US20130305738A1 - System and method for producing hydrogen rich fuel - Google Patents
System and method for producing hydrogen rich fuel Download PDFInfo
- Publication number
- US20130305738A1 US20130305738A1 US13/473,990 US201213473990A US2013305738A1 US 20130305738 A1 US20130305738 A1 US 20130305738A1 US 201213473990 A US201213473990 A US 201213473990A US 2013305738 A1 US2013305738 A1 US 2013305738A1
- Authority
- US
- United States
- Prior art keywords
- fuel
- compressor
- turbine
- working fluid
- compressed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Images
Classifications
-
- 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
-
- 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
-
- C—CHEMISTRY; METALLURGY
- C01—INORGANIC CHEMISTRY
- C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
- C01B3/00—Hydrogen; Gaseous mixtures containing hydrogen; Separation of hydrogen from mixtures containing it; Purification of hydrogen
- C01B3/02—Production of hydrogen or of gaseous mixtures containing a substantial proportion of hydrogen
- C01B3/32—Production of hydrogen or of gaseous mixtures containing a substantial proportion of hydrogen by reaction of gaseous or liquid organic compounds with gasifying agents, e.g. water, carbon dioxide, air
- C01B3/34—Production of hydrogen or of gaseous mixtures containing a substantial proportion of hydrogen by reaction of gaseous or liquid organic compounds with gasifying agents, e.g. water, carbon dioxide, air by reaction of hydrocarbons with gasifying agents
- C01B3/38—Production of hydrogen or of gaseous mixtures containing a substantial proportion of hydrogen by reaction of gaseous or liquid organic compounds with gasifying agents, e.g. water, carbon dioxide, air by reaction of hydrocarbons with gasifying agents using catalysts
-
- 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
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- 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
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- C—CHEMISTRY; METALLURGY
- C01—INORGANIC CHEMISTRY
- C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
- C01B2203/00—Integrated processes for the production of hydrogen or synthesis gas
- C01B2203/02—Processes for making hydrogen or synthesis gas
- C01B2203/0205—Processes for making hydrogen or synthesis gas containing a reforming step
- C01B2203/0227—Processes for making hydrogen or synthesis gas containing a reforming step containing a catalytic reforming step
-
- C—CHEMISTRY; METALLURGY
- C01—INORGANIC CHEMISTRY
- C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
- C01B2203/00—Integrated processes for the production of hydrogen or synthesis gas
- C01B2203/80—Aspect of integrated processes for the production of hydrogen or synthesis gas not covered by groups C01B2203/02 - C01B2203/1695
- C01B2203/84—Energy production
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2210/00—Working fluids
- F05D2210/20—Properties
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- General Health & Medical Sciences (AREA)
- Inorganic Chemistry (AREA)
- Health & Medical Sciences (AREA)
- General Chemical & Material Sciences (AREA)
- Hydrogen, Water And Hydrids (AREA)
- Liquid Carbonaceous Fuels (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
A system for providing hydrogen enriched fuel includes first and second gas turbines. The second gas turbine receives a fuel from a fuel supply and portion of compressed working fluid from the first gas turbine and produces a reformed fuel, and a fuel skid provides fluid communication between a turbine in the second gas turbine and a combustor in the first gas turbine. A method for providing hydrogen enriched fuel includes diverting a portion of a first compressed working fluid from a first compressor to a second compressor and providing a second compressed working fluid from the second compressor. Mixing a first portion of a compressed fuel with the second compressed working fluid in a reformer to produce a reformed fuel, flowing a second portion of the compressed fuel to a second turbine for cooling, and flowing the reformed fuel through the second turbine to cool the reformed fuel.
Description
- The present invention relates generally to an integrated gas turbine system that produces hydrogen rich fuel for subsequent combustion or distribution.
- Gas turbines are widely used in industrial and power generation operations. A typical gas turbine includes an axial compressor at the front, one or more combustors around the middle, and a turbine at the rear. Ambient air enters the compressor, and rotating blades and stationary vanes in the compressor progressively impart kinetic energy to the working fluid (air) to produce a compressed working fluid at a highly energized state. The compressed working fluid exits the compressor and flows to the combustors where it mixes with fuel and ignites to generate combustion gases having a high temperature, pressure, and velocity. The combustion gases expand in the turbine to produce work. For example, expansion of the combustion gases in the turbine may rotate a shaft connected to a generator to produce electricity.
- It is widely known that a leaner fuel-air mixture reduces the nitrous oxides produced from combustion. However, a leaner fuel-air mixture introduces flame instability in the combustor, increasing the chance of a lean blow out (LBO) event that might interrupt service provided by the gas turbine. The addition of hydrogen to the fuel can reduce the occurrence of lean blow out, improve emissions, and enhance the overall operation of most combustors, such as Dry Low NOx (DLN) combustors. Inasmuch as hydrogen is difficult to transport safely, an on-site production capability for the amount of hydrogen needed to supplement the fuel would be desirable. Various methods are known in the art for producing hydrogen on-site. For example, autothermal reformers (ATR) and steam methane reformers (SMR) may be used to produce a hydrogen enriched fuel. In general, these reformers expose a catalyst, such as nickel, to a fuel, such as natural gas, in a high temperature and pressure environment to produce pure hydrogen. As a result, the exothermic catalytic reaction produces a very high temperature exhaust that can present a problem for valves, seals, and other system components. Therefore, an integrated gas turbine system that can produce hydrogen enriched fuel on-site would be useful.
- Aspects and advantages of the invention are set forth below in the following description, or may be obvious from the description, or may be learned through practice of the invention.
- One embodiment of the present invention is a system for providing hydrogen enriched fuel. The system includes a first gas turbine including a first compressor, wherein the first compressor produces a first compressed working fluid, a combustor downstream of the first compressor, a first turbine downstream of the combustor. The system further comprises a second gas turbine. The second gas turbine includes, a second compressor in fluid communication with the first compressor, wherein the second compressor receives a portion of the first compressed working fluid from the first compressor and produces a second compressed working fluid having a higher pressure than the first compressed working fluid. The second gas turbine further includes a fuel compressor in fluid communication with a fuel source and including an inlet and an outlet, wherein the fuel compressor receives a fuel through the inlet from the fuel source at a first pressure and a first temperature and provides a compresses fuel at a higher pressure and a higher temperature than the first pressure and the first temperature. A reformer is positioned downstream of the second compressor and the fuel compressor, wherein the reformer receives the second compressed working fluid and the compressed fuel and produces a reformed fuel. A second turbine is positioned downstream of the reformer, wherein the second turbine receives the reformed fuel and produces a cooled reformed fuel. A fuel skid in fluid communication with the second turbine and the combustor, provides a flow path for the cooled reformed fuel from the second turbine to the combustor.
- Another embodiment of the present invention is a system for providing hydrogen enriched fuel that includes a low pressure compressor, a combustor downstream of the low pressure compressor and a low pressure turbine downstream of the combustor. The low pressure compressor produces a first compressed working fluid. A high pressure compressor is in fluid communication with the low pressure compressor. The high pressure compressor receives a portion of the first compressed working fluid and produces a second compressed working fluid having a higher pressure than the first compressed working fluid. A fuel compressor is downstream from the high pressure compressor and includes an inlet in fluid communication with a fuel source. The fuel compressor receives a fuel from the fuel source through the inlet at a first pressure and a first temperature and compresses the fuel to provide a compressed fuel at a higher pressure and a higher temperature. A reformer is downstream of the high pressure compressor and the fuel compressor. The reformer receives the second compressed working fluid and the compressed fuel produces a reformed fuel. A high pressure turbine is downstream of the reformer. The high pressure turbine receives the reformed fuel and produces a cooled reformed fuel. At least one shaft couples the low pressure compressor, the high pressure compressor, the fuel compressor, the high pressure turbine and the low pressure turbine. A fuel skid is in fluid communication with the combustor and the high pressure turbine and provides a flow path for the cooled reformed fuel from the high pressure turbine to the combustor.
- The present invention also includes a method for providing hydrogen enriched fuel. The method includes diverting a portion of a first compressed working fluid from a first compressor to a second compressor and providing a second compressed working fluid from the second compressor. The method also includes providing a fuel to a fuel compressor at a first pressure and a first temperature and compressing the fuel to a second pressure and a second temperature. A first portion of the compressed fuel is provided to a reformer. A second portion of the compressed fuel flows from the fuel compressor to a second turbine to cool the second turbine. The compressed fuel is mixed with the second compressed working fluid in the reformer to produce a reformed fuel. The reformed fuel flows through the second turbine to provide a cooled reformed fuel, and the cooled reformed fuel flows to a gas turbine combustor.
- Those of ordinary skill in the art will better appreciate the features and aspects of such embodiments, and others, upon review of the specification.
- A full and enabling disclosure of the present invention, including the best mode thereof to one skilled in the art, is set forth more particularly in the remainder of the specification, including reference to the accompanying figures, in which:
-
FIG. 1 provides a simplified block diagram of a system according to one embodiment of the present invention; and -
FIG. 2 provides a simplified block diagram of a system according to an alternate embodiment of the present invention. - Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention.
- Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the present invention without departing from the scope or spirit thereof. For instance, features illustrated or described as part of one embodiment may be used on another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.
- Various embodiments of the present invention utilize an integrated thermodynamic cycle to enhance the overall efficiency of a gas turbine. Specifically, the integrated thermodynamic cycle produces a reformed fuel from catalytic oxidation and recycles energy generated during the catalytic oxidation, thus improving the overall efficiency of the integrated gas turbine system.
-
FIG. 1 shows asystem 10 according to one embodiment of the present invention. As shown, thesystem 10 generally includes a first orprimary gas turbine 12 integrated with a second ormicro-gas turbine 14. The first orprimary gas turbine 12 may include any commercially available machine for combusting fuel to generate power. The second ormicro-gas turbine 14 is generally an order of magnitude smaller than the first orprimary gas turbine 12 and principally functions to reform or partially combust a fuel stream to produce a reformed fuel having enriched levels of hydrogen. Afuel supply 16 may supply afuel 18 to afuel skid 20. Possible fuels supplied to thefuel skid 20 include, for example, blast furnace gas, coke oven gas, natural gas, vaporized liquefied natural gas (LNG), and propane. Thefuel skid 20 provides fluid communication for thefuel 18 to flow between the first andsecond gas turbines - The
first gas turbine 12 generally includes acompressor 22, one ormore combustors 24 downstream of thecompressor 22, and aturbine 26 downstream of thecombustors 24, as is known in the art. A workingfluid 28, such as ambient air, enters thecompressor 22, and rotating blades and stationary vanes in thecompressor 22 progressively impart kinetic energy to the working fluid (air) to produce a first compressed working fluid, designated 30, at a highly energized state. The majority of the first compressed workingfluid 30 exits thecompressor 22 and flows to thecombustors 24 where it mixes with fuel and ignites to generate combustion gases, designated 32, having a high temperature, pressure, and velocity. Thecombustion gases 32 flow to theturbine 26 and expand in theturbine 26 to produce work. - A portion of the first compressed working fluid, designated 34, is diverted from the
compressor 22 and/orcombustors 24 to thesecond gas turbine 14. The diverted portion of the first compressed workingfluid 34 flows to asecond compressor 36 in thesecond gas turbine 14. Rotating blades and stationary vanes in thesecond compressor 36 progressively impart kinetic energy to the diverted portion of the first compressed workingfluid 34 to produce a second compressed working fluid, designated 38. The second compressed workingfluid 38 naturally has a higher pressure and temperature than the diverted portion of the first compressed workingfluid 34. - The second compressed working
fluid 38 exits thesecond compressor 36 and flows to areformer 40 downstream of thesecond compressor 36. Thereformer 40 may comprise a catalyst, combustor, or other similar device known to one of ordinary skill in the art for oxidizing fuel to produce a reformed fuel, designated 42, having increased levels of hydrogen. For example, thereformer 40 may comprise a catalytic partial oxidation (CPOX) converter that uses one or more precious metals as the catalyst. In other embodiments, thereformer 40 may comprise a combustor. - The
fuel supply 16 may provide thefuel 18 to thereformer 40, either directly, through thefuel skid 20 and/or through afuel compressor 44 positioned upstream from thereformer 40 as shown inFIG. 1 . Thefuel compressor 44 may include any compressor known in the art suitable to compress a fuel. Thefuel compressor 44 may also include aninlet 46 and anoutlet 48 downstream from theinlet 46 and in fluid communication with thereformer 40. In particular embodiments, thefuel compressor 44 may receive thefuel 18 at a first temperature and a first pressure. As the fuel flows through thefuel compressor 44, the pressure and temperature increases, thus providing acompressed fuel 50 at a higher temperature and a higher pressure. Thefuel compressor 44 may further include anextraction port 52 downstream from theinlet 46 for extracting at least a portion of the compressedfuel 50 from thefuel compressor 44. - The
reformer 40 mixes the compressedfuel 50 with the second compressed workingfluid 38 and/or catalyst so that the fuel-to-second compressed working fluid (air) has an equivalence ratio (φ) greater than 1, and preferably greater than approximately 2, such as between approximately 2.5 and 6, to ensure a suitable hydrogen content in the reformedfuel 42. As used herein, the equivalence ratio (φ) is defined as the ratio of the fuel-to-air ratio and the stoichiometric fuel-to-air ratio. - Mathematically, the equivalence ratio may be calculated as follows:
-
- where, m represents the mass and the suffix st stands for stoichiometric conditions.
- The
reformer 40 causes the compressedfuel 50 to react with the second compressed workingfluid 38 to consume or scavenge all available oxygen and produce the reformedfuel 42 having a high temperature and pressure. The temperature of the reformedfuel 42 exiting thereformer 40 may be between approximately 1400° F. and 1700° F., and the pressure of the reformedfuel 42 exiting thereformer 40 may be between approximately 300 psi and 400 psi, although the present invention is not limited to any particular temperature range or pressure range for the reformedfuel 42 unless specifically recited in the claims. The hydrogen content in the reformedfuel 42 may be greater than approximately 5%, 10%, or 15% by volume, depending on the particular embodiment and operational needs. - The reformed
fuel 42 flows to asecond turbine 54 downstream of thereformer 40. Thesecond turbine 54 may generally include a high pressure turbine. The reformedfuel 42 expands and cools in thesecond turbine 54 to produce work. Specifically, ashaft 56 may connect thesecond turbine 54 to thesecond compressor 36 to provide a driving engagement between thesecond turbine 54 and thesecond compressor 36. In this manner, the work generated by the expansion of the reformedfuel 42 in thesecond turbine 54 may be used to power, turn, or otherwise operate thefuel compressor 44, thereby enhancing the efficiency of theintegrated system 10. In addition, the work generated by the expansion of the reformedfuel 42 through the second turbine may also be used to power, turn or otherwise operate thesecond compressor 36. - The reformed
fuel 42 exits thesecond turbine 54 as a cooled reformedfuel 58. The temperature of the cooled reformedfuel 58 exiting thesecond turbine 54 may be between approximately 1000° F. and 1400° F., and the pressure of the cooled reformedfuel 58 exiting thesecond turbine 54 may be between approximately 200 psi and 300 psi. In particular embodiments, acoupling 60 may extend from theextraction port 52 of thefuel compressor 44 to thesecond turbine 54, thereby providing fluid communication from thefuel compressor 44 into thesecond turbine 54. In this manner, at least a portion of the compressedfuel 50 may flow from thefuel compressor 44 to thesecond turbine 54. As a result, the compressedfuel 50 may provide additional cooling to thesecond turbine 54, thereby further reducing the temperature of the cooled reformedfuel 58 exiting thesecond turbine 54. In addition, the compressedfuel 50 flowing through thesecond turbine 54 may reduce thermal stresses within thesecond turbine 54, thus increasing the mechanical life of thesecond turbine 54. As a result, the cooled reformedfuel 58 does not require additional cooling or pressure increase before introduction to thecombustors 24. The hydrogen content in the cooled reformedfuel 58 may be greater than approximately 5%, 10%, or 15% by volume, depending on the particular embodiment and operational needs. The present invention is not limited to any particular temperature range or pressure range for the cooled reformedfuel 58 unless specifically recited in the claims. - The
fuel skid 20 provides fluid communication between thesecond turbine 54 and thecombustors 24. As a result, the cooled reformedfuel 58 may flow from thesecond turbine 54 through thefuel skid 20 to thecombustors 24. Thefuel skid 20 may provide the cooled reformedfuel 58 to thecombustors 24 without any further adjustment or mixing. Alternately, or in addition, depending on the operational needs, thefuel skid 20 may mix the cooled reformedfuel 58 with thefuel 18 from thefuel supply 16. The mixing may also occur within amixer 62 downstream from thesecond turbine 54 and upstream from thefuel skid 20 that provides fluid communication between thesecond turbine 54 and thefuel skid 20. In this manner, thefuel skid 20 may provide thefuel 18, cooled reformedfuel 58, and/or a mixture of the two to thecombustors 24. Thecombustors 24 ignite the various fuels provided by thefuel skid 20 to generatecombustion gases 32 which expand in theturbine 26 to produce work, as previously described. As shown inFIG. 1 , thefuel skid 20 may also provide fluid communication between thesecond turbine 54 and an auxiliary process ordevice 64 such as another gas turbine other than thefirst gas turbine 12. This allows thesystem 10 to produce and supply hydrogen enriched fuel to more than one gas turbine at a site -
FIG. 2 shows asystem 100 according to an alternate embodiment of the present invention. As shown, thesystem 100 generally includes amulti-spooled gas turbine 102 having alow pressure compressor 104, ahigh pressure compressor 106, one ormore combustors 108, afuel compressor 110, ahigh pressure turbine 112, and alow pressure turbine 114. At least oneshaft 116 may couple thelow pressure compressor 104, thehigh pressure compressor 106, thefuel compressor 110, thehigh pressure turbine 112 and/or thelow pressure turbine 114. The shaft(s) 116 may be substantially concentric with each subsequent shaft(s) 116. Afuel supply 118 may supply afuel 120 to afuel skid 122. Thefuel skid 122 may provide fluid communication between thehigh pressure turbine 112, thecombustors 108, and/or multipleother gas turbines 124, as will be described. - A working
fluid 126, such as ambient air, enters thelow pressure compressor 104 and rotating blades and stationary vanes (not shown) in thelow pressure compressor 104 progressively impart kinetic energy to the workingfluid 126 to produce a first compressed working fluid, designated 128, at a highly energized state. The majority of the first compressed workingfluid 128 exits thelow pressure compressor 104 and flows to thecombustors 108 where it mixes with thefuel 120 and ignites to generate combustion gases, designated 130, having a high temperature, pressure, and velocity. Thecombustion gases 130 flow to thelow pressure turbine 114 and expand in thelow pressure turbine 114 to produce work. - A portion of the first compressed working
fluid 128 may be diverted from thelow pressure compressor 104 and/or thecombustors 108 to thehigh pressure compressor 106 downstream of thelow pressure compressor 104. Rotating blades and stationary vanes (not shown) in thehigh pressure compressor 106 progressively impart kinetic energy to the diverted portion of the first compressed workingfluid 128 to produce a second compressed working fluid, designated 132. The second compressed workingfluid 132 naturally has a higher pressure and temperature than the diverted portion of the first compressed workingfluid 128. The second compressed workingfluid 132 exits thehigh pressure compressor 106 and flows to areformer 134 downstream of thehigh pressure compressor 106. Thereformer 134 may comprise a catalyst, combustor, or other similar device known to one of ordinary skill in the art for oxidizing fuel to produce a reformed fuel, designated 136, having increased levels of hydrogen. For example, thereformer 134 may comprise a catalytic partial oxidation (CPOX) converter that uses one or more precious metals as the catalyst. In other embodiments, thereformer 134 may comprise a combustor. - The
fuel supply 118 may provide thefuel 120 to thereformer 134, either directly, through thefuel skid 122 and/or through thefuel compressor 110. Thefuel compressor 110 may include any rotatable compressor known in the art suitable to compress a fuel. Thefuel compressor 110 may also include aninlet 138 in fluid communication with thefuel supply 118 and/or thefuel skid 122. In particular embodiments, thefuel compressor 110 may receive thefuel 120 through theinlet 138 at a first temperature and a first pressure. As thefuel 120 flows through thefuel compressor 110, the pressure and temperature increases, thus providing acompressed fuel 140 at a higher temperature and a higher pressure. At least a portion of thecompressed fuel 140 flows from thefuel compressor 110 to thereformer 134. Thefuel compressor 110 may further include anextraction port 142 downstream from theinlet 138 for extracting at least a portion of thecompressed fuel 140 from thefuel compressor 110. - The
reformer 134 mixes thecompressed fuel 140 with the second compressed workingfluid 132 and/or catalyst so that the fuel-to-second compressed working fluid (air) has an equivalence ratio (φ) greater than 1, and preferably greater than approximately 2, such as between approximately 2.5 and 6, to ensure a suitable hydrogen content in the reformedfuel 136. Thereformer 134 causes thecompressed fuel 140 to react with the second compressed workingfluid 132 to consume or scavenge all available oxygen and produce the reformedfuel 136 having a high temperature and pressure. The temperature of the reformedfuel 136 exiting thereformer 134 may be between approximately 1400° F. and 1700° F., and the pressure of the reformedfuel 136 exiting thereformer 134 may be between approximately 300 psi and 400 psi, although the present invention is not limited to any particular temperature range or pressure range for the reformedfuel 136 unless specifically recited in the claims. The hydrogen content in the reformedfuel 136 may be greater than approximately 5%, 10%, or 15% by volume, depending on the particular embodiment and operational needs. - The reformed
fuel 136 flows to thehigh pressure turbine 112 downstream of thereformer 134. The reformedfuel 136 expands and cools in thehigh pressure turbine 112 to produce work. Specifically, the shaft(s) 116 may provide a driving engagement between thehigh pressure turbine 112, thefuel compressor 110, thehigh pressure compressor 106 and thelow pressure compressor 104. In this manner, the work generated by the expansion of the reformedfuel 136 in thehigh pressure turbine 112 may be used to power, turn, or otherwise operate thefuel compressor 110, thehigh pressure compressor 106 and/or thelow pressure compressor 104 thereby enhancing the efficiency of theintegrated system 100. The reformedfuel 136 exits thehigh pressure turbine 112 as a cooled reformedfuel 144. The temperature of the cooled reformedfuel 144 exiting thehigh pressure turbine 112 may be between approximately 1000° F. and 1400° F., and the pressure of the cooled reformedfuel 144 exiting thehigh pressure turbine 112 may be between approximately 200 psi and 300 psi, although the present invention is not limited to any particular temperature range or pressure range for the cooled reformedfuel 144 unless specifically recited in the claims. In particular embodiments, acoupling 146 may extend from theextraction port 142 to thehigh pressure turbine 112, thereby providing fluid communication from thefuel compressor 110 to thehigh pressure turbine 112. In this manner, at least a portion of thecompressed fuel 140 may flow from thefuel compressor 110 to thehigh pressure turbine 112. As a result, thecompressed fuel 140 may provide additional cooling to thehigh pressure turbine 112, thereby further reducing the temperature of the cooled reformedfuel 144 exiting thehigh pressure turbine 112. In addition, thecompressed fuel 140 flowing through thehigh pressure turbine 112 may reduce thermal stresses within thehigh pressure turbine 112, thus increasing the mechanical life of thehigh pressure turbine 112. As a result, the cooled reformedfuel 144 does not require additional cooling or pressure increase before introduction to thecombustors 108. The hydrogen content in the cooled reformedfuel 144 may be greater than approximately 5%, 10%, or 15% by volume, depending on the particular embodiment and operational needs. - The
fuel skid 122 provides fluid communication between thehigh pressure turbine 112 and thecombustors 108. As a result, the cooled reformedfuel 144 may flow from thehigh pressure turbine 112 through thefuel skid 122 to thecombustors 108. Thefuel skid 122 may provide the cooled reformedfuel 144 to thecombustors 108 without any further adjustment or mixing. Alternately, or in addition, depending on the operational needs, thefuel skid 122 may mix the cooled reformedfuel 144 with thefuel 120 from thefuel supply 118. The mixing may also occur within amixer 148 downstream from thehigh pressure turbine 112 and upstream from thefuel skid 122 that provides fluid communication between thehigh pressure turbine 112 and thefuel skid 122. In this manner, thefuel skid 122 may provide thefuel 120, cooled reformedfuel 144, and/or a mixture of the two, designated as 120, 144 to thecombustors 108. Thecombustors 108 ignite the various fuels provided by thefuel skid 122 to generatecombustion gases 130 which expand in thelow pressure turbine 114 to produce work, as previously described. As shown inFIG. 2 , thefuel skid 122 may also provide fluid communication to anothergas turbine 124 other than themulti-spooled gas turbine 102. This allows thesystem 100 to produce and supply hydrogen enriched fuel to more than one gas turbine at a site. In addition or in the alternative, thesystem 10 may provide at least a portion of the hydrogen enriched fuel for use in an auxiliary process ordevice 64 such as another gas turbine. - The systems described and illustrated in
FIGS. 1 and 2 provide a method for providing hydrogen enriched fuel. Specifically, the method may include diverting a portion of a first compressed working fluid from a first compressor to a second compressor. The first compressed working fluid may be further compressed by the second compressor, thus providing a second compressed working fluid. A fuel may be supplied to a fuel compressor at a first pressure and a first temperature where it may be compressed to a second pressure and a second temperature. At least a first portion of the compressed fuel may be diverted to a reformer downstream from the fuel compressor, and a second portion of the compressed fuel may be diverted from the fuel compressor to a second turbine to cool the second turbine. The compressed fuel and the working fluid at the second pressure and temperature may then be mixed in a reformer to produce a reformed fuel. If desired, the equivalence ratio between the compressed fuel and the second compressed working fluid may be greater than 2. The reformed fuel may be produced with hydrogen concentration of greater than 5% by volume. The reformed fuel may then flow into the second turbine to provide a cooled reformed fuel. The cooled reformed fuel may then flow to a gas turbine combustor for combustion. The method may further include mixing the cooled reformed fuel the fuel from the fuel supply, in the fuel skid and/or within a mixer before it is distributed to the combustor. - The systems and methods described in the present invention may provide several commercial advantages over existing technology. For example, integrating the reformer and reforming process into a conventional gas turbine system should increase the overall efficiency of the gas turbine system by allowing work performed by the reforming process to be captured or recycled. Compressing the fuel before it enters the reformer enhances the reaction within the reformer, thereby increasing the efficiency of the process. Cooling the second/high pressure turbine with the compressed fuel decreases the thermal stresses found within the second/high pressure turbine, thereby resulting in increased period between outages. The recycling or capturing of the work from the reforming process allows for the reformed fuel to be cooled, reducing the difficulty and cost associated with transporting or transferring the reformed fuel. In addition, a single reforming process integrated into a gas turbine system may provide sufficient hydrogen enriched fuel for multiple gas turbines at a site. In addition or in the alternative, the
system 10 may provide at least a portion of the hydrogen enriched fuel for use in an auxiliary process ordevice 64 such as another gas turbine. - This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other and examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
Claims (20)
1. A system for providing hydrogen enriched fuel, comprising:
a. a first gas turbine comprising:
i. a first compressor, wherein the first compressor produces a first compressed working fluid;
ii. a combustor downstream of the first compressor;
iii. a first turbine downstream of the combustor;
b. a second gas turbine comprising:
i. a second compressor in fluid communication with the first compressor, wherein the second compressor receives a portion of the first compressed working fluid from the first compressor and produces a second compressed working fluid having a higher pressure than the first compressed working fluid;
ii. a fuel compressor in fluid communication with a fuel source and including an inlet and an outlet, wherein the fuel compressor receives a fuel through the inlet from the fuel source at a first pressure and a first temperature and provides a compressed fuel at a higher pressure and a higher temperature than the first pressure and the first temperature;
iii. a reformer downstream of the second compressor and the fuel compressor, wherein the reformer receives the second compressed working fluid and the compressed fuel and produces a reformed fuel;
iv. a second turbine downstream of the reformer, wherein the second turbine receives the reformed fuel and produces a cooled reformed fuel; and
c. a fuel skid in fluid communication with the second turbine and the combustor, wherein the fuel skid provides a flow path for the cooled reformed fuel from the second turbine to the combustor.
2. The system as in claim 1 , wherein the fuel compressor further comprises an extraction port downstream from the inlet, wherein the extraction port provides fluid communication between the fuel compressor and the second turbine through a coupling.
3. The system of claim 1 , wherein the fuel source is in fluid communication with the fuel skid.
4. The system of claim 1 , further comprising a mixer downstream from the second turbine and upstream from the fuel skid, wherein the mixer provides fluid communication between the fuel source, the second turbine, and the fuel skid.
5. The system as in claim 4 , wherein the mixer provides a flow path for the cooled reformed fuel from the second turbine to at least one of a third gas turbine or an auxiliary process.
6. The system as in claim 4 , wherein the fuel skid provides a flow path for the cooled reformed fuel from the second turbine to at least one of a third gas turbine or an auxiliary process.
7. The system as in claim 1 , wherein the cooled reformed fuel comprises at least 5% by volume hydrogen.
8. The system as in claim 1 , wherein the reformer comprises at least one of a catalyst or a combustor.
9. A system for providing hydrogen enriched fuel, comprising:
a. a low pressure compressor, wherein the low pressure compressor produces a first compressed working fluid;
b. a combustor downstream of the low pressure compressor;
c. a low pressure turbine downstream of the combustor;
d. a high pressure compressor in fluid communication with the low pressure compressor, wherein the high pressure compressor receives a portion of the first compressed working fluid and produces a second compressed working fluid having a higher pressure than the first compressed working fluid;
e. a fuel compressor downstream from the high pressure compressor and including an inlet in fluid communication with a fuel source, wherein the fuel compressor receives a fuel from the fuel source through the inlet at a first pressure and a first temperature and compresses the fuel to provide a compressed fuel at a higher pressure and a higher temperature;
f. a reformer downstream of the high pressure compressor and the fuel compressor, wherein the reformer receives the second compressed working fluid and the compressed fuel produces a reformed fuel;
g. a high pressure turbine downstream of the reformer, wherein the high pressure turbine receives the reformed fuel and produces a cooled reformed fuel;
h. at least one shaft coupling the low pressure compressor, the high pressure compressor, the fuel compressor, the high pressure turbine and the low pressure turbine; and
i. a fuel skid in fluid communication with the combustor and the high pressure turbine, wherein the fuel skid provides a flow path for the cooled reformed fuel from the high pressure turbine to the combustor.
10. The system as in claim 9 , wherein the fuel compressor further comprises an inlet and an extraction port downstream from the inlet, wherein the extraction port provides fluid communication between the fuel compressor and the second turbine through a coupling.
11. The system of claim 9 , wherein the fuel source is in fluid communication with the fuel skid.
12. The system as in claim 9 , wherein the fuel skid mixes the cooled reformed fuel with the fuel supply.
13. The system as in claim 9 , wherein the fuel skid provides a flow path for the cooled reformed fuel from the high pressure turbine to at least one of a third gas turbine or an auxiliary process.
14. The system as in claim 9 , wherein the cooled reformed fuel comprises at least 5% by volume hydrogen.
15. The system as in claim 9 , wherein the reformer comprises at least one of a catalyst or a combustor.
16. A method for providing hydrogen enriched fuel, comprising:
a. diverting a portion of a first compressed working fluid from a first compressor to a second compressor;
b. providing a second compressed working fluid from the second compressor;
c. providing a fuel to a fuel compressor at a first pressure and a first temperature;
d. compressing the fuel to a second pressure and a second temperature;
e. flowing a first portion of the compressed fuel to a reformer;
f. flowing a second portion of the compressed fuel from the fuel compressor to a second turbine to cool the second turbine;
g. mixing and burning the compressed fuel with the second compressed working fluid in the reformer to produce a reformed fuel;
h. flowing the reformed fuel through the second turbine to provide a cooled reformed fuel; and
i. flowing the cooled reformed fuel to a gas turbine combustor.
17. The method as in claim 16 , further comprising coupling the second turbine to the fuel compressor with a shaft.
18. The method as in claim 16 , further comprising mixing the cooled reformed fuel with the fuel.
19. The method as in claim 16 , further comprising mixing and burning the compressed fuel with the second compressed working fluid in the reformer at an equivalence ratio of at least approximately 2.
20. The method as in claim 16 , further comprising providing the reformed fuel with greater than 5% by volume hydrogen.
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/473,990 US20130305738A1 (en) | 2012-05-17 | 2012-05-17 | System and method for producing hydrogen rich fuel |
JP2013101770A JP2013241931A (en) | 2012-05-17 | 2013-05-14 | System and method for producing hydrogen rich fuel |
EP13168027.4A EP2664764B1 (en) | 2012-05-17 | 2013-05-16 | System and method for producing hydrogen rich fuel |
CN201310180817.7A CN103422993B (en) | 2012-05-17 | 2013-05-16 | For producing the system and method for hydrogen-rich fuel |
RU2013122580/06A RU2013122580A (en) | 2012-05-17 | 2013-05-16 | SYSTEM (OPTIONS) AND METHOD FOR CREATING HYDROGEN ENRICHED FUEL |
US15/139,678 US10196976B2 (en) | 2012-05-17 | 2016-04-27 | System and method for producing hydrogen rich fuel |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/473,990 US20130305738A1 (en) | 2012-05-17 | 2012-05-17 | System and method for producing hydrogen rich fuel |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/139,678 Continuation US10196976B2 (en) | 2012-05-17 | 2016-04-27 | System and method for producing hydrogen rich fuel |
Publications (1)
Publication Number | Publication Date |
---|---|
US20130305738A1 true US20130305738A1 (en) | 2013-11-21 |
Family
ID=48446150
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/473,990 Abandoned US20130305738A1 (en) | 2012-05-17 | 2012-05-17 | System and method for producing hydrogen rich fuel |
US15/139,678 Active 2033-06-22 US10196976B2 (en) | 2012-05-17 | 2016-04-27 | System and method for producing hydrogen rich fuel |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/139,678 Active 2033-06-22 US10196976B2 (en) | 2012-05-17 | 2016-04-27 | System and method for producing hydrogen rich fuel |
Country Status (5)
Country | Link |
---|---|
US (2) | US20130305738A1 (en) |
EP (1) | EP2664764B1 (en) |
JP (1) | JP2013241931A (en) |
CN (1) | CN103422993B (en) |
RU (1) | RU2013122580A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20120180497A1 (en) * | 2011-01-13 | 2012-07-19 | General Electric Company | Fuel reformer system for a turbomachine system |
US20180209353A1 (en) * | 2014-08-13 | 2018-07-26 | Siemens Aktiengesellschaft | Power plant with emergency fuel system |
US10196976B2 (en) * | 2012-05-17 | 2019-02-05 | General Electric Company | System and method for producing hydrogen rich fuel |
US20200030720A1 (en) * | 2018-07-30 | 2020-01-30 | Hamilton Sundstrand Corporation | Fuel delivery system |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105041506A (en) * | 2014-06-10 | 2015-11-11 | 摩尔动力(北京)技术股份有限公司 | Internal combustion closed cycle hydrogen fuel heat power system |
US9551278B2 (en) * | 2014-07-16 | 2017-01-24 | Air Products And Chemicals, Inc. | Hydrogen production system and process |
US9874143B2 (en) * | 2015-12-15 | 2018-01-23 | General Electric Company | System for generating steam and for providing cooled combustion gas to a secondary gas turbine combustor |
EP3650757A1 (en) * | 2018-11-08 | 2020-05-13 | Siemens Aktiengesellschaft | Gas turbine and method for operating the same |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5595059A (en) * | 1995-03-02 | 1997-01-21 | Westingthouse Electric Corporation | Combined cycle power plant with thermochemical recuperation and flue gas recirculation |
US5927063A (en) * | 1997-08-19 | 1999-07-27 | Exxon Chemical Patents Inc. | High efficiency reformed methanol gas turbine power plants |
US6463741B1 (en) * | 1999-11-03 | 2002-10-15 | Alstom (Switzerland) Ltd | Method for operating a power plant |
US20070130957A1 (en) * | 2005-12-13 | 2007-06-14 | General Electric Company | Systems and methods for power generation and hydrogen production with carbon dioxide isolation |
US20090158701A1 (en) * | 2007-12-20 | 2009-06-25 | General Electric Company | Systems and methods for power generation with carbon dioxide isolation |
US20100115962A1 (en) * | 2007-01-23 | 2010-05-13 | Russ Fredric S | Methods and systems for gas turbine syngas warm-up with low emissions |
US20120055168A1 (en) * | 2010-09-08 | 2012-03-08 | General Electric Company | System and method for producing hydrogen rich fuel |
US8869502B2 (en) * | 2011-01-13 | 2014-10-28 | General Electric Company | Fuel reformer system for a turbomachine system |
Family Cites Families (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4033133A (en) * | 1976-03-22 | 1977-07-05 | California Institute Of Technology | Start up system for hydrogen generator used with an internal combustion engine |
JPS61106925A (en) | 1984-10-30 | 1986-05-24 | Osaka Gas Co Ltd | Gas turbine |
US5048284A (en) * | 1986-05-27 | 1991-09-17 | Imperial Chemical Industries Plc | Method of operating gas turbines with reformed fuel |
US5103630A (en) * | 1989-03-24 | 1992-04-14 | General Electric Company | Dry low NOx hydrocarbon combustion apparatus |
DK171830B1 (en) * | 1995-01-20 | 1997-06-23 | Topsoe Haldor As | Method for generating electrical energy |
DE19521308A1 (en) * | 1995-06-12 | 1996-12-19 | Siemens Ag | Gas turbine for burning a fuel gas |
DE19536836C2 (en) * | 1995-10-02 | 2003-11-13 | Alstom | Process for operating a power plant |
US6061936A (en) * | 1997-09-12 | 2000-05-16 | Texaco Inc. | Synthesis gas expander located immediately upstream of combustion turbine |
JP2000204965A (en) | 1999-01-14 | 2000-07-25 | Ishikawajima Harima Heavy Ind Co Ltd | Gas turbine generation system using methane gas |
US6322757B1 (en) * | 1999-08-23 | 2001-11-27 | Massachusetts Institute Of Technology | Low power compact plasma fuel converter |
US6269625B1 (en) * | 1999-09-17 | 2001-08-07 | Solo Energy Corporation | Methods and apparatus for igniting a catalytic converter in a gas turbine system |
JP3688550B2 (en) | 2000-04-10 | 2005-08-31 | 株式会社東芝 | Gas turbine system |
JP3789070B2 (en) | 2000-06-16 | 2006-06-21 | 株式会社東芝 | Gas turbine system and operation method thereof |
JP4101627B2 (en) | 2002-12-05 | 2008-06-18 | 関西電力株式会社 | Gas turbine system |
JP2005098255A (en) | 2003-09-26 | 2005-04-14 | Yanmar Co Ltd | Power generating device |
NO20051895D0 (en) * | 2005-04-19 | 2005-04-19 | Statoil Asa | Process for the production of electrical energy and CO2 from a hydrocarbon feedstock |
US20070130956A1 (en) * | 2005-12-08 | 2007-06-14 | Chen Alexander G | Rich catalytic clean burn for liquid fuel with fuel stabilization unit |
US20100175386A1 (en) * | 2009-01-09 | 2010-07-15 | General Electric Company | Premixed partial oxidation syngas generation and gas turbine system |
US8783040B2 (en) * | 2010-02-25 | 2014-07-22 | General Electric Company | Methods and systems relating to fuel delivery in combustion turbine engines |
WO2012099046A1 (en) | 2011-01-21 | 2012-07-26 | 三菱重工業株式会社 | Power generation plant |
US20130305738A1 (en) * | 2012-05-17 | 2013-11-21 | General Electric Company | System and method for producing hydrogen rich fuel |
CN203420787U (en) * | 2013-02-28 | 2014-02-05 | 通用电气公司 | System for operating power equipment |
US20150321155A1 (en) * | 2014-05-12 | 2015-11-12 | General Electric Company | Fuel delivery system and method of operating a power generation system |
US9957900B2 (en) * | 2015-05-11 | 2018-05-01 | General Electric Company | System and method for flow control in turbine |
-
2012
- 2012-05-17 US US13/473,990 patent/US20130305738A1/en not_active Abandoned
-
2013
- 2013-05-14 JP JP2013101770A patent/JP2013241931A/en active Pending
- 2013-05-16 EP EP13168027.4A patent/EP2664764B1/en active Active
- 2013-05-16 CN CN201310180817.7A patent/CN103422993B/en active Active
- 2013-05-16 RU RU2013122580/06A patent/RU2013122580A/en not_active Application Discontinuation
-
2016
- 2016-04-27 US US15/139,678 patent/US10196976B2/en active Active
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5595059A (en) * | 1995-03-02 | 1997-01-21 | Westingthouse Electric Corporation | Combined cycle power plant with thermochemical recuperation and flue gas recirculation |
US5927063A (en) * | 1997-08-19 | 1999-07-27 | Exxon Chemical Patents Inc. | High efficiency reformed methanol gas turbine power plants |
US6463741B1 (en) * | 1999-11-03 | 2002-10-15 | Alstom (Switzerland) Ltd | Method for operating a power plant |
US20070130957A1 (en) * | 2005-12-13 | 2007-06-14 | General Electric Company | Systems and methods for power generation and hydrogen production with carbon dioxide isolation |
US20100115962A1 (en) * | 2007-01-23 | 2010-05-13 | Russ Fredric S | Methods and systems for gas turbine syngas warm-up with low emissions |
US20090158701A1 (en) * | 2007-12-20 | 2009-06-25 | General Electric Company | Systems and methods for power generation with carbon dioxide isolation |
US20120055168A1 (en) * | 2010-09-08 | 2012-03-08 | General Electric Company | System and method for producing hydrogen rich fuel |
US8869502B2 (en) * | 2011-01-13 | 2014-10-28 | General Electric Company | Fuel reformer system for a turbomachine system |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20120180497A1 (en) * | 2011-01-13 | 2012-07-19 | General Electric Company | Fuel reformer system for a turbomachine system |
US8869502B2 (en) * | 2011-01-13 | 2014-10-28 | General Electric Company | Fuel reformer system for a turbomachine system |
US10196976B2 (en) * | 2012-05-17 | 2019-02-05 | General Electric Company | System and method for producing hydrogen rich fuel |
US20180209353A1 (en) * | 2014-08-13 | 2018-07-26 | Siemens Aktiengesellschaft | Power plant with emergency fuel system |
US10590861B2 (en) * | 2014-08-13 | 2020-03-17 | Siemens Aktiengesellschaft | Power plant with emergency fuel system |
US20200030720A1 (en) * | 2018-07-30 | 2020-01-30 | Hamilton Sundstrand Corporation | Fuel delivery system |
US11078846B2 (en) * | 2018-07-30 | 2021-08-03 | Hamilton Sunstrand Corporation | Fuel delivery system |
Also Published As
Publication number | Publication date |
---|---|
CN103422993B (en) | 2016-09-07 |
US20160237893A1 (en) | 2016-08-18 |
JP2013241931A (en) | 2013-12-05 |
RU2013122580A (en) | 2014-11-27 |
EP2664764A2 (en) | 2013-11-20 |
EP2664764A3 (en) | 2018-03-07 |
US10196976B2 (en) | 2019-02-05 |
CN103422993A (en) | 2013-12-04 |
EP2664764B1 (en) | 2020-11-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US10196976B2 (en) | System and method for producing hydrogen rich fuel | |
US8904748B2 (en) | System and method for producing hydrogen rich fuel | |
JP6169840B2 (en) | Method for separating CO2 from N2 and O2 in a turbine engine system | |
US20120204531A1 (en) | High altitude combustion system | |
US8459039B2 (en) | Generating power using an ion transport membrane | |
US20150321155A1 (en) | Fuel delivery system and method of operating a power generation system | |
WO2004101129A2 (en) | NOx REDUCTION MEHOD | |
EP2620621A2 (en) | Gas turbine engine system and method for controlling a temperature of a conduit in a gas turbine engine system | |
US8850825B2 (en) | Generating power using an ion transport membrane | |
CN103133140A (en) | Hydrogen assisted oxy-fuel combustion | |
EP2578840A2 (en) | Power plant with exhaust gas recirculation system | |
US20120204573A1 (en) | System and method for producing a hydrogen enriched fuel | |
US20120180497A1 (en) | Fuel reformer system for a turbomachine system | |
Rabovitser et al. | Development of a partial oxidation gas turbine (POGT) for innovative gas turbine systems | |
Rabovitser et al. | Partial oxidation gas turbine (POGT) cycles,‖ |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:HUGHES, MICHAEL JOHN;BERRY, JONATHAN DWIGHT;SIGNING DATES FROM 20120508 TO 20120510;REEL/FRAME:028226/0671 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |