CA1209813A - Turbine combustor having more uniform mixing of fuel and air for improved downstream combustion - Google Patents
Turbine combustor having more uniform mixing of fuel and air for improved downstream combustionInfo
- Publication number
- CA1209813A CA1209813A CA000434626A CA434626A CA1209813A CA 1209813 A CA1209813 A CA 1209813A CA 000434626 A CA000434626 A CA 000434626A CA 434626 A CA434626 A CA 434626A CA 1209813 A CA1209813 A CA 1209813A
- Authority
- CA
- Canada
- Prior art keywords
- fuel
- air
- combustor
- sidewall
- mixing
- 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.)
- Expired
Links
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
- F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
-
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- 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
- F23R3/346—Feeding into different combustion zones for staged combustion
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
- Combustion Of Fluid Fuel (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE
A combustor for a land based turbine comprising a generally tubular sidewall having a downstream mixing zone where a mixture of fuel and air is developed for downstream combustion, said sidewall further having an upstream primary zone into which air is admitted through sidewall openings to develop an axial airflow for mixing with downstream injection fuel, means for spraying fuel in small rapidly evaporable droplets generally radially inwardly through said sidewall at a location between said primary zone and said mixing zone for mixing with the primary air flow, a catalyst is coupled to the combustor sidewall at the outlet of said mixing zone, a plurality of circumferentially disposed air scoops located in upstream proximity to said fuel spraying means and angled down-stream to produce said booster air streams.
A combustor for a land based turbine comprising a generally tubular sidewall having a downstream mixing zone where a mixture of fuel and air is developed for downstream combustion, said sidewall further having an upstream primary zone into which air is admitted through sidewall openings to develop an axial airflow for mixing with downstream injection fuel, means for spraying fuel in small rapidly evaporable droplets generally radially inwardly through said sidewall at a location between said primary zone and said mixing zone for mixing with the primary air flow, a catalyst is coupled to the combustor sidewall at the outlet of said mixing zone, a plurality of circumferentially disposed air scoops located in upstream proximity to said fuel spraying means and angled down-stream to produce said booster air streams.
Description
~2~ 3 1 50,364 TURBINE COMBUSTOR ~LAVING MORE UNIFORM
MIXING OF FUEL AND AIR FOR IMPROVED
DOWNSTREAM COMBUSTION
CROSS REFERENCE TO RELATED APPLICATIONS
None BACKGROUND OF THE INVENTION
The present invention relates to combustors employed in land based combustion turbines and more par-ticularly to combustors in which substantially uniform m;x;ng of ~uel and air across the combustor mix;ng zone is needed prior to entry of the mix into the combustion zone, i.e. the catalyst in catalytic combustors.
Prem;~;ng of fuel and air in premix combustors is needed to provide long combustion life, high combustor efficiency and low emissions through proper combustor operating temperatures and chemistry. Catalytic combus-tors provide a prospective commercial al~ernative for low pollutant, and especially low NOx, combustion turblne operation for electric power plants and other land based applications, and proper catalytic combustion especially requires substantial uniformity in the prem;~;ng of fuel and air within the combustor m;x;ng zone.
With the operating compressor discharge pressure in most engine designs, some preheating of fuel/air mixture is needed for proper catalytic combustion. Thus, a catalytic combustor may be provided with a generally tubwlar envelope having a primary combustion ~one followed in sequence first by a s~condary fuel injection and m;x;ng zone and
MIXING OF FUEL AND AIR FOR IMPROVED
DOWNSTREAM COMBUSTION
CROSS REFERENCE TO RELATED APPLICATIONS
None BACKGROUND OF THE INVENTION
The present invention relates to combustors employed in land based combustion turbines and more par-ticularly to combustors in which substantially uniform m;x;ng of ~uel and air across the combustor mix;ng zone is needed prior to entry of the mix into the combustion zone, i.e. the catalyst in catalytic combustors.
Prem;~;ng of fuel and air in premix combustors is needed to provide long combustion life, high combustor efficiency and low emissions through proper combustor operating temperatures and chemistry. Catalytic combus-tors provide a prospective commercial al~ernative for low pollutant, and especially low NOx, combustion turblne operation for electric power plants and other land based applications, and proper catalytic combustion especially requires substantial uniformity in the prem;~;ng of fuel and air within the combustor m;x;ng zone.
With the operating compressor discharge pressure in most engine designs, some preheating of fuel/air mixture is needed for proper catalytic combustion. Thus, a catalytic combustor may be provided with a generally tubwlar envelope having a primary combustion ~one followed in sequence first by a s~condary fuel injection and m;x;ng zone and
2 50,364 finally by a catalyst. The primary combustion æone oper-ates for example during startup when operating tempera-tures do not adequately support catal~tic combustion.
During the catalytic combustion phase of operation, secon-dary fuel is injected into the mixing zone where it mixeswith air for delivery to the flow channels through the catalyst.
Typically, the secondary fuel injectors are disposed circumferentially about the mixing zone and they may inject fuel radially inwardly at a right or other angle into the combustor mixing zone. Further, the fuel must be essentially completely vapori~ed before entering the catalyst which requires that the fuel nozzle produce very small droplets which can evaporate rapidly. Small droplets can be obtained by using a very high fuel nozzle pressure drop (pressure atomization~, by using a small amount of high energ~ atomizing air (air assist), or by using a relatively large amount of low energy atomizing air (air blast). In all cases, the momentum of the resul-ting fuel spray is quite high. In fact the momentum ofthe fuel spray with respect to the momentum of the cross flowing air inside the combustor is high enough that the uel tends to penetrate to the center (axis) o the com-bustor. This action produces a fuel rich core, i.e. the fuel/air ratio profile has a sin~le center peak shape across a reference diameter of a cross section of the combustor mixing zone.
The fuel/air ratio is highest at the axis in the fuel injection plane or region, and it decreases in the radial outward direction. As the mix flows downstream through the mixing zone, additional mixing action causes the uel/air ratio profile to flatten somewhat. In gen-eral, however, the scope of fuel penetration in the injec-tion region has resulted in too much axial fuel concentra~
tion to permit available downstream mixing to produce a substantially uniform fuel/air ratio distribution at the catalyst entry plane.
8~3
During the catalytic combustion phase of operation, secon-dary fuel is injected into the mixing zone where it mixeswith air for delivery to the flow channels through the catalyst.
Typically, the secondary fuel injectors are disposed circumferentially about the mixing zone and they may inject fuel radially inwardly at a right or other angle into the combustor mixing zone. Further, the fuel must be essentially completely vapori~ed before entering the catalyst which requires that the fuel nozzle produce very small droplets which can evaporate rapidly. Small droplets can be obtained by using a very high fuel nozzle pressure drop (pressure atomization~, by using a small amount of high energ~ atomizing air (air assist), or by using a relatively large amount of low energy atomizing air (air blast). In all cases, the momentum of the resul-ting fuel spray is quite high. In fact the momentum ofthe fuel spray with respect to the momentum of the cross flowing air inside the combustor is high enough that the uel tends to penetrate to the center (axis) o the com-bustor. This action produces a fuel rich core, i.e. the fuel/air ratio profile has a sin~le center peak shape across a reference diameter of a cross section of the combustor mixing zone.
The fuel/air ratio is highest at the axis in the fuel injection plane or region, and it decreases in the radial outward direction. As the mix flows downstream through the mixing zone, additional mixing action causes the uel/air ratio profile to flatten somewhat. In gen-eral, however, the scope of fuel penetration in the injec-tion region has resulted in too much axial fuel concentra~
tion to permit available downstream mixing to produce a substantially uniform fuel/air ratio distribution at the catalyst entry plane.
8~3
3 50,364 SUMMARY OF THE INVENTION
In accordance with the present invention, im-proved operation is obtained in combustors and especially catalytic combus-tors through structure which assists deflection of injected fuel in the axial direction to produce more uniform mixing of fuel and air in a mixing zone located immediately upstream from the zone ~here combustion occurs. Peferahly, the structure includes circumferentially distributed holes in the combustor wall upstream from the fuel injectors such that entering air streams are angled downstream. The entering air streams have high velocity due to the pressure drop across the combustor wall and accordingly greatly assist the internal gas flow in axially deflecting the injected fuel and producing a substantially uniform fuel/air ratio profile at the catalyst entry plane.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 shows an elevation view of a catalytic combustor having portions thereof cut away and being arranged in accordance with the principles of the inven-tion.
Figure 2 shows a schematic diagram of a cata-lytic combustor like that of Ei~ure 1 with operating features of the invention illustrated in greater detail.
Fi~ure 3 shows a diagram like that of Figure 2 but representing an alternative embodiment in which exter-nal air scoops are employed.
Figure 4 shows test results obtained with use of the present invention as compared to results obtained with a prior art reference.
Figure 5 shows a diagram of a prior art combus-tor configuration used in obtaining comparative test results.
DESCRIPTION OF THE PREFERRED EMBODIMENT
More particularly, a catalytic combustor 10 is shown in Figure 1 for a land based combustion turbine which is typically used in electric power and other indus-trial plants.
~2~ l3
In accordance with the present invention, im-proved operation is obtained in combustors and especially catalytic combus-tors through structure which assists deflection of injected fuel in the axial direction to produce more uniform mixing of fuel and air in a mixing zone located immediately upstream from the zone ~here combustion occurs. Peferahly, the structure includes circumferentially distributed holes in the combustor wall upstream from the fuel injectors such that entering air streams are angled downstream. The entering air streams have high velocity due to the pressure drop across the combustor wall and accordingly greatly assist the internal gas flow in axially deflecting the injected fuel and producing a substantially uniform fuel/air ratio profile at the catalyst entry plane.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 shows an elevation view of a catalytic combustor having portions thereof cut away and being arranged in accordance with the principles of the inven-tion.
Figure 2 shows a schematic diagram of a cata-lytic combustor like that of Ei~ure 1 with operating features of the invention illustrated in greater detail.
Fi~ure 3 shows a diagram like that of Figure 2 but representing an alternative embodiment in which exter-nal air scoops are employed.
Figure 4 shows test results obtained with use of the present invention as compared to results obtained with a prior art reference.
Figure 5 shows a diagram of a prior art combus-tor configuration used in obtaining comparative test results.
DESCRIPTION OF THE PREFERRED EMBODIMENT
More particularly, a catalytic combustor 10 is shown in Figure 1 for a land based combustion turbine which is typically used in electric power and other indus-trial plants.
~2~ l3
4 50,364 The combustor 10 includes a generally tubular sidewall 12 having successive circumferential row of holes 14, 16 for entry of air used in the combustion process. A-t a head end 18 of the combustor 10, a primary fuel nozzle 20 admits fuel for burning in a primary zone 22 to yenerate the energy needed for startup until opera-ting conditions support catalytic combustion. In addi-tion, the primary nozzle 20 supplies some fuel for primary combustion during catalytic operation to provide any preheating needed to keep the gas temperature at a cata-lyst entry pla~e~4 at the value needed (i.e. approxi-~v ~ ~ ~
mately 1~00~-- 195~Q~) for efficient catalytic combustion.
The overall combustor operation involves amounts of pri-mary fuel combustion such that NOx production is well below prescribed environmental limits.
An outlet end 26 of the combustor wall 12 is outwardly flared and coupled to a conventional catalyst element 28 ha~ing a honeycomb structure. In turn, the catalyst outlet 30 is coupled to a transition duct (not shown) which directs the ho-t gases to the turbine (not shown3.
Secondary fuel is injected into the combustor 10 during the catalytic combustion phase of operation by a set of circumferentially spaced nozzles 32 at the down-stream end o the primary combustor zone 22. Air may ormay not enter the combustor 10 at the nozzle locations. A
combustor region 34 between the primary zone and the catalyst element 28 provides for mixing of the secondary fuel and air prior to its entry into the catalyst 28. The region 34 is referred to as a mixing zone, and combustion does not occur in this zone since 1ashback can damage the combustor and/or catalyst 28. As more fully described in conn~ction with Figures 2 and 4, a circumferential row of air holes 36 immediately upstream of the secondary fuel ~JCCtlon3 in the combustor sidewall are angled to admit air in the downstream direction to produce uniform mixing of the secondary fuel and air in the mixing zone 34.
50,364 As shown in the enlarged view of Figure 2, internal angular scoops 37 are provided for produciny an angled air stream flow 39 through the holes 36 so as to assist in deflecting the secondary fuel to produce a substantially uniform fuel/air mixture~_for the catalyst ~L~ ç~
38. As shown in Figur~e 2, the angled~air stream 39 signif-~ 3 Q IE~i;) D`r JJ
icantly assists~internal crossflow air 41 in deflecting the fuel spray produced by the secondary fuel nozzles 32.
In Fiyure 3, an alternate embodiment is illustrated in which external scoops 33 produce similar fuel-air mixing action.
Generally, the fuel/air distribution is con-trolled and the center peaked fuel/air mix situation is avoided by taking advantage of the pressure drop across the combustor wall or liner 12. This pressure drop is typically high enough that the velocity of the air enter-ing the combustor 10 through holes is much higher than that of the air already flowing inside the combustor 10.
Therefore, the momentum flux (momentum per unit area per unit time) of the entering air is much higher. With plunged holes or scoops located just upstream of the fuel spray and angled downstream, the high velocity of the air admitted through the holes provides a basis for avoiding the nonuniform center peaked fual/air mix situation. In fact, the angle of the holes can be varied to control the fuel/air mix profile entering the catalyst 28.
With the provision of angled air admission as described, sidewall injection of fuel for catalytic com-bustors is capable of giving the needed even fuel/air mixture approaching the catalyst.
As shown by test results in Figure 4, the cata-lyst outlet temperature, which reflects the catalyst entry fuel/air ratio profile, shows a relatively even distribu tion 44 (i.e. a generally flattened shape) for an embodi-ment of the invention as compared to the cent.er peaked distribution for the prior art. Figure 5 shows the config~
uration used for the prior art in the test while Eigure 6 50,364 shows the invention configuration used in the test. The provision of angled air streams in the invention confiyura-tion is the principal reason for the improvem~nt. I'he improved mixing is believed to occur as a result of deflec-tion of the fuel spray by the angled air s'cream to a moreadvantageous mix location and/or possibly as a result of air boosted turbulent kinetic energy in the region where the secondary fuel spray enters the combustor.
The following are the conditions applicable to the test of Figure 4:
COMPARISON OF CATALYST OUTLET TEMPERATURE
PROFILES FROM FULL SCALE TESTS IN CONCORDVILLE LAB
Prior Art Invention AIR INLET TEMP.: 757F 701F
AIR INLET PRESS.: 100.1 psig 151.6 psig CATALYST APPROACH
VELOCITY: 73.6 fps 79.4 fps PRESSURE DROP: 3.47% 3.85%
(CATALYST3 FUEL/AIR RATIO: 0.0139 0.0136 ATOMIZING AIR
PRESS. DROP, ~SECONDARY NOZZ.:3 73.5 psid 185.3 psid
mately 1~00~-- 195~Q~) for efficient catalytic combustion.
The overall combustor operation involves amounts of pri-mary fuel combustion such that NOx production is well below prescribed environmental limits.
An outlet end 26 of the combustor wall 12 is outwardly flared and coupled to a conventional catalyst element 28 ha~ing a honeycomb structure. In turn, the catalyst outlet 30 is coupled to a transition duct (not shown) which directs the ho-t gases to the turbine (not shown3.
Secondary fuel is injected into the combustor 10 during the catalytic combustion phase of operation by a set of circumferentially spaced nozzles 32 at the down-stream end o the primary combustor zone 22. Air may ormay not enter the combustor 10 at the nozzle locations. A
combustor region 34 between the primary zone and the catalyst element 28 provides for mixing of the secondary fuel and air prior to its entry into the catalyst 28. The region 34 is referred to as a mixing zone, and combustion does not occur in this zone since 1ashback can damage the combustor and/or catalyst 28. As more fully described in conn~ction with Figures 2 and 4, a circumferential row of air holes 36 immediately upstream of the secondary fuel ~JCCtlon3 in the combustor sidewall are angled to admit air in the downstream direction to produce uniform mixing of the secondary fuel and air in the mixing zone 34.
50,364 As shown in the enlarged view of Figure 2, internal angular scoops 37 are provided for produciny an angled air stream flow 39 through the holes 36 so as to assist in deflecting the secondary fuel to produce a substantially uniform fuel/air mixture~_for the catalyst ~L~ ç~
38. As shown in Figur~e 2, the angled~air stream 39 signif-~ 3 Q IE~i;) D`r JJ
icantly assists~internal crossflow air 41 in deflecting the fuel spray produced by the secondary fuel nozzles 32.
In Fiyure 3, an alternate embodiment is illustrated in which external scoops 33 produce similar fuel-air mixing action.
Generally, the fuel/air distribution is con-trolled and the center peaked fuel/air mix situation is avoided by taking advantage of the pressure drop across the combustor wall or liner 12. This pressure drop is typically high enough that the velocity of the air enter-ing the combustor 10 through holes is much higher than that of the air already flowing inside the combustor 10.
Therefore, the momentum flux (momentum per unit area per unit time) of the entering air is much higher. With plunged holes or scoops located just upstream of the fuel spray and angled downstream, the high velocity of the air admitted through the holes provides a basis for avoiding the nonuniform center peaked fual/air mix situation. In fact, the angle of the holes can be varied to control the fuel/air mix profile entering the catalyst 28.
With the provision of angled air admission as described, sidewall injection of fuel for catalytic com-bustors is capable of giving the needed even fuel/air mixture approaching the catalyst.
As shown by test results in Figure 4, the cata-lyst outlet temperature, which reflects the catalyst entry fuel/air ratio profile, shows a relatively even distribu tion 44 (i.e. a generally flattened shape) for an embodi-ment of the invention as compared to the cent.er peaked distribution for the prior art. Figure 5 shows the config~
uration used for the prior art in the test while Eigure 6 50,364 shows the invention configuration used in the test. The provision of angled air streams in the invention confiyura-tion is the principal reason for the improvem~nt. I'he improved mixing is believed to occur as a result of deflec-tion of the fuel spray by the angled air s'cream to a moreadvantageous mix location and/or possibly as a result of air boosted turbulent kinetic energy in the region where the secondary fuel spray enters the combustor.
The following are the conditions applicable to the test of Figure 4:
COMPARISON OF CATALYST OUTLET TEMPERATURE
PROFILES FROM FULL SCALE TESTS IN CONCORDVILLE LAB
Prior Art Invention AIR INLET TEMP.: 757F 701F
AIR INLET PRESS.: 100.1 psig 151.6 psig CATALYST APPROACH
VELOCITY: 73.6 fps 79.4 fps PRESSURE DROP: 3.47% 3.85%
(CATALYST3 FUEL/AIR RATIO: 0.0139 0.0136 ATOMIZING AIR
PRESS. DROP, ~SECONDARY NOZZ.:3 73.5 psid 185.3 psid
Claims (6)
1. A combustor for a land based turbine compris-ing a generally tubular sidewall having a downstream mixing zone where a mixture of fuel and air is developed for downstream combustion, said sidewall further having an upstream primary zone into which air is admitted through sidewall openings to develop an axial airflow for mixing with downstream injection fuel, means for spraying fuel in small rapidly evaporable droplets generally radially inwardly through said sidewall at a location between said primary zone and said mixing zone for mixing with the primary air flow, and means for directing booster air streams angularly downstream against the sprayed fuel to boost the mixing of fuel and air for improved unuformity of the fuel/air mixture at the outlet of mixing zone outlet, said booster air streams having a higher velocity than that of the axial airflow from the primary zone.
2. A combustor as set forth in claim 1 wherein a catalyst is coupled to the combustor sidewall at the outlet of said mixing zone.
3. A combustor as set forth in claim 2 wherein a head end of said combustor upstream from said primary zone includes a primary fuel nozzle which supplies fuel for combustion in said primary zone to supplement the catalytic combustion under limited predetermined operating conditions.
4. A combustor as set forth in claim 2 wherein said air stream directing means are a plurality of circum-ferentially disposed air scoops located in upstream prox-imity to said fuel spraying means and angled downstream to produce said booster air streams.
5. A combustor as set forth in claim 4 wherein said coops are located substantially internally of said combustor sidewall.
6. A combustor as set forth in claim 4 wherein said scoops are located substantially externally of said combustor sidewall.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US40968282A | 1982-08-19 | 1982-08-19 | |
| US409,682 | 1982-08-19 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1209813A true CA1209813A (en) | 1986-08-19 |
Family
ID=23621546
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000434626A Expired CA1209813A (en) | 1982-08-19 | 1983-08-15 | Turbine combustor having more uniform mixing of fuel and air for improved downstream combustion |
Country Status (7)
| Country | Link |
|---|---|
| EP (1) | EP0103159B1 (en) |
| JP (1) | JPS5944524A (en) |
| AR (1) | AR229741A1 (en) |
| CA (1) | CA1209813A (en) |
| DE (1) | DE3368974D1 (en) |
| IE (1) | IE54394B1 (en) |
| MX (1) | MX156751A (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6223537B1 (en) * | 1997-11-24 | 2001-05-01 | Alliedsignal Power Systems | Catalytic combustor for gas turbines |
| US6908232B2 (en) | 2003-03-21 | 2005-06-21 | Agilent Technologies, Inc. | Fiber optic connectors and methods of making the same |
| CN105121962B (en) * | 2013-04-25 | 2018-06-22 | 安萨尔多能源瑞士股份公司 | Continuous burning with diluent gas |
| CN115445130A (en) * | 2022-08-23 | 2022-12-09 | 国网安徽省电力有限公司电力科学研究院 | Pipe flow mechanism for fire monitor |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2579614A (en) * | 1944-06-23 | 1951-12-25 | Allis Chalmers Mfg Co | Combustion chamber with rotating fuel and air stream surrounding a flame core |
| FR2221621B1 (en) * | 1973-03-13 | 1976-09-10 | Snecma | |
| US3937008A (en) * | 1974-12-18 | 1976-02-10 | United Technologies Corporation | Low emission combustion chamber |
| US4118171A (en) * | 1976-12-22 | 1978-10-03 | Engelhard Minerals & Chemicals Corporation | Method for effecting sustained combustion of carbonaceous fuel |
-
1983
- 1983-07-22 IE IE171983A patent/IE54394B1/en unknown
- 1983-08-05 JP JP14263683A patent/JPS5944524A/en active Granted
- 1983-08-09 DE DE8383107832T patent/DE3368974D1/en not_active Expired
- 1983-08-09 EP EP19830107832 patent/EP0103159B1/en not_active Expired
- 1983-08-10 MX MX19834583A patent/MX156751A/en unknown
- 1983-08-12 AR AR29389083A patent/AR229741A1/en active
- 1983-08-15 CA CA000434626A patent/CA1209813A/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| IE831719L (en) | 1984-02-19 |
| DE3368974D1 (en) | 1987-02-12 |
| MX156751A (en) | 1988-09-29 |
| EP0103159B1 (en) | 1987-01-07 |
| IE54394B1 (en) | 1989-09-13 |
| EP0103159A1 (en) | 1984-03-21 |
| JPS622216B2 (en) | 1987-01-19 |
| AR229741A1 (en) | 1983-10-31 |
| JPS5944524A (en) | 1984-03-13 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |