GB2116308A - Improved Low-NOx, rich-lean combustor - Google Patents
Improved Low-NOx, rich-lean combustor Download PDFInfo
- Publication number
- GB2116308A GB2116308A GB08305112A GB8305112A GB2116308A GB 2116308 A GB2116308 A GB 2116308A GB 08305112 A GB08305112 A GB 08305112A GB 8305112 A GB8305112 A GB 8305112A GB 2116308 A GB2116308 A GB 2116308A
- Authority
- GB
- United Kingdom
- Prior art keywords
- combustion
- fuel
- zone
- rich
- ceramic
- 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.)
- Granted
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 78
- 239000000446 fuel Substances 0.000 claims abstract description 75
- 239000002184 metal Substances 0.000 claims description 33
- 239000000919 ceramic Substances 0.000 claims description 31
- 238000001816 cooling Methods 0.000 claims description 18
- 238000010791 quenching Methods 0.000 claims description 17
- 238000011144 upstream manufacturing Methods 0.000 claims description 13
- 230000003197 catalytic effect Effects 0.000 claims description 7
- 238000009792 diffusion process Methods 0.000 claims description 6
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 230000004888 barrier function Effects 0.000 claims description 2
- 238000010276 construction Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 claims 2
- 238000007084 catalytic combustion reaction Methods 0.000 claims 1
- 230000003247 decreasing effect Effects 0.000 claims 1
- 230000001105 regulatory effect Effects 0.000 claims 1
- 230000015572 biosynthetic process Effects 0.000 abstract description 11
- 239000000203 mixture Substances 0.000 abstract 2
- 206010021143 Hypoxia Diseases 0.000 abstract 1
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 29
- 229910052757 nitrogen Inorganic materials 0.000 description 14
- 238000006243 chemical reaction Methods 0.000 description 8
- 239000003208 petroleum Substances 0.000 description 8
- 239000007789 gas Substances 0.000 description 7
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 6
- 239000001301 oxygen Substances 0.000 description 6
- 229910052760 oxygen Inorganic materials 0.000 description 6
- 238000002156 mixing Methods 0.000 description 4
- 238000002360 preparation method Methods 0.000 description 4
- 230000002950 deficient Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008016 vaporization Effects 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 239000003245 coal Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 229910017464 nitrogen compound Inorganic materials 0.000 description 1
- 150000002830 nitrogen compounds Chemical class 0.000 description 1
- 239000004058 oil shale Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C13/00—Apparatus in which combustion takes place in the presence of catalytic material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
- F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
- F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
Abstract
A low-NOx combustor 12 is provided with a rich, primary burn zone 42 for burning a rich fuel mixture and a subsequent, secondary burn zone 62 for burning a relatively lean fuel mixture. NOx formation is inhibited in the rich burn zone by oxygen deficiency, and inhibited in the lean burn zone by a low temperature of combustion reaction. <IMAGE>
Description
SPECIFICATION
Improved low-NOx, rich-lean combustor
The present invention relates to combustion turbines as may be employed in a variety of uses, such as industrial processes, electric power generation, or aircraft engines. More particularly, the present invention is directed to combustors employed in combustion turbines for heating
motive gases which drive the turbine.
In general terms, a typical prior art combustion turbine comprises three sections: a compressor section, a combustor section, and a turbine section. Air drawn into the compressor section is compressed, increasing its temperature and density. The compressed air from the compressor section flows through the combustor section where the temperature of the air mass is further increased. From the combustor section the hot pressurized gases flow into the turbine section where the energy of the expanding gases is transformed into rotational motion of a turbine rotor.
A typical combustor section comprises a plurality of combustors arranged in an annular array about the circumference of the combustion turbine. In conventional combustor technology, pressurized gases flowing from the compressor section are heated by a diffusion flame in the combustor before passing to the turbine section.
In the diffusion flame technique, fuel is sprayed into the upstream end of a combustor by means of a nozzle. The flame is maintained immediately downstream of the nozzle by strong aerodynamic recirculation. The lack of thorough mixing of the fuel results in pockets of high fuel concentration and correspondingly high combustion reaction temperatures. Because the reaction temperature is high, hot gases flowing from the combustion reaction must be diluted downstream by cool air so as to prevent damage to turbine components positioned downstream. In addition, the flame diffusion technique commonly used produces emissions with significant levels of undesirable chemical compounds, including NOx.
NOx results from two basic reactions. Thermal NOx is produced from the combination of nitrogen and oxygen in the fuel oxidizer (air) during and.
after the combustion process when the temperature level is sufficiently high to permit the overall reaction which can be represented by N2+02o2NO to occur at a measurable rate. The thermal NO reaction occurs for all combustion processes using air and is essentially independent of the fuel.
NOx is also formed from fuel-bound nitrogen, which forms NO-type compounds in the combustion process in a manner somewhat analogous to the formation of CO and CO2 from fuel carbon and H20 from fuel hydrogen. The differences between the two mechanisms for forming NOx lie in the time and temperature of the combustion process. Fuel-bound nitrogen compounds appear virtually simultaneously with the CO, CO2, and H20, while the formation of NOx from the oxidizer appears later and is governed by a kinetic rate mechanism.
Increased environmental awareness has resulted in more stringent emission standards for
NOx. The more stringent standards are leading to development of improved combustor technologies. One such improvement is a premixing, pre-vaporizing combustor. In this type of combustor, fuel is sprayed into a fuel preparation zone where it is thoroughly mixed to achieve a homogeneous concentration which pervades within definite limits of the mean concentration.
Additionally, a certain amount of fuel is vaporized in the fuel preparation zone. Fuel combustion occurs at a point downstream from the fuel preparation zone. The substantially uniform fuel concentration achieved in the fuel preparation zone results in a uniform reaction temperature which may be limited to approximately 2000 to 30000 F. Due to the uniformity of the combustion, the pre-mixing, pre-vaporizing combustor produces lower levels of thermal NOx than does a conventional combustor using the same amount of fuel. NOx formed from fuel-bound nitrogen is tolerable because of the comparatively low nitrogen content of the typical petroleum fuel utilized.
The increased environmental awareness of recent years regarding emission-standards has been accompanied by a recognition of the limited availability of petroleum fuels. Consequently, a trend has developed focusing on the use of nonpetroleum fuels for combustion turbines. Nonpetroleum fucls typically have a higher nitrogen content than do petroleum fuels. For example, a typical petroleum fuel might have a nitrogen content of 0.1% by weight, while coal-derived liquids contain fuel-bound nitrogen up to 1% by weight, and, oil shale-derived liquid fuels contain fuel-bound nitrogen up to 2% by weight. Because they do not inhibit NOx formed from fuel-bound nitrogen, pre-mixing, pre-vaporizing combustors would likely fail the stringent NOx standards when operated with nonpetroleum fuels.
Hence, it appears that known prior art combustors do not adequately provide for low NOx emissions when operated with nonpetroleum fuels.
The present invention provides a combustor which can efficiently handle nonpetroleum fuels at the same time producing low NOx emissions.
The present invention in its broad form comprises a combustion turbine, a combustor with an improved construction which will inhibit production of excess NOx the combustor comprising: a basket, having an upstream end and a downstream end, and having walls for containing a combustion reaction therein, said upstream end containing a fuel rich combustion zone, said downstream end containing a fuel-lean combustion zone; means at the upstream end of said basket for injection fuel into said basket; means in the upstream end of said basket for providing fuel-rich combustion of the injected fuel and heat barrier means associated with said wall of the fuel rich combustion zone to support combustion in said fuel-rich combustion zone; means in the downstream end of said basket for providing fuel-lean combustion of gaseous products which exit from said fuel-rich combustion means.
A combustion turbine combustor arranged to achieve low-NOx emissions comprises a basket, means for injecting fuel into the basket, means for providing fuel-rich combustion in a primary combustion zone, and means for providing fuellean combustion in a secondary combustion zone.
The fuel-rich combustion disassociates fuelbound nitrogen and inhibits the formation of NOx due to the oxygen-deficient atmosphere. The fuellean combustion, while completing the combustion process, is carried out at temperatures too low to enable the formation of thermal NOx Hence, stringent NOx emission standards may be adhered to when nonpetroleum as well as petroleum fuels are used to fuel the present combustor.
A more detailed understanding of the invention may be had from the following description of a preferred embodiment, given by way of example and to be studied in conjunction with the accompanying drawing wherein:
Figure 1 shows a longitudinal section of a landbased combustion turbine arranged for the production of electric power; in particular, a combustor is depicted within the combustion turbine;
Figure 2 shows a sectional view of the combustor shown in Figure 1;
Figure 3 shows an alternative embodiment of the wall of the combustor shown in Figure 2;
Figure 4 shows a third embodiment of the wall of the combustor shown in Figure 2; and
Figure 5 shows an alternative embodiment of the downstream portion of the combustor shown in Figure 2.
As illustrated, Figure 1 shows a combustion turbine 10 having a plurality of generally cylindrical combustors 12. Fuel is supplied to the combustors 12 through a nozzle structure 14 and air is supplied to the combustors 12 by a compressor 1 6 through air flow space 1 8 within a combustion casing 20.
Hot gaseous products of combustion are directed from each combustor 1 2 through a transition duct 22 where they are discharged into the annular space through which turbine blades 24, 26 rotate under the driving force of the expanding gases.
In accordance with the principles of the invention, combustor 1 2 is structured to provide improved, low-NOx combustion emissions when operated with non-petroleum fuels as well as with petroleum fuels. The combustor 12, shown in greater detail in Figure 2, comprises a generally cylindrical outer metal jacket 30 having conicalshaped upstream end 32 and being openended at the downstream end 34. The conical end 32 of the metal jacket defines a centrally positioned opening 36 having a pressure atomizing fuel injector 38, of a type well known in the art, protruding therethrough.
A ceramic cylinder 40, within the metal jacket 30, surrounds a rich burn zone 42 within the combustor 12. The ceramic cylinder 40 may comprise a monolithic cylinder or a cylinder formed from a plurality of sections. An expansion layer 44, comprising, for example, a network of wire mesh, separates the ceramic cylinder 40 from the metal jacket 30. The expansion layer 44 compensates for the different rates of r thermal expansion of the ceramic cylinder 40 and the metal jacket 30. A plurality of bleed ports 45 in the metal jacket 30 provide a source of cooling air to the expansion layer 44. An insulating layer 46, comprised of suitable insulating material, separates the ceramic cylinder 40 from the expansion layer 44.
A flame tube 48 protrudes through the combustor wall (comprising at this point metal jacket 30, the expansion layer 44, the insulating layer 46, and the ceramic cylinder 40) at a point immediately downstream of the fuel injector 38.
The flame tube 48 connects a torch igniter 50 to the rich burn zone 42, providing a hot flame jet for positive ignition of the combustor. Downstream of the flame tube 48, the combustor wall defines an annular ring of radially extending primary air ports 52 for delivery of an air supply for combustion in the rich burn' zone 42.
A quench zone 54, downstream of the rich burn zone 42, comprises a Venturi-shaped section of the interior combustor wall. The combustor wall surrounding the quench zone 54 comprises the metal jacket 30 encasing cast ceramic 56.
The cast ceramic, which is shaped to achieve the
Venturi effect, is affixed to the metal jacket 30 by metal retainers 58 which are attached, such as by welding, to the metal jacket 30 and cast within the ceramic 56. The metal retainers 58 may be arranged in any fashion, such as in a helical arrangement depicted in Figure 2, which ensures the rigid attachment of the cast ceramic to the metal jacket 30.
The throat of the Venturi-shaped combustor wall surrounding the quench zone 54 defines a plurality of annularly disposed cooling air ports 60 extending radially through the combustor wall (comprising at this point the metal jacket 30 and the cast ceramic 56) for the delivery of cooling air to hot gaseous products produced in the primary burn zone 42.
A lean burn zone 62, positioned downstream of the quench zone 54, comprises a catalytic section 64 for secondary combustion of the gaseous products from the rich burn zone 42. The catalytic section 64 is surrounded by an expansion layer 66 of the same structure as the expansion layer 44 surrounding the rich burn zone 42. The expansion layer 66 is surrounded and contained by the metal jacket 30.
In operation, the atomizing fuel injector 38 sustains a diffusion flame in the fuel-rich atmosphere of the rich burn zone 42. Utilization of a diffusion flame for combustion of nonpetroleum liquid fuels as heretofore not been acceptable (according to known prior art) due to the problems associated with this technique. The ceramic cylinder 40 encasing the rich burn zone 42 eliminates the necessity for film-cooling the interior wall of the combustor, obviating a feature typical of the prior art. The lack of film cooling within the rich burn zone enables the success of fuel-rich combustion and actually enhances the combustion process by maintaining the walls at an elevated temperature.
The fuel equivalence ratio of a combustion zone is defined as the ratio of the actual fuel-toair ratio to the stoichiometric fuel-to-air ratio. A lean combustion zone may have a fuel equivalence ratio as low as 0.4 while a rich combustion zone may operate at a value as high as 2.5. It is suggested that the rich burn zone of the present invention may operate favorably at a fuel equivalence ratio of 1.7.
Fuel-rich combustion provides an oxygen deficient atmosphere in which the relatively inactive fuel-bound nitrogen molecules, disassociated from the fuel by the combustion process, cannot compete with carbon and hydrogen for the limited oxygen molecules.
Consequently, most of the nitrogen leaving the rich burn zone 42 is in the form of free nitrogen (N2), rather than in the form of NOx The hot gaseous products leaving the rich burn zone 42 are quickly cooled to a lower temperature within the quench zone 54. The Venturi shape of the quench zone 54 promotes through and homogeneous mixing of the cooling air supplied to the ports 60 with the gaseous products from the rich burn zone.
The combustion process is completed in the lean burn zone 62, where the gaseous products from the rich burn zone 42, such as CO, smoke, and other unburned fuel components, are passed through the catalytic section 64. Combustion within the catalytic section 64 occurs at a temperature significantly reduced from the
reaction temperature in the rich burn zone.
The formation of thermal NOx is minimized bathe lower lean combustion reaction temperature, which in essence limits the reaction rate of the formation of NOx Hence, the combustor 12 produces low-NOx emissions by disassociating the fuel-bound nitrogen in a rich combustion reaction in the rich burn zone 42 and completing the combustion process at temperatures too low for the formation of thermal NOx. The formation of thermal NOx within the rich burn zone is inhibited by the deficiency of the oxygen molecules necessary for the reaction.
Figure 3 shows an alternative embodiment for the combustor wall surrounding the rich burn zone 42. This embodiment comprises a structure substantially similar to that of the combustor wall surrounding the quench zone 54. In the alternative embodiment, the rich burn zone is surrounded by a ceramic layer 70 cast to the metal jacket 30 and affixed to the metal jacket by metal retainers 72.
Figure 4 depicts an alternative embodiment for the wall of the combustor 12. This embodiment comprises the outer metal jacket 30 surrounding an inner metal jacket 74, the jackets 30, 74 extending from the dome 32 to the downstream end 34 of the combustor 12. Cooling air, depicted at 76, enters the space between the metal jackets 30, 74 at the upstream end of the rich burn zone 42. The cooling air circulates around the primary air supply ports 52 to reach the cooling air ports 60. In this embodiment, the cooling air which entered at 76 cools the inner metal jacket 74 along the rich burn zone and provides the sole source of cooling air used within the quench zone to dilute the temperature of the hot gaseous products leaving the rich burn zone. Some of the cooling air which entered at 76 is diverted to cool the inner metal jacket downstream of the cooling air ports 60.
Figure 5 depicts an alternative embodiment for the lean burn zone 62. In this embodiment, the lean burn zone comprises a straight cylindrical section, structured substantially similar to the rich burn zone 42 of Figure 2, or the rich burn zone of
Figure 3. In this embodiment, lean combustion is accomplished at the lower temperatures of the gases within the lean burn zone, which temperatures are still high enough to ensure combustion. Further, the ceramic wall 80 surrounding the lean burn zone 62 enhances the secondary combustion process.
Hence, the present invention provides an efficient combustor for achieving low-NOx emissions from the combustion of nonpetroleum as well as petroleum fuels. Combustion in a fuelrich burn zone disassociates fuel-bound nitrogen in an oxygen-deficient atmosphere which inhibits the formation of thermal NOx and combustion is completed in a fuel-lean combustion zone at temperatures too low to allow the formation of thermal NOx.
Claims (14)
1. In a combustion turbine, a combustor with an improved construction which will inhibit production of excess NOx, the combustor comprising:
a basket, having an upstream end and a downstream end, and having walls for containing a combustion reaction therein, said upstream end containing a fuel rich combustion zone, said downstream end containing a fuel-lean combustion zone;
means at the upstream end of said basket for injecting fuel into said basket;
means in the upstream end of said basket for providing fuel-rich combustion of the injected fuel and heat barrier means associated with said wall of the fuel rich combustion zone to support combustion in said fuel-rich combustion zone;
means in the downstream end of said basket for providing fuel-lean combustion of gaseous products which exit from said fuel-rich combustion means.
2. A combustor according to claim 1 wherein said fuel-rich combustion means comprises a rich burn zone arranged to support combustion by a diffusion flame, said rich burn zone comprising at least a first enclosure with a ceramic lining;
said combustor further including means for ensuring that the fuel equivalence ratio within said zone is greater than 1.0; and means for igniting the injected fuel.
3. A combustor according to claim 2 wherein said fuel-lean combustion means comprises:
a quench zone, having an upstream end and a downstream end, positioned immediately downstream of said rich burn zone for cooling gaseous products generated therein; and
a lean combustion zone immediately downstream of said quench zone for supporting combustion of gaseous products leaving said quench zone.
4. A combustor according to claim 3 wherein said quench zone comprises:
a first section at the upstream end of said quench zone gradually decreasing in diameter in the downstream direction;
a second section at the downstream end of said quench zone gradually increasing in diameter in the downstream direction; and
a third section between said first and second sections having a constant inner diameter and a plurality of annularly disposed cooling ports extending radially therethrough for communicating a supply of cooling air to said quench zone.
5. A combustor according to claim 4 wherein said first, second, and third sections of said quench zone are constituted by a second ceramic enclosure.
6. A combustor according to claim 4 wherein said lean burn zone comprises a catalytic element for supporting catalytic combustion.
7. A combustor according to claim 4 wherein said lean burn zone comprises a third ceramic enclosure for supporting,fuel-lean combustion by perpetuating the combustion reaction of the gaseous products leaving the quench zone.
8. A combustor according to claim 2 wherein said means for ensuring the air equivalence ratio comprises:
a plurality of annularly disposed air supply ports extending radially through said first ceramic enclosure for communicating a predetermined flow of primary combustion air to said rich burn zone; and
means for regulating the flow of fuel injected by said injecting means to a predetermined level.
9. A combustor according to claim 2 wherein said first ceramic enclosure comprises a monolithic ceramic cylinder and said rich burn zone further comprises:
a metal jacket surrounding and enclosing said first ceramic enclosure; and
an expansion layer between said metal jacket and said first ceramic enclosure, said expansion layer comprising a wire mesh material.
10. A combustor according to claim 9 wherein said first ceramic enclosure comprises a cast ceramic member affixed to a metal jacket which surrounds said first ceramic enclosure.
1 A combustor according to claim 5 wherein said second ceramic enclosure comprises ceramic cast and affixed to a metal jacket surrounding said ceramic enclosure.
12. A combustor according to claim 6 wherein said lean burn zone further comprises:
a metal jacket surrounding and enclosing said catalytic element; and
an expansion layer between said metal jacket and said catalytic element, comprising a wire mesh material.
13. A combustor according to claim 7 wherein said third ceramic enclosure comprises a cast ceramic element affixed to a metal jacket surrounding said third ceramic enclosure.
14. A combustor according to claim 1 wherein said basket comprises a first metal enclosure encircled by a second substantially coaxial metal enclosure, defining therebetween an annular space supporting the flow of cooling air for cooling said first metal enclosure.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US35606882A | 1982-03-08 | 1982-03-08 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB8305112D0 GB8305112D0 (en) | 1983-03-30 |
| GB2116308A true GB2116308A (en) | 1983-09-21 |
| GB2116308B GB2116308B (en) | 1985-11-13 |
Family
ID=23399972
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08305112A Expired GB2116308B (en) | 1982-03-08 | 1983-02-24 | Improved low-nox, rich-lean combustor |
Country Status (7)
| Country | Link |
|---|---|
| JP (1) | JPS58164929A (en) |
| BE (1) | BE896105A (en) |
| BR (1) | BR8301099A (en) |
| CA (1) | CA1206764A (en) |
| GB (1) | GB2116308B (en) |
| IT (1) | IT1170117B (en) |
| MX (1) | MX158476A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3545524A1 (en) * | 1985-12-20 | 1987-07-02 | Kraftwerk Union Ag | Multi-stage combustion chamber for the combustion of nitrogen-containing gas with reduced NOx emission and process for the operation thereof |
| US4850195A (en) * | 1985-09-30 | 1989-07-25 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Fuel spray combustion device |
| DE3903687A1 (en) * | 1988-02-08 | 1989-08-17 | Vaillant Joh Gmbh & Co | Device for the combustion in stages of a fuel/air mixture |
| US5117636A (en) * | 1990-02-05 | 1992-06-02 | General Electric Company | Low nox emission in gas turbine system |
| DE4422535A1 (en) * | 1994-06-28 | 1996-01-04 | Abb Research Ltd | Process for operating a furnace |
| DE19612507A1 (en) * | 1996-03-29 | 1997-10-02 | Kunkel Klaus | Method for driving a shaft and drive therefor |
| US5996351A (en) * | 1997-07-07 | 1999-12-07 | General Electric Company | Rapid-quench axially staged combustor |
| EP1241334A1 (en) * | 2001-03-16 | 2002-09-18 | ALSTOM (Switzerland) Ltd | Ignition method for a turbomachine |
| EP1522792A1 (en) * | 2003-10-09 | 2005-04-13 | United Technologies Corporation | Combustor |
| GB2457564A (en) * | 2008-02-25 | 2009-08-26 | Gen Electric | Combustion system with reduced nitrogen oxide emissions |
-
1983
- 1983-02-24 GB GB08305112A patent/GB2116308B/en not_active Expired
- 1983-02-28 CA CA000422504A patent/CA1206764A/en not_active Expired
- 1983-03-01 MX MX196427A patent/MX158476A/en unknown
- 1983-03-04 IT IT19895/83A patent/IT1170117B/en active
- 1983-03-07 BR BR8301099A patent/BR8301099A/en not_active IP Right Cessation
- 1983-03-08 BE BE0/210276A patent/BE896105A/en not_active IP Right Cessation
- 1983-03-08 JP JP58036795A patent/JPS58164929A/en active Granted
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4850195A (en) * | 1985-09-30 | 1989-07-25 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Fuel spray combustion device |
| DE3545524A1 (en) * | 1985-12-20 | 1987-07-02 | Kraftwerk Union Ag | Multi-stage combustion chamber for the combustion of nitrogen-containing gas with reduced NOx emission and process for the operation thereof |
| US5002483A (en) * | 1985-12-20 | 1991-03-26 | Bernard Becker | Multi-stage combustion chamber for combustion of nitrogen-containing gas with reduced NOx emissions, and method for its operation |
| DE3903687A1 (en) * | 1988-02-08 | 1989-08-17 | Vaillant Joh Gmbh & Co | Device for the combustion in stages of a fuel/air mixture |
| US5117636A (en) * | 1990-02-05 | 1992-06-02 | General Electric Company | Low nox emission in gas turbine system |
| DE4422535A1 (en) * | 1994-06-28 | 1996-01-04 | Abb Research Ltd | Process for operating a furnace |
| DE19612507A1 (en) * | 1996-03-29 | 1997-10-02 | Kunkel Klaus | Method for driving a shaft and drive therefor |
| DE19612507C2 (en) * | 1996-03-29 | 2002-06-27 | Kunkel Klaus | Method for driving a shaft and drive therefor |
| EP0890795A3 (en) * | 1997-07-07 | 2000-03-22 | General Electric Company | Rapid-quench axially staged combustor |
| US5996351A (en) * | 1997-07-07 | 1999-12-07 | General Electric Company | Rapid-quench axially staged combustor |
| EP1241334A1 (en) * | 2001-03-16 | 2002-09-18 | ALSTOM (Switzerland) Ltd | Ignition method for a turbomachine |
| US6718773B2 (en) | 2001-03-16 | 2004-04-13 | Alstom Technology Ltd | Method for igniting a thermal turbomachine |
| EP1522792A1 (en) * | 2003-10-09 | 2005-04-13 | United Technologies Corporation | Combustor |
| GB2457564A (en) * | 2008-02-25 | 2009-08-26 | Gen Electric | Combustion system with reduced nitrogen oxide emissions |
| GB2457564B (en) * | 2008-02-25 | 2013-01-30 | Gen Electric | Combustion systems and processes for burning fossil fuel with reduced nitrogen oxide emissions |
| US8430665B2 (en) | 2008-02-25 | 2013-04-30 | General Electric Company | Combustion systems and processes for burning fossil fuel with reduced nitrogen oxide emissions |
Also Published As
| Publication number | Publication date |
|---|---|
| MX158476A (en) | 1989-02-03 |
| GB8305112D0 (en) | 1983-03-30 |
| JPS58164929A (en) | 1983-09-29 |
| BR8301099A (en) | 1983-11-22 |
| JPH0210348B2 (en) | 1990-03-07 |
| CA1206764A (en) | 1986-07-02 |
| IT8319895A0 (en) | 1983-03-04 |
| GB2116308B (en) | 1985-11-13 |
| BE896105A (en) | 1983-09-08 |
| IT1170117B (en) | 1987-06-03 |
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| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 19950224 |