WO1996041990A1 - Katalytische gasturbinenbrenner - Google Patents
Katalytische gasturbinenbrenner Download PDFInfo
- Publication number
- WO1996041990A1 WO1996041990A1 PCT/DE1996/001018 DE9601018W WO9641990A1 WO 1996041990 A1 WO1996041990 A1 WO 1996041990A1 DE 9601018 W DE9601018 W DE 9601018W WO 9641990 A1 WO9641990 A1 WO 9641990A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- gas
- fuel gas
- catalytic
- gas turbine
- combustion
- Prior art date
Links
- 230000003197 catalytic effect Effects 0.000 title claims abstract description 15
- 239000007789 gas Substances 0.000 claims abstract description 34
- 238000007084 catalytic combustion reaction Methods 0.000 claims abstract description 13
- 125000002485 formyl group Chemical class [H]C(*)=O 0.000 claims abstract description 8
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229930195733 hydrocarbon Natural products 0.000 claims abstract description 4
- 150000002430 hydrocarbons Chemical class 0.000 claims abstract description 4
- 239000004215 Carbon black (E152) Substances 0.000 claims abstract description 3
- 239000002737 fuel gas Substances 0.000 claims description 50
- 239000003054 catalyst Substances 0.000 claims description 20
- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 claims description 8
- 229910000510 noble metal Inorganic materials 0.000 claims description 4
- 239000004408 titanium dioxide Substances 0.000 claims description 4
- 229910000314 transition metal oxide Inorganic materials 0.000 claims description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 abstract description 45
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 abstract description 20
- 238000002485 combustion reaction Methods 0.000 abstract description 9
- 239000003345 natural gas Substances 0.000 abstract description 6
- 239000000446 fuel Substances 0.000 abstract description 3
- 239000000126 substance Substances 0.000 abstract description 3
- 239000000567 combustion gas Substances 0.000 abstract 6
- 239000000203 mixture Substances 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 229910052739 hydrogen Inorganic materials 0.000 description 5
- 239000001257 hydrogen Substances 0.000 description 5
- 230000009467 reduction Effects 0.000 description 5
- 238000006722 reduction reaction Methods 0.000 description 5
- 230000005611 electricity Effects 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 239000003638 chemical reducing agent Substances 0.000 description 3
- 150000002431 hydrogen Chemical class 0.000 description 3
- 229910044991 metal oxide Inorganic materials 0.000 description 3
- 150000004706 metal oxides Chemical class 0.000 description 3
- 238000002407 reforming Methods 0.000 description 3
- 239000010948 rhodium Substances 0.000 description 3
- MHOVAHRLVXNVSD-UHFFFAOYSA-N rhodium atom Chemical compound [Rh] MHOVAHRLVXNVSD-UHFFFAOYSA-N 0.000 description 3
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- UQSXHKLRYXJYBZ-UHFFFAOYSA-N Iron oxide Chemical compound [Fe]=O UQSXHKLRYXJYBZ-UHFFFAOYSA-N 0.000 description 2
- KDLHZDBZIXYQEI-UHFFFAOYSA-N Palladium Chemical compound [Pd] KDLHZDBZIXYQEI-UHFFFAOYSA-N 0.000 description 2
- RAHZWNYVWXNFOC-UHFFFAOYSA-N Sulphur dioxide Chemical compound O=S=O RAHZWNYVWXNFOC-UHFFFAOYSA-N 0.000 description 2
- WGLPBDUCMAPZCE-UHFFFAOYSA-N Trioxochromium Chemical compound O=[Cr](=O)=O WGLPBDUCMAPZCE-UHFFFAOYSA-N 0.000 description 2
- XHCLAFWTIXFWPH-UHFFFAOYSA-N [O-2].[O-2].[O-2].[O-2].[O-2].[V+5].[V+5] Chemical compound [O-2].[O-2].[O-2].[O-2].[O-2].[V+5].[V+5] XHCLAFWTIXFWPH-UHFFFAOYSA-N 0.000 description 2
- 229910000420 cerium oxide Inorganic materials 0.000 description 2
- 229910000423 chromium oxide Inorganic materials 0.000 description 2
- AMWRITDGCCNYAT-UHFFFAOYSA-L hydroxy(oxo)manganese;manganese Chemical compound [Mn].O[Mn]=O.O[Mn]=O AMWRITDGCCNYAT-UHFFFAOYSA-L 0.000 description 2
- GKOZUEZYRPOHIO-UHFFFAOYSA-N iridium atom Chemical compound [Ir] GKOZUEZYRPOHIO-UHFFFAOYSA-N 0.000 description 2
- 229910000476 molybdenum oxide Inorganic materials 0.000 description 2
- QGLKJKCYBOYXKC-UHFFFAOYSA-N nonaoxidotritungsten Chemical compound O=[W]1(=O)O[W](=O)(=O)O[W](=O)(=O)O1 QGLKJKCYBOYXKC-UHFFFAOYSA-N 0.000 description 2
- BMMGVYCKOGBVEV-UHFFFAOYSA-N oxo(oxoceriooxy)cerium Chemical compound [Ce]=O.O=[Ce]=O BMMGVYCKOGBVEV-UHFFFAOYSA-N 0.000 description 2
- PQQKPALAQIIWST-UHFFFAOYSA-N oxomolybdenum Chemical compound [Mo]=O PQQKPALAQIIWST-UHFFFAOYSA-N 0.000 description 2
- 229910052697 platinum Inorganic materials 0.000 description 2
- 229910052703 rhodium Inorganic materials 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 229910001930 tungsten oxide Inorganic materials 0.000 description 2
- 229910001935 vanadium oxide Inorganic materials 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 238000003916 acid precipitation Methods 0.000 description 1
- 150000001298 alcohols Chemical class 0.000 description 1
- 150000001335 aliphatic alkanes Chemical class 0.000 description 1
- 229910021529 ammonia Inorganic materials 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 238000010531 catalytic reduction reaction Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 229910000428 cobalt oxide Inorganic materials 0.000 description 1
- IVMYJDGYRUAWML-UHFFFAOYSA-N cobalt(ii) oxide Chemical compound [Co]=O IVMYJDGYRUAWML-UHFFFAOYSA-N 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 125000004435 hydrogen atom Chemical group [H]* 0.000 description 1
- 239000012813 ignitable substance Substances 0.000 description 1
- 229910052741 iridium Inorganic materials 0.000 description 1
- 229910000457 iridium oxide Inorganic materials 0.000 description 1
- 229910052747 lanthanoid Inorganic materials 0.000 description 1
- 150000002602 lanthanoids Chemical class 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000010327 methods by industry Methods 0.000 description 1
- 229910000480 nickel oxide Inorganic materials 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- GNRSAWUEBMWBQH-UHFFFAOYSA-N oxonickel Chemical compound [Ni]=O GNRSAWUEBMWBQH-UHFFFAOYSA-N 0.000 description 1
- 229910052763 palladium Inorganic materials 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 229910003446 platinum oxide Inorganic materials 0.000 description 1
- 229910052761 rare earth metal Inorganic materials 0.000 description 1
- 150000002910 rare earth metals Chemical class 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 229910003450 rhodium oxide Inorganic materials 0.000 description 1
- 238000007086 side reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
-
- 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
- F02C3/26—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 solid or pulverulent, e.g. in slurry or suspension
- F02C3/28—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 solid or pulverulent, e.g. in slurry or suspension using a separate gas producer for gasifying the fuel before combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
Definitions
- the invention relates to a gas turbine for combusting a fuel gas.
- a gas turbine usually consists of a compressor part, a burner part and a turbine part.
- the compressor part and the turbine part are usually located on a common shaft which at the same time drives a generator for generating electricity.
- preheated fresh air is compressed to the pressure required in the burner section.
- the compressed and preheated fresh air is mixed with a fuel, e.g. Natural gas or petroleum, burned.
- the hot burner exhaust gas is fed to the turbine part and expanded there.
- nitrogen oxides NO x When the compressed and preheated fresh air is burned with the fuel gas, nitrogen oxides NO x also form as particularly undesirable combustion products. In addition to sulfur dioxide, these nitrogen oxides are regarded as the main cause of the environmental problem of acid rain. One is therefore - also due to strict legal limit values for NO x emissions - willing to keep the NO x emissions particularly low by a gas turbine and at the same time largely not influence the performance of the gas turbine.
- the reduction in flame temperature in the burner section reduces nitrogen oxide.
- water vapor is added to the fuel gas or the compressed and preheated fresh air or water is injected into the combustion chamber.
- Measures which reduce the nitrogen oxide emissions of the gas turbine per se are referred to as primary measures for reducing nitrogen oxides.
- Recent considerations with regard to the design of the burner part are based on the fact that the diffusion burners or swirl-stabilized premix burners usually used are replaced by a catalytic combustion chamber. With a catalytic combustion chamber, lower nitrogen oxide emissions are achieved than is possible with the above-mentioned burner types. In this way, the known disadvantages of the SCR process (large catalyst volumes, reducing agent consumption, high pressure loss) can be overcome.
- a disadvantage of a catalytic combustion chamber and also a conventional combustion chamber is the ignition temperature necessary for combustion, which in the case of use of natural gas is around 400 ° C. This fact restricts the working range of the combustion chamber in a gas turbine too much and requires the use of an auxiliary burner, which naturally represents a nitrogen oxide source.
- the invention is based, to reduce the ignition temperature and without using an auxiliary burner, even better catalytically convert the part of the fuel gas passed through the catalytic stage.
- a gas turbine is provided for the combustion of a fuel gas, in which a line system is provided such that part of the fuel gas is drawn off, passed through a catalytic stage and then fed back to the fuel gas to lower its ignition temperature, whereby the catalytic stage is a preforming stage which comprises a catalyst system which is provided for converting the hydrocarbon contained in the fuel gas into an alcohol and / or an aldehyde.
- the partial fuel stream withdrawn in the preforming step becomes alcohol in the catalytically easily combustible substances and / or aldehyde decomposed.
- other substances such as hydrogen
- the preformed fuel gas partial stream is fed back to the rest of the fuel gas stream, so that the mixture produced in this way has a lower ignition temperature than is the case with the original fuel gas, such as natural gas.
- the partially oxidized compounds alcohol and aldehyde mentioned additionally lead to a lowering of the ignition temperature and thus to an improved nitrogen oxide reduction in the exhaust gas of a gas turbine compared to the prior art.
- the supply of this preformed fuel gas partial flow for lowering the ignition temperature of the fuel gas is understood on the one hand to mean that the preformed fuel gas partial flow is first supplied to the fuel gas and then mixed with the compressor air. On the other hand, it can also be provided that the preformed fuel gas partial flow is fed to a gas mixture which consists of the compressor air and the remaining fuel gas partial flow.
- the comparatively easy-to-ignite gas mixtures obtained in this way have an ignition temperature in the range from 200 to 350 ° C., depending on the amount of the sub-stream of fuel gas that is drawn off and then preformed.
- the preforming stage in the flow direction of the fuel gas partial stream comprises a preheating device for the fuel gas partial stream.
- the preheating device can be provided in particular if the fuel gas partial stream enters the preforming stage without preheating.
- a temperature of the fuel gas substream at the inlet of the catalyst system which is advantageous for the subsequent preforming in the catalyst system can be approximately 100 ° C.
- the catalyst system comprises a honeycomb and / or plate-shaped catalyst which consists essentially of titanium dioxide TiC> 2 and comprises at least one transition metal oxide and / or at least one noble metal.
- Transition metal oxides are understood in particular to be the oxides of the 3d series and the 4f series (lanthanides, rare earth metals) in the periodic system of the elements.
- Suitable noble metals are in particular rhodium, iridium, palladium, platinum.
- Molybdenum oxide, tungsten oxide, vanadium oxide, chromium oxide, iron oxide, cerium oxide, manganese oxide, nickel oxide and cobalt oxide are particularly suitable.
- metal oxides of the spin type of the aforementioned metals and metal oxides can also be used.
- a solution which is particularly advantageous in terms of process engineering provides for a maximum of 25% by volume of the fuel gas to be drawn off and then passed over the preforming stage. This limitation defines a preferred range in which the effort (catalyst volume) is balanced with respect to the benefit (catalytic ignition temperature reduction).
- FIG. 1 shows a schematic illustration of a gas turbine 2 with a line system 4 for achieving a comparatively low catalytic ignition temperature of a fuel gas 6.
- the gas turbine consists of a compressor part 8, a catalytic combustion chamber 10 and an expansion part 12.
- the compressor part 8 and the relaxation part 12 are arranged on a common shaft 14, via which a generator for generating electricity, which is not shown here, is driven.
- preheated air 16 is compressed to the inlet pressure of the catalytic combustion chamber 10.
- a line system 4 is provided for the fuel gas 6, in the exemplary embodiment natural gas, with which a part of the fuel gas 6, here about 15% by volume, of a preforming stage 18 as a fuel gas part Stream 20 is supplied.
- the remaining fuel gas 6 is fed directly to the catalytic combustion chamber 10.
- the fuel gas partial flow 20 is first heated in the preforming stage 18 to approximately 100 ° C. by means of a heat exchanger 22.
- the heated fuel gas partial stream 20 then flows through honeycomb catalysts 24, which essentially consist of titanium dioxide and comprise a mixture of vanadium oxide, tungsten oxide, molybdenum oxide, platinum and rhodium. Due to the catalytic action of the honeycomb catalysts 24, most of the fuel gas partial stream 20 is preformed, i.e. The catalytically easily ignitable substances alcohol, aldehyde and hydrogen form from the natural gas 6.
- the fuel gas partial stream 20 preformed in this way is likewise fed to the catalytic combustion chamber 10.
- the fuel gas 6, the preformed fuel gas partial stream 20 and the preheated and compressed air 16 are mixed by means of a mixing element, e.g. a static mixer 26, mixed and then supplied to suitable catalysts, here honeycomb catalysts 28.
- the honeycomb catalysts 28 have a particularly strong oxidation effect for the catalytic combustion of fuel gas 6, fuel gas partial stream 20 and preheated, compressed air 16.
- they have titanium dioxide TiC> 2 as the base material and comprise platinum, rhodium, iridium as well as cerium oxide and chromium oxide as the catalytically active components.
- the aforementioned noble metals are each 1% by weight and the aforementioned metal oxides are each 3 % By weight is present in the honeycomb catalysts 28.
- other compositions of the catalytically active components are also possible.
- the gas mixture mixed by means of the static mixer 26 ignites at a temperature of approximately 250 ° C. and then burns completely in the honeycomb catalysts 28 the hot burner outlet 30 of the catalytic combustion chamber 10 entering the expansion section has a temperature of approximately 1100 ° C. and is expanded in the expansion section 12.
- a heat recovery steam generator which is not shown here. Due to the comparatively low catalytic ignition temperature of the gas mixture burned in the catalytic combustion chamber 10, the use of an auxiliary burner which generates a support or pilot flame can be dispensed with entirely. This auxiliary burner is therefore also eliminated as a nitrogen oxide source, so that the burner exhaust gas 30 has a comparatively low nitrogen oxide content when it emerges from the expansion part 12.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Catalysts (AREA)
Priority Applications (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP96915990A EP0832397B1 (de) | 1995-06-12 | 1996-06-11 | Katalytische gasturbinenbrenner |
| DE59604547T DE59604547D1 (de) | 1995-06-12 | 1996-06-11 | Katalytische gasturbinenbrenner |
| RU98100425A RU2142566C1 (ru) | 1995-06-12 | 1996-06-11 | Газовая турбина для сжигания горючего газа |
| JP9502489A JPH11507428A (ja) | 1995-06-12 | 1996-06-11 | 燃料ガスを燃焼するガスタービン |
| US08/990,033 US5904040A (en) | 1995-06-12 | 1997-12-12 | Gas turbine for the combustion of reformed fuel gas |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19521308A DE19521308A1 (de) | 1995-06-12 | 1995-06-12 | Gasturbine zur Verbrennung eines Brenngases |
| DE19521308.4 | 1995-06-12 |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US08/990,033 Continuation US5904040A (en) | 1995-06-12 | 1997-12-12 | Gas turbine for the combustion of reformed fuel gas |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO1996041990A1 true WO1996041990A1 (de) | 1996-12-27 |
Family
ID=7764160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/DE1996/001018 WO1996041990A1 (de) | 1995-06-12 | 1996-06-11 | Katalytische gasturbinenbrenner |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US5904040A (instruction) |
| EP (1) | EP0832397B1 (instruction) |
| JP (1) | JPH11507428A (instruction) |
| DE (2) | DE19521308A1 (instruction) |
| ES (1) | ES2143760T3 (instruction) |
| IN (1) | IN189223B (instruction) |
| RU (1) | RU2142566C1 (instruction) |
| WO (1) | WO1996041990A1 (instruction) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2791415A1 (fr) * | 1999-03-25 | 2000-09-29 | Sunkiss Aeronautique | Procede de combustion catalytique emettant un rayonnement infrarouge, avec controle de la puissance de ce dernier |
Families Citing this family (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5740667A (en) * | 1994-12-15 | 1998-04-21 | Amoco Corporation | Process for abatement of nitrogen oxides in exhaust from gas turbine power generation |
| DE10164097A1 (de) * | 2001-12-24 | 2003-07-03 | Alstom Switzerland Ltd | Vormischbrenner mit hoher Flammenstabilität |
| DE50212753D1 (de) | 2001-07-26 | 2008-10-23 | Alstom Technology Ltd | Vormischbrenner mit hoher Flammenstabilität |
| DE10160837B4 (de) * | 2001-12-12 | 2006-03-02 | Daimlerchrysler Ag | Verfahren der Mischung von heißen Brennergasen mit Sekundärluft zur Temperaturbegrenzung |
| JP4167039B2 (ja) * | 2002-04-10 | 2008-10-15 | 三菱重工業株式会社 | ガスタービン単独プラントの改造方法、触媒の再利用方法 |
| US7007487B2 (en) * | 2003-07-31 | 2006-03-07 | Mes International, Inc. | Recuperated gas turbine engine system and method employing catalytic combustion |
| EP1510761A1 (de) | 2003-08-13 | 2005-03-02 | Siemens Aktiengesellschaft | Verfahren zur Verbrennung eines fluidischen Brennstoffs sowie Brenner, insbesondere für eine Gasturbine, zur Durchführung des Verfahrens |
| US20050144961A1 (en) * | 2003-12-24 | 2005-07-07 | General Electric Company | System and method for cogeneration of hydrogen and electricity |
| US7444820B2 (en) * | 2004-10-20 | 2008-11-04 | United Technologies Corporation | Method and system for rich-lean catalytic combustion |
| RU2342601C1 (ru) * | 2007-06-14 | 2008-12-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Газотурбинная установка регенеративного цикла с каталитической камерой сгорания |
| CN101307915B (zh) * | 2008-06-24 | 2010-06-02 | 北京航空航天大学 | 一种燃用乙醇燃料的燃气轮机预蒸发燃烧室 |
| US8381531B2 (en) | 2008-11-07 | 2013-02-26 | Solar Turbines Inc. | Gas turbine fuel injector with a rich catalyst |
| US20120055168A1 (en) | 2010-09-08 | 2012-03-08 | General Electric Company | System and method for producing hydrogen rich fuel |
| PL2630342T3 (pl) * | 2010-10-19 | 2015-03-31 | General Electric Technology Gmbh | Sposób działania pracującego w cyklu połączonym zakładu energetycznego z produkcją skojarzoną, oraz pracujący w cyklu połączonym zakład energetyczny do wykonywania tego sposobu |
| US8869502B2 (en) | 2011-01-13 | 2014-10-28 | General Electric Company | Fuel reformer system for a turbomachine system |
| US20130305738A1 (en) * | 2012-05-17 | 2013-11-21 | General Electric Company | System and method for producing hydrogen rich fuel |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB209128A (en) * | 1922-08-01 | 1924-01-01 | Clarence Parshall Byrnes | Improved manufacture of liquid fuel |
| FR2209892A1 (instruction) * | 1972-12-11 | 1974-07-05 | Siemens Ag | |
| FR2228535A1 (en) * | 1973-05-08 | 1974-12-06 | Engelhard Min & Chem | Adiabatic combustion of carbonaceous fuels - e.g. used I.C. engine and gas turbines |
| US4202169A (en) * | 1977-04-28 | 1980-05-13 | Gulf Research & Development Company | System for combustion of gases of low heating value |
| US4519992A (en) * | 1983-05-26 | 1985-05-28 | Alkhazov Tofik G O | Process for purifying gases from hydrogen sulphide |
| JPS6153425A (ja) * | 1984-08-24 | 1986-03-17 | Hitachi Ltd | ガスタ−ビン用の燃焼器並びにその燃焼方法 |
| US5048284A (en) * | 1986-05-27 | 1991-09-17 | Imperial Chemical Industries Plc | Method of operating gas turbines with reformed fuel |
| GB2268694A (en) * | 1992-07-14 | 1994-01-19 | Rolls Royce Plc | A catalytic combustion chamber |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2839892A (en) * | 1947-10-04 | 1958-06-24 | Rosenthal Henry | Gas turbine cycle employing secondary fuel as a coolant, and utilizing the turbine exhaust gases in chemical reactions |
| US4185456A (en) * | 1976-07-02 | 1980-01-29 | Cummings Donald Ray | Providing energy from the combustion of methanol |
| US4811556A (en) * | 1986-10-14 | 1989-03-14 | General Electric Company | Multiple-propellant air vehicle and propulsion system |
| DE3741887A1 (de) * | 1987-12-10 | 1989-06-22 | Asea Brown Boveri | Katalysator und verfahren zu seiner herstellung |
| RU2015380C1 (ru) * | 1990-01-17 | 1994-06-30 | Вилен Вагаршевич Азатян | Способ работы газотурбинной установки |
| DE4133337A1 (de) * | 1990-10-08 | 1992-04-09 | Riken Kk | Abgasreiniger und verfahren zum reinigen von abgasen |
| DE19536836C2 (de) * | 1995-10-02 | 2003-11-13 | Alstom | Verfahren zum Betrieb einer Kraftwerksanlage |
-
1995
- 1995-06-12 DE DE19521308A patent/DE19521308A1/de not_active Withdrawn
-
1996
- 1996-06-11 WO PCT/DE1996/001018 patent/WO1996041990A1/de active IP Right Grant
- 1996-06-11 EP EP96915990A patent/EP0832397B1/de not_active Expired - Lifetime
- 1996-06-11 RU RU98100425A patent/RU2142566C1/ru not_active IP Right Cessation
- 1996-06-11 DE DE59604547T patent/DE59604547D1/de not_active Expired - Fee Related
- 1996-06-11 ES ES96915990T patent/ES2143760T3/es not_active Expired - Lifetime
- 1996-06-11 JP JP9502489A patent/JPH11507428A/ja not_active Ceased
- 1996-06-12 IN IN1092CA1996 patent/IN189223B/en unknown
-
1997
- 1997-12-12 US US08/990,033 patent/US5904040A/en not_active Expired - Lifetime
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB209128A (en) * | 1922-08-01 | 1924-01-01 | Clarence Parshall Byrnes | Improved manufacture of liquid fuel |
| FR2209892A1 (instruction) * | 1972-12-11 | 1974-07-05 | Siemens Ag | |
| FR2228535A1 (en) * | 1973-05-08 | 1974-12-06 | Engelhard Min & Chem | Adiabatic combustion of carbonaceous fuels - e.g. used I.C. engine and gas turbines |
| US4202169A (en) * | 1977-04-28 | 1980-05-13 | Gulf Research & Development Company | System for combustion of gases of low heating value |
| US4519992A (en) * | 1983-05-26 | 1985-05-28 | Alkhazov Tofik G O | Process for purifying gases from hydrogen sulphide |
| JPS6153425A (ja) * | 1984-08-24 | 1986-03-17 | Hitachi Ltd | ガスタ−ビン用の燃焼器並びにその燃焼方法 |
| US5048284A (en) * | 1986-05-27 | 1991-09-17 | Imperial Chemical Industries Plc | Method of operating gas turbines with reformed fuel |
| GB2268694A (en) * | 1992-07-14 | 1994-01-19 | Rolls Royce Plc | A catalytic combustion chamber |
Non-Patent Citations (1)
| Title |
|---|
| PATENT ABSTRACTS OF JAPAN vol. 010, no. 216 (M - 502) 29 July 1986 (1986-07-29) * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2791415A1 (fr) * | 1999-03-25 | 2000-09-29 | Sunkiss Aeronautique | Procede de combustion catalytique emettant un rayonnement infrarouge, avec controle de la puissance de ce dernier |
Also Published As
| Publication number | Publication date |
|---|---|
| DE19521308A1 (de) | 1996-12-19 |
| EP0832397A1 (de) | 1998-04-01 |
| IN189223B (instruction) | 2003-02-01 |
| RU2142566C1 (ru) | 1999-12-10 |
| US5904040A (en) | 1999-05-18 |
| ES2143760T3 (es) | 2000-05-16 |
| EP0832397B1 (de) | 2000-03-01 |
| DE59604547D1 (de) | 2000-04-06 |
| JPH11507428A (ja) | 1999-06-29 |
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