EP1150072A2 - Gasturbinenbrennkammer mit Zuleitungsöffnung - Google Patents
Gasturbinenbrennkammer mit Zuleitungsöffnung Download PDFInfo
- Publication number
- EP1150072A2 EP1150072A2 EP01109768A EP01109768A EP1150072A2 EP 1150072 A2 EP1150072 A2 EP 1150072A2 EP 01109768 A EP01109768 A EP 01109768A EP 01109768 A EP01109768 A EP 01109768A EP 1150072 A2 EP1150072 A2 EP 1150072A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- openings
- flame tube
- combustion chamber
- tube wall
- row
- 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 title claims description 64
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 12
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 12
- 239000003344 environmental pollutant Substances 0.000 description 10
- 231100000719 pollutant Toxicity 0.000 description 10
- 238000013461 design Methods 0.000 description 7
- 230000009467 reduction Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 230000002349 favourable effect Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000005352 clarification Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 239000004071 soot Substances 0.000 description 1
Images
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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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
Definitions
- the invention relates to a gas turbine combustor with at least one pilot burner and at least one main burner, which are axially and radially offset from each other are, the combustion chamber an outer and an inner Flame tube wall includes, in each of which openings for Air supply line are formed, the main burner adjacent to the outer flame tube wall and the pilot burner are arranged adjacent to the inner flame tube wall.
- Gas turbine combustion chambers are known from the prior art, which are designed, for example, as ring combustion chambers are.
- two-zone combustion chambers were developed, where is a zone for combustion at idle speed and Part load and the other zone designed for the upper load range are. It is thus possible to develop the corresponding pollutants to influence optimally.
- the prior art thus shows combustion chambers with stepped Combustion management, in which a pilot stage and a Main level perform different functions. Both Levels can be separated by their respective levels Operating conditions specific pollutant generation mechanisms be optimized.
- the main stage comes here primarily the function of the pollutant emissions in the Pollutants that occur at full load, such as nitrogen oxides and soot compared to conventional combustion chambers to reduce.
- the combustion control in the main stage is designed so that from the main fuel atomizers first set air-fuel ratio, based on the stoichiometric ratio due to excess fuel is marked. By adding air, the mixture becomes into a lean one characterized by excess air Burned state transferred. This admixture or that Mix the half-burned gases with the mixed air done as intensely as possible so that a homogeneously mixed Condition can be set as quickly as possible. On Fast mixing (quenching) minimizes the time spent in the room of the reacting gas in the range of stoichiometric Combustion and affects the formation process of thermal against nitrogen oxides.
- the geometric design is therefore the mixed air openings in the flame tube of the combustion chamber for the pollutant reduction potential of a gas turbine combustion chamber of central importance.
- the mixing openings will continue to be designed the resulting temperature distribution at the combustion chamber outlet or determined at the turbine inlet. Due to high temperatures there is a risk of damage to the high pressure turbine.
- the gas turbine combustion chambers known from the prior art are regarding the reduction of all relevant combustion-related Designed for pollutants.
- combustion chambers are still in a tiered manner Construction known.
- Such, also as two-zone annular combustion chambers designated combustion chambers have an outer and an inner area.
- One of the areas is optimized for combustion at idle and part load, while the other area is designed for the upper load range is.
- a reduction in nitrogen oxide emissions is required however, an optimized pilot hole and the main level.
- the constructions known from the prior art do not solve this task or only partially.
- the pilot burner is known from the prior art and the main burner either in one level or in Arranged circumferentially offset from each other.
- FIG. 96/27766 A1 Another embodiment of an axially stepped double ring combustion chamber WO 96/27766 A1 shows a gas turbine. Also in this document there are openings or holes shown for mixed air jets, but also, similar to the above-mentioned DE 197 20 402 A1 with regard to their design and arrangement no closer are explained.
- DE 28 38 258 A1 describes a combustion chamber arrangement previously known, in which at least one pilot burner and at least one main burner are provided. Either on the outer as well as on the inner combustion chamber wall openings are formed in the form of nozzles are. In contrast to the present construction however, two parallel firing zones are provided, the unite in a common zone relatively late. In this respect there are flow and combustion conditions, which differ fundamentally from the present invention.
- the object of the invention is a gas turbine combustion chamber of the type mentioned at the beginning, which with a simple structure and inexpensive to manufacture in terms of pollutant emissions at different Load ranges is optimized.
- the object is characterized by the features of Main claim solved, the sub-claims show more advantageous embodiments.
- the outer flame tube wall provided with a first arrangement of openings and that in the inner flame tube wall a second arrangement is formed by openings.
- the gas turbine combustor according to the invention stands out through a number of significant advantages.
- Arrangement of the mixed air openings is achieved that with different operating conditions always one optimal combustion can take place so that the pollutant emissions can be reduced considerably.
- the first arrangement of openings train single-row or double-row, whereby in the latter case the openings of the second row in the middle or off-center and back to the intermediate areas of the Openings of the first row can be arranged.
- the supply of mixed air is optimized.
- the second array of openings in the inner Flame tube wall is formed in one row, the openings centered or off-center in the intermediate area of the first Row of openings of the first arrangement of the outer flame tube wall are arranged.
- the second arrangement of openings in the inner flame tube wall can also be designed in two rows, the openings of the first row then being centered or off-center to the intermediate areas of the first row of openings the first arrangement are arranged and wherein the openings the second row in the middle or off-center to the intermediate areas the second row of openings the first Arrangement are arranged.
- the respective openings can be circular or be non-circular.
- the openings either as simple Design holes or use them as drawn holes form an edge pointing into the combustion chamber or with a tubular approach pointing into the combustion chamber Mistake.
- the diameter of the openings in a Range is 0.12 ⁇ d / h ⁇ 0.3, where h is the flame tube height of the main burner and where the diameter d is either the diameter of a circular opening or the hydraulic one Diameter of a non-circular opening is.
- Fig. 1 shows an axial sectional view through an embodiment the combustion chamber 1 according to the invention the staged arrangement of a pilot burner 2, which is used for idling, Part load and full load is used, as well a main burner 3, particularly for full load operation is used, shown.
- the combustion chamber 1 has one outer flame tube wall 4 and an inner flame tube wall 5 and is, as can be seen for example from FIG. 8 leaves, designed as an annular combustion chamber.
- the central axis of the is a plurality of main burners 3 distributed around the circumference provided with the reference number 18.
- Reference numeral 14 denotes the wall of a flame tube 15 of the main burner 3.
- Fig. 1 is a pilot burner 2 assigned or downstream pilot zone 20 shown while reference number 3 denotes a main and mixing zone 30, which is assigned to the main burner.
- 2 shows in view X (viewing direction X according to 1) the arrangement of openings according to a first embodiment, which are formed in the outer flame tube wall 4 are.
- 2 shows a first arrangement 6 of Openings that are double-row.
- the openings The first row is 8, the openings of the second row designated 9.
- the openings are circular.
- the Openings 9 of the second row are in the middle in the intermediate area arranged between the openings 8.
- Are dashed Openings 11 of the inner flame tube wall 5 are shown. By the projection these openings appear oval or elliptical, however, they are designed as round openings.
- the Openings 11 are in Fig. 2 and the other figures Clarification "behind" the openings 8 and 9 respectively.
- the outer flame tube wall 4 thus has a double-row mixing hole.
- the hole diameter the openings 8 of the first row and the openings 9 of the second row of the first arrangement 6 can either be with each other be the same or different size.
- the assignment both rows are offset by the distance a, that is the hole axes of both rows are aligned, seen downstream not or do not lie in one plane of a longitudinal section through the combustion chamber.
- the opposite row of holes on the inner flame tube wall is in the embodiment single row and designed in such a way that the graduation of the Hole axes to be aligned with the main burner axes 18 comes or lies in one plane to the main burner axes.
- the hole diameter of the openings 11 of this second arrangement 7 of openings in the inner flame tube wall 5 can each be the same or different size.
- the assignment the openings of the inner flame tube wall 5 to the outer Flame tube wall 4 is selected in the exemplary embodiment so that the hole axes are either aligned or offset to the first row of openings 8 or the second row of openings 9 of the outer flame tube wall 4 are arranged.
- FIG. 3 shows the position of the first arrangement 6 of openings 8 or 9 of the outer flame tube wall 4. It thus results the axial, downstream position of the openings.
- the value t gives the distance between the openings on the outer one Flame tube wall 4 to the wall 14 of the flame tube 15 or Main burner outlet level 19. The distance t is thus the distance of the axes of the recesses.
- the flame tube height h which is the height of the flame tube the main combustion zone.
- FIG. 4 shows different positions of the openings 11 to 13 of the first and second series of second arrangements 7 of the inner flame tube wall 5.
- FIG. 5 shows a modified design of the inner Flame tube wall 5 in an analogous representation of the "positions".
- the exit axes of the openings 11, 12, 13 of the inner Flame tube wall 5 are aligned so that they are on an area the combustion chamber, which through the intersection A the main burner axis 18 with the main burner exit plane 19 and the intersection point C of the axis of the arrangement 6 of openings 8 to 10 of the outer flame tube wall 4 is limited.
- the maximum upstream alignment is thus one directed to the entry plane of the main burner axis 18 Center axis of the recesses 11 to 13 (point A) limited.
- the maximum downstream alignment of the openings 11 to 13 of the inner flame tube wall 5 is by a the exit plane of the second downstream row of FIG. 8 limited to 10 of the outer flame tube wall 4 (point C).
- the Fig. 4 shows three "positions" of the openings 11 to 13 of the inner flame tube wall 5 in an exemplary representation. It it goes without saying that the flame tube wall 5 is different on the one hand Can have contours (see differences 4 and 5) and additional "positions" of the openings in the specified range.
- the specified "positions" the openings 11 to 13 are therefore all in the range of Main zone of the main burner 3 while the exit directions of the openings not in the area of the pilot zone of the pilot burner 2 extend.
- FIG. 6 shows different configurations of the openings 8 to 13 specified.
- the opening has a tubular extension 17 which extends extends into the combustion chamber, the opening is thus "chuted".
- the middle embodiment of FIG. 6 is a simple, circular hole (plain).
- the right embodiment variant of FIG. 6 has one plunged on, with one pointing towards the edge of the combustion chamber 16. It understands themselves that the openings are circular or non-circular could be.
- the size of the openings is for all in openings through a region described in the invention limited by 0.12 ⁇ d / h ⁇ 0.3. d corresponds to that Diameter of a circular opening or the hydraulic one Diameter of a non-circular opening.
- H is the flame tube height of the main burner (see Fig. 3).
- Fig. 7 shows a further embodiment, in which in only a row of openings 10 in the outer flame tube wall is formed, while the inner flame tube wall a second, includes a row arrangement of openings 11.
- the openings are circular, appear in dashed lines Representation of FIG. 7, however, conditionally as ellipses by the direction of view of "View X".
- the diameter of the openings 10 within the row can be the same or different sizes.
- the second arrangement 7 of openings 11 of the inner flame tube wall 5 is formed in one row and arranged so that the hole axes are staggered in relation to the hole axes of the openings 10 of the outer flame tube wall 4.
- the diameter of the Openings 11 of the inner flame tube wall 5 can be the same or be of different sizes. In this embodiment it is irrelevant whether all or certain hole axes of the Openings 11 of the inner flame tube wall 5 or the openings 10 of the outer flame tube wall 4 in levels of the main burner 3 lie or not.
- FIG 8 shows an axial partial sectional view of the invention Combustion chamber.
- reference number 22 shows the air flows through the outer flame tube wall
- reference numeral 21 air flows from the inner Flame tube wall 5 represents. It follows that the Comb individual jets of mixed air.
- FIG. 9 is another embodiment of the arrangement of the openings shown.
- the arrangement is analogous to the illustration 7, wherein the first arrangement 6 of openings the outer flame tube wall 4 is also double-row is like the second arrangement 7 of openings of the inner Flame tube wall 5.
- the openings 13 the second row and the openings 12 of the first row the second arrangement 7 of openings of the inner flame tube wall 5 shown elliptically, since Fig. 9 is a view in Viewing direction X shows. This results in opposing ones Rows of openings in terms of their arrangement comb together.
- the invention relates to a gas turbine combustion chamber with at least a pilot burner 2 and at least one main burner 3, which are axially and radially offset from one another are, the combustion chamber 1 an outer 4 and an inner 5 flame tube wall, in each of which openings are designed to supply air, the main burner 3 to the outer flame tube wall 4 and the pilot burner 2 are arranged adjacent to the inner flame tube wall 5, characterized in that the outer flame tube wall 4 with a first arrangement 6 of openings is provided and that in the inner flame tube wall 5 a second arrangement 7 of Openings is formed, which is behind the first arrangement 6 is arranged. (Fig. 1).
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
Description
- Fig. 1
- eine vereinfachte, schematische Axialschnitt-Ansicht einer erfindungsgemäßen Brennkammer,
- Fig. 2
- eine Ansicht eines Ausführungsbeispiels der Belochung der äußeren Flammrohrwand,
- Fig. 3
- eine Seiten-Schnittansicht, analog Fig. 1, mit Angabe der Bemessungswerte der Flammrohrhöhe und der Lage der Öffnungen der äußeren Flammrohrwand,
- Fig. 4
- eine Schnittansicht, ähnlich den Figuren 1 und 3, in welcher die Lagen der Öffnungen der inneren Flammrohrwand dargestellt sind,
- Fig. 5
- eine Schnittansicht eines Ausführungsbeispiels der inneren Flammrohrwand in Abwandlung zu der Darstellung gemäß Fig. 4,
- Fig. 6
- verschiedene Ausgestaltungsformen der Öffnungen in der Flammrohrwand,
- Fig. 7
- ein weiteres Ausführungsbeispiel einer Belochung, analog der Darstellung gemäß Fig. 2,
- Fig. 8
- eine axiale Seitenansicht eines Teilbereichs der Ringbrennkammer mit Darstellung der Luftaustrittsströmungen, und
- Fig. 9
- eine Darstellung eines weiteren Ausführungsbeispieles der Belochung, analog der Darstellung in den Fig. 2 und 7.
- 1
- Brennkammer
- 2
- Pilotbrenner
- 3
- Hauptbrenner
- 4
- äußere Flammrohrwand
- 5
- innere Flammrohrwand
- 6
- erste Anordnung von Öffnungen in äußerer Flammrohrwand 4
- 7
- zweite Anordnung von Öffnungen in innerer Flammrohrwand 5
- 8
- Öffnungen der ersten Reihe der ersten Anordnung 6
- 9
- Öffnungen der zweiten Reihe der ersten Anordnung 6
- 10
- Öffnungen der ersten Anordnung 6
- 11
- Öffnungen der zweiten Anordnung 7
- 12
- Öffnungen der erste Reihe der zweiten Anordnung 7
- 13
- Öffnungen der zweiten Reihe der zweiten Anordnung 7
- 14
- Wand des Flammrohrs 15 des Hauptbrenners 3
- 15
- Flammrohr des Hauptbrenners 3
- 16
- Rand
- 17
- rohrförmiger Ansatz
- 18
- Achse des Hauptbrenners 3
- 19
- Hauptbrenneraustrittsebene
- 20
- Pilotzone
- 21
- Luftstrahl von innen
- 22
- Luftstrahl von außen
- 30
- Haupt- und Mischzone
- A
- Schnittpunkt der Hauptbrennerachse mit Wand 14
- B
- Schnittpunkt der Lochachse der ersten Reihe der ersten Anordnung 8 mit der Innenwandseite der äußeren Flammrohrwand 15
- c
- Schnittpunkt der Lochachse der zweiten Reihe der ersten Anordnung 9 mit der Innenwandseite der äußeren Flammrohrwand 15
- D
- Schnittpunkt der Lochachse der ersten Reihe der zweiten Anordnung 7 mit der Innenwandseite der inneren Flammrohrwand 15
- X
- Ansicht auf Außenwand der äußeren Flammrohres
Claims (11)
- Gasturbinenbrennkammer mit zumindest einer einem Pilotbrenner (2) zugeordneten separaten Pilotzone (20) und zumindest einer einem Hauptbrenner (3) zugeordneten gemeinsamen Haupt- und Mischzone (30), welche zueinander axial und radial versetzt angeordnet sind, wobei die gemeinsame Haupt- und Mischzone (30) eine äußere (4) und eine innere (5) Flammrohrwand umfasst, in welchen jeweils Öffnungen zur Zuleitung von Luft ausgebildet sind, wobei der Hauptbrenner (3) an die äußere Flammrohrwand (4) und der Pilotbrenner (2) angrenzend an die innere Flammrohrwand (5) angeordnet sind, dadurch gekennzeichnet, dass die äußere Flammrohrwand (4) mit einer ersten Anordnung (6) von einreihigen Öffnungen der gemeinsamen Haupt- und Mischzone (30) versehen ist und dass in der inneren Flammrohrwand (5) eine zweite Anordnung (7) von einreihigen Öffnungen ausgebildet ist, wobei die Öffnungen (11) mittig oder außermittig zu dem Zwischenbereich der ersten Reihe von Öffnungen (8) der ersten Anordnung (6) der äußeren Flammrohrwand (4) angeordnet sind .
- Gasturbinenbrennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die erste Anordnung (6) von Öffnungen doppelreihig ausgebildet ist, wobei die Öffnungen (9) der zweiten Reihe mittig oder außermittig und nach hinten zu dem Zwischenbereich der Öffnungen (8) der ersten Reihe angeordnet sind.
- Gasturbinenbrennkammer nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass die zweite Anordnung (7) von Öffnungen der inneren Flammrohrwand (5) zweireihig ausgebildet ist, wobei die Öffnungen (12) der ersten Reihe mittig oder außermittig zu den Zwischenbereichen der ersten Reihe von Öffnungen (8) der ersten Anordnung (6) angeordnet sind und wobei die Öffnungen (13) der zweiten Reihe mittig oder außermittig zu den Zwischenbereichen der ersten Reihe von Öffnungen (9) der ersten Anordnung (6) angeordnet sind.
- Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der Abstand t1 der Mittelpunkte der Öffnungen (8) der ersten Reihe und der Abstand t2 der Mittelpunkte der Öffnungen (9) der zweiten Reihe der ersten Anordnung (6) in der äußeren Flammrohrwand (4) von einer stromaufwärtigen Wand (14) eines Flammrohres (15) des Hauptbrenners (3) (Ebene Hauptbrenneraustritt) zu der Höhe h des Flammrohres (15) folgenden Beziehungen genügen:t1/h = 0,4 (minimaler Abstand)t2/h = 1,2 (maximaler Abstand).
- Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Öffnungen (8 bis 13) kreisrund ausgebildet sind.
- Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Öffnungen (8 bis 13) nicht-kreisrund ausgebildet sind.
- Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Öffnungen (8 bis 13) als einfache Löcher ausgebildet sind.
- Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Öffnungen (8 bis 13) als gezogene Löcher mit einem geringen, in die Brennkammer (1) weisenden Rand (16) ausgebildet sind.
- Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Öffnungen (8 bis 13) einen rohrförmigen, in die Brennkammer (1) weisenden Ansatz (17) aufweisen.
- Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass die Austrittsachse der Öffnungen (11, 12, 13) der inneren Flammrohrwand (5) so ausgebildet ist, dass sie auf einen Bereich der Brennkammer treffen, der durch den Schnittpunkt (A) der Hauptbrennerachse (18) mit der Hauptbrenneraustrittsebene (19) und den Schnittpunkt (C) der Achse der Anordnung (6) von Öffnungen (8, 9, 10) mit der äußeren Flammrohrwand (4) begrenzt wird.
- Gasturbinenbrennkammer nach einem der Ansprüche 1 bis 10, dadurch gekennzeichnet, dass der Durchmesser d der Öffnungen (8-10; 11-13) in einem Bereich von 0,12 ≤ d/h ≤ 0,3 liegt, wobei h die Flammrohrhöhe des Hauptbrenners ist.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10020598A DE10020598A1 (de) | 2000-04-27 | 2000-04-27 | Gasturbinenbrennkammer mit Zuleitungsöffnungen |
| DE10020598 | 2000-04-27 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1150072A2 true EP1150072A2 (de) | 2001-10-31 |
| EP1150072A3 EP1150072A3 (de) | 2001-12-19 |
| EP1150072B1 EP1150072B1 (de) | 2006-07-05 |
Family
ID=7640079
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01109768A Expired - Lifetime EP1150072B1 (de) | 2000-04-27 | 2001-04-20 | Gasturbinenbrennkammer mit Zuleitungsöffnung |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US7654089B2 (de) |
| EP (1) | EP1150072B1 (de) |
| DE (2) | DE10020598A1 (de) |
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| EP4198396A1 (de) * | 2021-12-16 | 2023-06-21 | Rolls-Royce Deutschland Ltd & Co KG | Brennkammerbaugruppe mit spezifisch angeordneten mischluftlöchern an innerer und äusserer brennkammerwand |
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| FR2897143B1 (fr) * | 2006-02-08 | 2012-10-05 | Snecma | Chambre de combustion d'une turbomachine |
| US8616004B2 (en) * | 2007-11-29 | 2013-12-31 | Honeywell International Inc. | Quench jet arrangement for annular rich-quench-lean gas turbine combustors |
| US8171740B2 (en) * | 2009-02-27 | 2012-05-08 | Honeywell International Inc. | Annular rich-quench-lean gas turbine combustors with plunged holes |
| US9416970B2 (en) * | 2009-11-30 | 2016-08-16 | United Technologies Corporation | Combustor heat panel arrangement having holes offset from seams of a radially opposing heat panel |
| US8850819B2 (en) * | 2010-06-25 | 2014-10-07 | United Technologies Corporation | Swirler, fuel and air assembly and combustor |
| US9416972B2 (en) * | 2011-12-07 | 2016-08-16 | Pratt & Whitney Canada Corp. | Two-stage combustor for gas turbine engine |
| EP2912381B1 (de) | 2012-10-24 | 2018-06-13 | Ansaldo Energia Switzerland AG | Sequenzielle verbrennung mit verdünnungsgasmischer |
| CN105121962B (zh) * | 2013-04-25 | 2018-06-22 | 安萨尔多能源瑞士股份公司 | 具有稀释气体的连续燃烧 |
| EP3008391B1 (de) | 2013-06-11 | 2020-05-06 | United Technologies Corporation | Brennkammer mit axialer stufung für einen gasturbinenmotor |
| EP2957833B1 (de) | 2014-06-17 | 2018-10-24 | Rolls-Royce Corporation | Brennkammeranordnung mit rinnen |
| US9453646B2 (en) * | 2015-01-29 | 2016-09-27 | General Electric Company | Method for air entry in liner to reduce water requirement to control NOx |
| US11754284B2 (en) | 2021-11-11 | 2023-09-12 | General Electric Company | Combustion liner |
| US11686473B2 (en) | 2021-11-11 | 2023-06-27 | General Electric Company | Combustion liner |
| US11808454B2 (en) | 2021-11-11 | 2023-11-07 | General Electric Company | Combustion liner |
| US12173900B2 (en) | 2021-11-11 | 2024-12-24 | General Electric Company | Combustion liner having a dilution passage |
| US12130016B1 (en) * | 2023-05-31 | 2024-10-29 | General Electric Company | Turbine engine including a combustor |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2838258A1 (de) | 1977-09-02 | 1979-03-15 | Snecma | Brennkammeranordnung |
| WO1996027766A1 (de) | 1995-03-08 | 1996-09-12 | Bmw Rolls-Royce Gmbh | Axial gestufte doppelring-brennkammer einer gasturbine |
| DE19720402A1 (de) | 1997-05-15 | 1998-11-19 | Bmw Rolls Royce Gmbh | Axial gestufte Ringbrennkammer einer Gasturbine |
| EP0927854A2 (de) | 1997-12-31 | 1999-07-07 | United Technologies Corporation | Gasturbinenbrenner mit niedrigem NOx Ausstoss |
| EP0943868A2 (de) | 1998-03-18 | 1999-09-22 | General Electric Company | Gasturbinenbrennkammer |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5284019A (en) * | 1990-06-12 | 1994-02-08 | The United States Of America As Represented By The Secretary Of The Air Force | Double dome, single anular combustor with daisy mixer |
| JPH05149543A (ja) | 1991-11-27 | 1993-06-15 | Mitsubishi Heavy Ind Ltd | ガスタービンの燃焼器 |
| FR2686683B1 (fr) * | 1992-01-28 | 1994-04-01 | Snecma | Turbomachine a chambre de combustion demontable. |
| US5406799A (en) * | 1992-06-12 | 1995-04-18 | United Technologies Corporation | Combustion chamber |
| FR2727193B1 (fr) * | 1994-11-23 | 1996-12-20 | Snecma | Chambre de combustion a deux tetes fonctionnant du ralenti au plein gaz |
| FR2748088B1 (fr) * | 1996-04-24 | 1998-05-29 | Snecma | Optimisation du melange de gaz brules dans une chambre de combustion annulaire |
| FR2770283B1 (fr) * | 1997-10-29 | 1999-11-19 | Snecma | Chambre de combustion pour turbomachine |
| US6474070B1 (en) * | 1998-06-10 | 2002-11-05 | General Electric Company | Rich double dome combustor |
-
2000
- 2000-04-27 DE DE10020598A patent/DE10020598A1/de not_active Withdrawn
-
2001
- 2001-04-20 EP EP01109768A patent/EP1150072B1/de not_active Expired - Lifetime
- 2001-04-20 DE DE50110374T patent/DE50110374D1/de not_active Expired - Lifetime
- 2001-04-27 US US09/843,168 patent/US7654089B2/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2838258A1 (de) | 1977-09-02 | 1979-03-15 | Snecma | Brennkammeranordnung |
| WO1996027766A1 (de) | 1995-03-08 | 1996-09-12 | Bmw Rolls-Royce Gmbh | Axial gestufte doppelring-brennkammer einer gasturbine |
| DE19720402A1 (de) | 1997-05-15 | 1998-11-19 | Bmw Rolls Royce Gmbh | Axial gestufte Ringbrennkammer einer Gasturbine |
| EP0927854A2 (de) | 1997-12-31 | 1999-07-07 | United Technologies Corporation | Gasturbinenbrenner mit niedrigem NOx Ausstoss |
| EP0943868A2 (de) | 1998-03-18 | 1999-09-22 | General Electric Company | Gasturbinenbrennkammer |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4198396A1 (de) * | 2021-12-16 | 2023-06-21 | Rolls-Royce Deutschland Ltd & Co KG | Brennkammerbaugruppe mit spezifisch angeordneten mischluftlöchern an innerer und äusserer brennkammerwand |
Also Published As
| Publication number | Publication date |
|---|---|
| DE10020598A1 (de) | 2002-03-07 |
| US7654089B2 (en) | 2010-02-02 |
| EP1150072B1 (de) | 2006-07-05 |
| US20020017101A1 (en) | 2002-02-14 |
| EP1150072A3 (de) | 2001-12-19 |
| DE50110374D1 (de) | 2006-08-17 |
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