combusted with a portion of the oxygen 44 so that the combustion in the primary combustor 8 may be characterized as oxygen rich/fuel lean. Such combustion prevents the temperature from becoming excessively high, such as might occur if the hydrogen were combusted stoichiometrically.
W O 97131184 PCT/U~97~'~2814 The products of the combustion of the hydrogen and oxygen in the primary combustor 8 are pure water in the form of supercritical steam. Consequently, the primary combustor 8 discharges a hot pressurized gas 71 comprised of a mixture of supercritical steam and oxygen.
Preferably, sufficient hydrogen 56 is combusted in the primary combustor 8 to heat the high pressure steam/oxygen mixture 71 to approximately 1650~C (3000~F).
From the primary combustor 8, the high pressure steam/oxygen mixture 71 is partially expanded to an intermediate pressure in the high pressure turbine 14 so as to produce useful shaft power. In so doing, the temperature of the steam/oxygen mixture 72 is reduced, preferably to about 810~C (1500~F). The intermediate pressure steam/oxygen mixture 72 discharged ~rom the high pressure turbine 14 is then reheated in the secondary combustor 10, in which the second portion 59 of the hydrogen fuel is combusted with a portion of the oxygen in the steam/oxygen mixture 72. Since not all of the r~m~;ning oxygen is consumed in the second combustor lO, the combustion may again be characterized as oxygen rich/fuel lean. The combustion in the secondary combustor lO preferably raising the temperature of the intermediate pressure steam/oxygen mixture back to approximately 1650~C
(3000~F).
The reheated intermediate steam/oxygen mixture 73 from the secondary combustor 10 is then further e~r~n~d to a low pressure in the intermediate pressure turbine 16, thereby producing additional shaft power. In 50 doing, its temperature is again reduced, preferably to about 810~C
~1500~F). The low pressure steam/oxygen mixture 74 discharged from the intermediate pressure turbine 16 is then reheated in the tertiary combustor 12, in which the third portion 57 o~ the hydrogen fuel i5 combusted with the r~m~;ning portion of the oxygen in the steam/oxygen mixture 74, preferably raising the temperature of the low pressure steam/oxygen mixture back to approximately 1650~C (3000~F) W 097/31184 PCTIU~Y7;~2814 Since the oxygen is pre~erably depleted by the combustion in the tertiary combustor 12, this combustion may ~e characterized as stoichiometric and the fluid discharged by the tertiary combustor is essentlally pure steam.
The reheated low pressure steam 75 ~rom the tertiary combustor 12 is then ~urther expanded in the low pressure turbine 18, where its temperature is again reduced, preferably to about 810~C (lS00~F). Thus, the low pressure turbine 18 produces yet more shaft power.
Preferably, the pressure of the ~ n~ed steam 76 discharged ~rom the low pressure turbine 18 i8 at sub-atmospheric pressure, for example, about 7 kPa (1 psia).
Preferably, the total pressure drop experienced by the fluid from the primary combustor 8 to the recuperator 6 is approximately evenly divided among the high, intermediate and low pressure turbines 14, 16 and 18, respectively, so that the expansion ratio in each turbine is the cube root of 3.
Although in the pre~erred embs~;m~nt, the combustion in the tertiary combustor 12 consumes all of the r~m~ i n; ng oxygen, it may be desirable in some circumstance to employ lean combustion in the tertiary combustor 12 as well, so that the fluid discharged from the tertiary combustor will contain some excess oxygen. Moreover, although the emho~;m~t shown in Figure 1 employs three turbines 24, 16 and 18, a greater or lesser number of turbines could also be utilized in order to optimize thermodynamic efficiency and cost.
The steam 76 discharged from low pressure turbine 18 is directed to the recuperator 6, where its temperature is further reduced by transferring heat to the incomi ng flows of cryogenic oxygen and hydrogen 32 and 52, respecti~ely. By transferring heat ~rom the steam exhausting from the low pressure turbine 16 to the oxygen 32 and hydrogen 52 fuel, optimum use is made of the energy input into the cycle, thereby m~ximizing thermal ef~iciency. The temperature of the steam 77 dischar~ed CA 02247l97 l998-08-2l W 097/31184 PCT/US97~al4 from the recuperator 6 will be a function of the temperature and mass flow rate of the incoming steam 76 as well as the inlet and outlet temperatures and flow rates o~
the oxygen and hydrogen. Preferably, the steam 77 will be S sufficiently cooled in the recuperator 6 so that it is condensed. The condensate 77 is then discharged for use as process water or discharged to the environment.
Alternately, the recuperator 6 may only partially cool the steam 76, in which case the partially cooled expanded steam discharged from the recuperator will then be directed to a ~ncer (not shown~.
Thus, according to the current invention, rotating shaft power is efficiently produced without the generation of NOx. Indeed, the only emission from the power plant is pure water, which can be safely discharged to the environment after, at most, a slight cooling.
Figure 2 shows a second embodiment of the current invention. ln this embodiment, oxygen 132 and hydrogen 152 ~ are supplied by oxygen and hydrogen sources 101 and 102, respectively. Prefera~ly, the oxygen 132 and hydrogen 152 are pressurized above their critical pressures but are not cryogenic -- e.g., ambient temperature and approximately 20,500 kPa ~3000 psia). The oxygen 132 and hydrogen 152 are heated in a recuperator 106 by the transfer of heat ~rom the low ~ressure steam 176, as before. In this embodiment, the oxygen 134 and hydrogen 154 are preferably heated to approximately 260-540~C (500-1000~F).
From the recuperator 6, the heated oxygen 134 and heated hydrogen 154 are each divided into three streams.
The first portion 144 of the oxygen and the first portion of the hydrogen 160 are com~usted in a primary combustor 108. However, in this em~odiment, the combustion is carried out essentially stoichiometrically so that essentially all of the oxygen 144 is consumed in combusting all of the hyd-oyen 160. As a result, the primary combustor 108 discharges a ~low o~ high pressure ~upercritical essentially pure steam 171 -- i.e., steam at W O 97f31184 PCT/U~7/~2814 a pressure greater than the supercritical pressure of steam, which is approximately 21,840 kPa (3168 psia).
Despite the stoichiometric nature of the combustion, the temperature is prevented from becoming excessive by the introduction of flows of supercritical steam 181 and 188 into the primary combustor 108, as discussed below, that moderate the combustion temperature.
Consequently, the high pressure supercritical steam 171 discharged from the primary combustor 108 is comprised of the steam formed by the combustion of the oxygen 144 and hydrogen 160, as well as the injection of steam 181 and 188. Preferably, the supercritical steam 171 discharged by the primary combustor 108 is at a pressure and temperature of approximately 20,500 kPa (3000 psia) and 1650~C
(3000~F), respectively.
From the primary combustor 108, the high pressure supercritical steam 171 is partially expanded to an intermediate pressure in the high pressure turbine 114 so as to produce useful sha~t power. In so doing, the temperature of the steam is reduced, preferably to a~out 810~C (lSQ0~F). The intermediate pressure steam 172 discharged from the high pressure turbine 114 is then reheated in the secondary combustor 110, in which the second portion 159 of the hydrogen fuel is combusted with the second portion 136 of the oxygen. Again, the combustion in the ~econdary combustor 110 is preferably carried out under essentially stoichiometric conditions 80 that essentially pure intermediate pressure steam 173 is produced. The combustion in the secondary combustor llo preferably raises the temperature of the intermediate pressure steam 173 back to approximately 1650~C (3000~F).
The reheated intermediate pressure steam 173 ~rom the secondary combustor 110 is then ~urther expanded to a low pressure in the intermediate pressure turbine 116, thereby producing additional shaft power. In so doing, its temperature is again reduced, preferably to about 810~C
(1500~F). The low pressure steam 174 discharged from the W O 97131184 PCT~US97/02814 intermediate pressure turbine 116 is then reheated in the tertiary combustor 112, in which the third portion 157 of the hydrogen fuel is combusted with the third portion 135 of the oxygen. Again, the combustion in the tertiary combustor 112 5 is preferably carried out under essentially stoichiometric conditions so that essentially pure low pressure steam 175 is produced. The combustion in the tertiary combustor 112 preferably raises the temperature of the low pressure steam 175 back to approximately 1650~C (3000~F).
The reheated low pres~ure steam 175 from the tertiary combustor 112 is then further expanded in the low pressure turbine 18, where its temperature is again reduced, preferably to about 810~C (1500~F). Thus, the low pressure turbine 118 produces yet more shaft power.
15 Preferably, the pressure of the expanded steam 176 discharged from the low pressure turbine 118 is at sub-atmospheric pressure as before, with the total pressure drop experienced by the fluid being approximately evenly divided among the high, intermediate and low pressure 20 turbines 114, 116 and 118, respectively. Moreover, although the embodiment shown in Figure 2 employs three turbines 14, 16 and 18, a greater or lesser number of turbines could also be utilized, as previously discussed.
The steam 176 discharged from the low pressure 25 turbine 118 is directed to the recuperator 106, where its temperature is further reduced by transferring heat to the incoming flows of oxygen 132 and hydrogen 152, respectively, as before, but also to pressurized water 179, as discussed below. The cooled steam 177 is then directed 30 to a condenser 198. The condensate from the condenser 198 is divided into two steams 178 and 199. The stream 199 is discharged for other uses or to the environment.
The co~n~ate stream 178 is pressurized by a pump 200 to a pressure greater than its critical pressure, 35 and preferably to approximately 20,500 kPa (3000 psia).
Although the pressurized water 179 could be injected W 097/31184 PCT/U~57/~2~14 directly into the primary combustor 108 in order to control the combustion temperature, the pressurized water 179 preferably first flows through the recuperator 106 where its temperature is raised by the transfer of heat from the expanded steam 176. Within the recuperator 106, the water 179 is divided into two streams 180 and 181.
The first stream 180 is discharged from the recuperator 6 as a flow of supercritical steam after having flowed through only a portion of the heat transfer apparatus. Preferably its temperature is raised to approximately 260~C (500~F). The steam 180 discharged from the recuperator 106 is then divided into three streams 182, 184 and 186, each of which flows through one of the cooling flow path~ 124, 126 and 128 formed in the components of the high, intermediate and low pressure turbines 114, 116 and 118, as previously discus9ed. In each of the cooling flow paths, heat is transferred to the steam, preferably raising its temperature to approximately 540~C (1000~F). The streams of heated supercritical steam 183, 185, and 187 discharged from the turbines is then introduced into the primary combustor 108 in order to control the combustion temperature, as previously discussed. Although Figure 2 shows a clo~ed loop turbine steam cooling arrangement, all or a portion of the steam directed to the cooling flow 2S paths 124, 126 and 128 could be discharged directly into the steam flowing through its respective turbine.
The second stream of supercritical steam 181 from the recuperator 106 is discharged after having flowed through the entirety of the heat transfer apparatus so that its temperature is raised beyond that of the steam 180, and preferably to approximately the same temperature as the steam flows 183, 185 and 187 discharged from the tur~ine cooling flow paths 124, 126 and 128 -- i.e., to approximately 540~C (1000~F). From the recuperator 106, the second flow of heated supercritical steam is directed directly to the primary combustor 108.
W O 97131184 PCT~US97~02814 Although in the embodiment shown in Figure 2, the recuperator 106 is located downstream of the low pressure turbine 118, the recuperator could also be advantageously located ups~ream of the low pressure turbine. This would reduce the pressure differential between the flows of pressurized oxygen 132, hydrogen 152 and water 179 flowing through the recuperator 106 on the one hand and the steam 176 flowing through the recuperator on the other hand, thereby reducing the stresses imposed on the heat transfer components. In such an embodiment, the low pressure turbine 118 may be of the condensing type, and the low pressure combustor may be eliminated.
As the foregoing indicates, the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereo~ and, accordingly, reference should be made to the appended claims, rather than to the foregoing specification, as indicating the scope of the invention.
:3~ t~
Claims (6)
1. A method of generating rotating shaft power having the steps of:
combusting a first flow of pressurized hydrogen (56) in a first flow of pressurized oxygen gas (44) in a first combustor (8), thereby consuming at least a first portion of said first flow of pressurized oxygen gas and producing a first flow of hot pressurized steam (71);
expanding said first flow of hot pressurized steam so as to produce a flow of at least partially expanded steam (72), at least a portion of said expansion being accomplished in a first turbine (14), thereby producing shaft power; and transferring heat from said flow of at least partially expanded steam to at least one of said first flows of pressurized hydrogen and pressurized oxygen gas prior to said combustion thereof; characterized by the step of:
condensing said at least partially expanded steam (176) after said transfer of heat therefrom, so as to produce water (177).
combusting a first flow of pressurized hydrogen (56) in a first flow of pressurized oxygen gas (44) in a first combustor (8), thereby consuming at least a first portion of said first flow of pressurized oxygen gas and producing a first flow of hot pressurized steam (71);
expanding said first flow of hot pressurized steam so as to produce a flow of at least partially expanded steam (72), at least a portion of said expansion being accomplished in a first turbine (14), thereby producing shaft power; and transferring heat from said flow of at least partially expanded steam to at least one of said first flows of pressurized hydrogen and pressurized oxygen gas prior to said combustion thereof; characterized by the step of:
condensing said at least partially expanded steam (176) after said transfer of heat therefrom, so as to produce water (177).
2. The method according to claim 1, further characterized by the steps of:
pressurizing said water (177); and introducing said pressurized water (179) into said first combustor (108) for cooling of said first flow of hot pressurized steam (171) produced by said combustion.
pressurizing said water (177); and introducing said pressurized water (179) into said first combustor (108) for cooling of said first flow of hot pressurized steam (171) produced by said combustion.
3. The method according to claim 1, further characterized by the steps of:
pressurizing said water (177);
transferring heat from said partially expanded steam (176) to said pressurized water (179) so as to produce a flow of cooling steam (181); and introducing said flow of cooling steam into said first combustor (108) for cooling of said first flow of hot pressurized steam (171) produced by said combustion.
pressurizing said water (177);
transferring heat from said partially expanded steam (176) to said pressurized water (179) so as to produce a flow of cooling steam (181); and introducing said flow of cooling steam into said first combustor (108) for cooling of said first flow of hot pressurized steam (171) produced by said combustion.
4. The method according to claim 1, further characterized by the steps of transferring heat from said first turbine (114) to said first flow of pressurized oxygen gas (180), thereby cooling said first turbine and heating said oxygen.
5. The method according to claim 4, further characterized by the steps of transferring heat from said first turbine (114) to said first flow of pressurized oxygen gas (180) comprising flowing at least a portion of said flow of pressurized oxygen gas through said first turbine.
6 The method according to claim 2, further characterized by the steps of flowing at least a portion of said pressurized water (179) through said first turbine (114) to remove heat from said first turbine prior to the step of introducing said pressurized water into said first combustor (108).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US60662896A | 1996-02-26 | 1996-02-26 | |
| US08/606,628 | 1996-02-26 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2247197A1 true CA2247197A1 (en) | 1997-08-28 |
Family
ID=24428772
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002247197A Abandoned CA2247197A1 (en) | 1996-02-26 | 1997-02-25 | Hydrogen fueled power plant with recuperation |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JP2001515556A (en) |
| KR (1) | KR19990087240A (en) |
| CA (1) | CA2247197A1 (en) |
| WO (1) | WO1997031184A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4361419A1 (en) * | 2022-10-24 | 2024-05-01 | Rolls-Royce plc | Gas turbine engine fuel system |
| US12221924B2 (en) | 2022-10-24 | 2025-02-11 | Rolls-Royce Plc | Combined gas turbine engine and fuel cell |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5953900A (en) * | 1996-09-19 | 1999-09-21 | Siemens Westinghouse Power Corporation | Closed loop steam cooled steam turbine |
| JP3051678B2 (en) * | 1996-09-30 | 2000-06-12 | 三菱重工業株式会社 | Low temperature hydrogen combustion turbine |
| US5775091A (en) * | 1996-10-21 | 1998-07-07 | Westinghouse Electric Corporation | Hydrogen fueled power plant |
| US8631658B2 (en) * | 2008-03-07 | 2014-01-21 | Clean Energy Systems, Inc. | Method and system for enhancing power output of renewable thermal cycle power plants |
| US20110030335A1 (en) * | 2009-08-06 | 2011-02-10 | General Electric Company | Combined-cycle steam turbine and system having novel cooling flow configuration |
| GB201213695D0 (en) * | 2012-07-31 | 2012-09-12 | Corbishley Timothy J H | Energy storage system using hydrostatically pressurised gasses to provide gas transmission,heat energy recovery and or condensing |
| ES2715401T3 (en) | 2014-02-04 | 2019-06-04 | James Corbishley | Energy recovery apparatus and method for use in a power generation system |
| JP2016079828A (en) * | 2014-10-10 | 2016-05-16 | 川崎重工業株式会社 | Turbine blade cooling structure and gas turbine engine |
| SE2100028A1 (en) * | 2021-03-01 | 2022-02-23 | Procope Maarten | Utilization of hydrogen and oxygen for explosion engines and heating of buildings etc. |
| DE102021203730A1 (en) * | 2021-04-15 | 2022-10-20 | Siemens Energy Global GmbH & Co. KG | Generation of electrical energy from hydrogen and oxygen |
| EP4083501A1 (en) * | 2021-04-30 | 2022-11-02 | Siemens Energy Global GmbH & Co. KG | Combustion device for combustion of hydrogen and method for carrying out the combustion |
| US11686222B2 (en) | 2021-07-28 | 2023-06-27 | Pratt & Whitney Canada Corp. | Aircraft engine with hydrogen fuel system |
| KR102793753B1 (en) * | 2021-11-05 | 2025-04-08 | 인하대학교 산학협력단 | Combined power generation system and method for generating power using the same |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1000608A (en) * | 1946-03-11 | 1952-02-14 | Rateau Soc | High power gas turbine engine unit with good efficiency at fractional loads |
| US4148185A (en) * | 1977-08-15 | 1979-04-10 | Westinghouse Electric Corp. | Double reheat hydrogen/oxygen combustion turbine system |
-
1997
- 1997-02-25 KR KR1019980706641A patent/KR19990087240A/en not_active Withdrawn
- 1997-02-25 WO PCT/US1997/002814 patent/WO1997031184A1/en not_active Application Discontinuation
- 1997-02-25 JP JP53036397A patent/JP2001515556A/en active Pending
- 1997-02-25 CA CA002247197A patent/CA2247197A1/en not_active Abandoned
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4361419A1 (en) * | 2022-10-24 | 2024-05-01 | Rolls-Royce plc | Gas turbine engine fuel system |
| US12221924B2 (en) | 2022-10-24 | 2025-02-11 | Rolls-Royce Plc | Combined gas turbine engine and fuel cell |
| US12270341B2 (en) | 2022-10-24 | 2025-04-08 | Rolls-Royce Plc | Gas turbine engine fuel system |
Also Published As
| Publication number | Publication date |
|---|---|
| KR19990087240A (en) | 1999-12-15 |
| JP2001515556A (en) | 2001-09-18 |
| WO1997031184A1 (en) | 1997-08-28 |
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