EP1384950A2 - Annular combustion chamber for a gas turbine - Google Patents
Annular combustion chamber for a gas turbine Download PDFInfo
- Publication number
- EP1384950A2 EP1384950A2 EP03405504A EP03405504A EP1384950A2 EP 1384950 A2 EP1384950 A2 EP 1384950A2 EP 03405504 A EP03405504 A EP 03405504A EP 03405504 A EP03405504 A EP 03405504A EP 1384950 A2 EP1384950 A2 EP 1384950A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- lining segments
- segments
- chamber according
- divided
- 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
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
Definitions
- the present invention relates to the field of gas turbine technology. It relates to an annular combustion chamber for a gas turbine according to the Preamble of claim 1.
- Such a combustion chamber as e.g. 3 is shown at Gas turbines in use for a long time.
- the combustion chamber 26, which is part of a gas turbine, not shown and of which only the section above the turbine axis is reproduced extends in the longitudinal direction along the turbine axis in Flow direction (from right to left in Fig. 3).
- On the entry page (right Page in Fig. 3) is a number on a circular ring concentric to the turbine axis distributed by burners 27, which in the present case are known as so-called Double cone burners are designed according to EP 0321809.
- burners 27 which in the present case are known as so-called Double cone burners are designed according to EP 0321809.
- the swirling fuel-air mixture emerging from the burners 27 burns with flame formation in the primary zone following the burner 27 30 and the resulting hot gases emerge from the combustion chamber 26 at one Combustion chamber outlet 31 out and into the subsequent turbine section, where it expand under work performance.
- Protecting gases are on the inside of the combustion chamber walls 29 special lining segments ("liner segments") 28 arranged and attached.
- the lining segments 28 are continuous in the axial direction and therefore as long as the interior of the combustion chamber 26. This has the advantage that the number of parts and the length of the leaky column is minimal.
- the known configuration of the lining segments has the disadvantage that that the segments are comparatively long. This creates in terms of manufacturability and mechanical integrity problems. These problems will be even larger and possibly not solvable if for very large gas turbines correspondingly large combustion chambers with very long lining segments are needed.
- the object is achieved by the entirety of the features of claim 1.
- the essence of the invention is that in a combustion chamber the mentioned type, the lining segments in the axial direction in several successive arranged parts are divided. By dividing the individual Partial elements smaller, which simplifies their manufacture and the mechanical stability increased. At the same time, the assembly of the segments is simplified.
- the lining segments according to a preferred embodiment of the invention in two parts are divided when the liner segments are divided where the flow rate the hot gases is low, or if the liner segments are divided such that the lengths of the individual segment parts in axial direction are approximately the same.
- the assembly can be further simplified if according to another embodiment the invention the lining segments attached to segment carriers are, and the segment carrier also divided into several parts in the axial direction are.
- the lining segments are preferably convection-cooled.
- the divided lining segments can be separately convection-cooled be through the downstream portions of the liner segments flowing cooling medium into the hot gas flow of the combustion chamber becomes.
- Connection channels are provided through which the convectively cooling cooling medium from one part of the lining segments to the other part of the lining segments can flow.
- Fig. 1 is a section through a combustion chamber arranged in a gas turbine with lining segments subdivided in the axial direction according to a preferred Embodiment of the invention reproduced.
- the gas turbine 10 from which is only shown a part lying above the turbine axis has one outer turbine housing 11 on which a filled with compressed air Surrounds plenum 12, in which the actual annular combustion chamber 13 is arranged is.
- the flow course takes place from right to left in FIG. 1.
- burners 14, 15 which in two
- the fuel-air mixture enters the primary zone one above the other 32 blown into the combustion chamber 13 and burns there with the formation of flames.
- the resulting hot gases pass through the combustion chamber outlet 33 out of the combustion chamber 13 and into the subsequent turbine.
- the combustion chamber 13 is separated from the surrounding plenum by several segment carriers 18, .., 21 12 separated.
- segment carriers 18, .., 21 On the inner walls of the segment carrier 18, .., 21 are in axial First and second lining segments 16 and 17 fastened in the direction one behind the other, with inner (in Fig. 1 lower) and outer (in Fig. 1 upper) lining segments are provided.
- the split liner segments 16, 17 have about the same (axial) length and are separated where the corresponding ones Butt segment carriers 19, 20 and 18, 21 together.
- the place where the butted divided liner segments 16, 17 (space 24 in Fig. 2), is where the flow rate of the hot gases is low.
- the split liner segments 16, 17 are convection cooled in the same way, as is already the case with the undivided lining segments is.
- the division of the segment carriers 18, .., 21 ensures that the assembly is simplified. This applies in particular to the inner (lower) lining. If the inner lining is assembled from two parts, the Separation gap screwed along the entire length. The dividing line the segment carrier 18, 21 for the second lining segments 17 are for Bolt accessible so that a wedge is no longer needed.
- the division of the lining segments according to the invention makes it possible to to realize larger combustion chambers without having correspondingly large ones Segments must be constructed. This way you can look at already proven ones Use segment sizes.
- the invention also makes it possible in different Gas turbines have the same burners 14, 15 and first liner segments 16 to use. Adapted to different turbine inlet geometries then only the combustion chamber outlet 33 with the second lining segments 17 and their segment carriers 18, 21.
- the configuration of the liner segments 16, 17 is the same as for the EV and SEV combustion chambers of the known gas turbines of the applicant of the type GT24B and GT26B (see the article by D. K. Mukherjee "State-of-the-art gas turbines - a brief update ", ABB review 2/1997, pp. 4-14 (1997)).
- a specialty is the provision of connecting channels 22, 23 (Fig. 1 and Fig. 2) between the second liner segments 17 and the first liner segments 16. Through these connecting channels 22, 23 for the convective cooling of the Lining segments 16, 17 used cooling air from the second lining segments 17 flow into the first lining segments 16 and there to Contribute cooling.
- the cooling system of the second liner segments 17 is operated only with a part of the total cooling mass flow to the flow velocities to avoid pressure drops in the connection channels 22, 23 to keep small.
- the transition area between the inner second and first liner segments 17 and 16 is in Fig. 2 shown enlarged.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die vorliegende Erfindung bezieht sich auf das Gebiet der Technik von Gasturbinen.
Sie betrifft eine ringförmige Brennkammer für eine Gasturbine gemäss dem
Oberbegriff des Anspruchs 1.The present invention relates to the field of gas turbine technology.
It relates to an annular combustion chamber for a gas turbine according to the
Preamble of
Eine solche Brennkammer, wie sie z.B. in der Fig. 3 wiedergegeben ist, ist bei Gasturbinen seit längerem im Einsatz.Such a combustion chamber as e.g. 3 is shown at Gas turbines in use for a long time.
In Fig. 3 ist in einer Schnittdarstellung eine ringförmige Brennkammer, eine sogenannte
EV-Brennkammer (EV = Environmental), nach dem Stand der Technik
wiedergegeben. Die Brennkammer 26, die Teil einer nicht dargestellten Gasturbine
ist und von der nur der oberhalb der Turbinenachse liegende Abschnitt wiedergegeben
ist, erstreckt sich in Längsrichtung entlang der Turbinenachse in
Strömungsrichtung (in Fig. 3 von rechts nach links). Auf der Eintrittsseite (rechte
Seite in Fig. 3) ist auf einem zur Turbinenachse konzentrischen Kreisring eine Anzahl
von Brennern 27 verteilt angeordnet, die im vorliegenden Fall als sogenannte
Doppelkegelbrenner gemäss EP 0321809 ausgebildet sind. Dies ist indes keine
zwingende Voraussetzung, und es versteht sich von selbst, dass die hier diskutierten
Brennkammern auch mit anderen Brennervarianten betrieben werden können.
Das aus den Brennern 27 austretende, verwirbelte Brennstoff-Luft-Gemisch
verbrennt unter Flammenbildung in der auf die Brenner 27 folgenden Primärzone
30 und die entstehenden heissen Gase treten aus der Brennkammer 26 an einem
Brennkammeraustritt 31 aus und in den nachfolgenden Turbinenteil ein, wo sie
unter Arbeitsleistung expandieren. Um die Brennkammerwände 29 vor den heissen
Gasen zu schützen, sind auf der Innenseite der Brennkammerwände 29
spezielle Auskleidungssegmente ("liner segments") 28 angeordnet und befestigt.
Die Auskleidungssegmente 28 sind in axialer Richtung durchgehend ausgebildet
und daher so lang wie der Innenraum der Brennkammer 26. Dies hat den Vorteil,
dass die Anzahl der Teile und die Länge der undichten Spalte minimal ist.In Fig. 3 is a sectional combustion chamber, a so-called
EV combustion chamber (EV = Environmental), according to the state of the art
played. The
Nachteilig ist bei der bekannten Konfiguration der Auskleidungssegmente jedoch, dass die Segmente vergleichsweise lang sind. Dies schafft hinsichtlich der Herstellbarkeit und der mechanischen Integrität Probleme. Diese Probleme werden noch grösser und möglicherweise nicht lösbar, wenn für sehr grosse Gasturbinen entsprechend grosse Brennkammern mit sehr langen Auskleidungssegmenten benötigt werden.However, the known configuration of the lining segments has the disadvantage that that the segments are comparatively long. This creates in terms of manufacturability and mechanical integrity problems. These problems will be even larger and possibly not solvable if for very large gas turbines correspondingly large combustion chambers with very long lining segments are needed.
Es ist daher Aufgabe der Erfindung, eine Brennkammer zu schaffen, welche die oben beschriebenen Nachteile bekannter Brennkammern vermeidet und sich durch eine Vereinfachung der Herstellung und Montage sowie eine verbesserte mechanische Stabilität und mechanische und thermische Belastbarkeit auszeichnet.It is therefore an object of the invention to provide a combustion chamber which Avoids disadvantages of known combustion chambers described above and itself by simplifying production and assembly, as well as improved mechanical stability and mechanical and thermal resilience.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruches 1 gelöst.
Der Kern der Erfindung besteht darin, dass bei einer Brennkammer der eingangs
genannten Art die Auskleidungssegmente in axialer Richtung in mehrere hintereinander
angeordnete Teile unterteilt sind. Durch die Aufteilung werden die einzelnen
Teilelemente kleiner, wodurch sich ihre Herstellung vereinfacht und die
mechanische Stabilität erhöht. Gleichzeitig vereinfacht sich die Montage der Segmente.The object is achieved by the entirety of the features of
Es hat sich dabei als besonders günstig herausgestellt, wenn die Auskleidungssegmente gemäss einer bevorzugten Ausgestaltung der Erfindung in zwei Teile unterteilt sind, wenn die Auskleidungssegmente dort unterteilt sind, wo die Strömungsgeschwindigkeit der heissen Gase niedrig ist, oder wenn die Auskleidungssegmente derart unterteilt sind, dass die Längen der einzelnen Segmentteile in axialer Richtung in etwa gleich sind.It has been found to be particularly favorable if the lining segments according to a preferred embodiment of the invention in two parts are divided when the liner segments are divided where the flow rate the hot gases is low, or if the liner segments are divided such that the lengths of the individual segment parts in axial direction are approximately the same.
Die Montage kann weiter vereinfacht werden, wenn gemäss einer anderen Ausgestaltung der Erfindung die Auskleidungssegmente an Segmentträgern befestigt sind, und die Segmentträger ebenfalls in axialer Richtung in mehrere Teile unterteilt sind.The assembly can be further simplified if according to another embodiment the invention the lining segments attached to segment carriers are, and the segment carrier also divided into several parts in the axial direction are.
Bevorzugt sind die Auskleidungssegmente konvektionsgekühlt.The lining segments are preferably convection-cooled.
Dabei können die unterteilten Auskleidungssegmente separat konvektionsgekühlt sein, wobei das durch die stromabwärts gelegenen Teile der Auskleidungssegmente strömende Kühlmedium in den Heissgasstrom der Brennkammer ausgelassen wird.The divided lining segments can be separately convection-cooled be through the downstream portions of the liner segments flowing cooling medium into the hot gas flow of the combustion chamber becomes.
Es ist aber auch denkbar, dass zwischen den unterteilten Auskleidungssegmenten Verbindungskanäle vorgesehen sind, durch welche das konvektiv kühlende Kühlmedium vom einen Teil der Auskleidungssegmente in den anderen Teil der Auskleidungssegmente strömen kann.But it is also conceivable that between the subdivided lining segments Connection channels are provided through which the convectively cooling cooling medium from one part of the lining segments to the other part of the lining segments can flow.
Weitere Ausführungsformen ergeben sich aus den abhängigen Ansprüchen.Further embodiments result from the dependent claims.
Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigen
- Fig. 1
- einen Schnitt durch eine in einer Gasturbine angeordnete Brennkammer mit in axialer Richtung unterteilten Auskleidungssegmenten gemäss einem bevorzugten Ausführungsbeispiel der Erfindung;
- Fig. 2
- einen vergrösserten Ausschnitt aus der Darstellung der Fig. 1; und
- Fig. 3
- einen Schnitt durch eine ringförmige Brennkammer nach dem Stand der Technik.
- Fig. 1
- a section through a combustion chamber arranged in a gas turbine with lining segments subdivided in the axial direction according to a preferred embodiment of the invention;
- Fig. 2
- an enlarged section of the illustration of Fig. 1; and
- Fig. 3
- a section through an annular combustion chamber according to the prior art.
In Fig. 1 ist ein Schnitt durch eine in einer Gasturbine angeordnete Brennkammer
mit in axialer Richtung unterteilten Auskleidungssegmenten gemäss einem bevorzugten
Ausführungsbeispiel der Erfindung wiedergegeben. Die Gasturbine 10, von
der nur ein oberhalb der Turbinenachse liegender Teil dargestellt ist, weist eine
äusseres Turbinengehäuse 11 auf welches ein mit komprimierter Luft gefülltes
Plenum 12 umgibt, in dem die eigentliche ringförmige Brennkammer 13 angeordnet
ist. Der Strömungsverlauf erfolgt in Fig. 1 von rechts nach links. Durch die in
einem Kopfraum der Brennkammer 13 angeordneten Brenner 14, 15, die in zwei
Reihen übereinander liegen, wird das Brennstoff-Luft-Gemisch in die Primärzone
32 der Brennkammer 13 eingeblasen und verbrennt dort unter Bildung von Flammen.
die entstehenden heissen Gase treten durch den Brennkammeraustritt 33
aus der Brennkammer 13 aus und in die nachfolgende Turbine ein. Die Brennkammer
13 wird durch mehrere Segmentträger 18,..,21 vom umgebenden Plenum
12 abgetrennt. An den Innenwänden der Segmentträger 18,..,21 sind in axialer
Richtung hintereinander erste und zweite Auskleidungssegmente 16 und 17 befestigt,
wobei jeweils innere (in Fig. 1 untere) und äussere (in Fig. 1 obere) Auskleidungssegmente
vorgesehen sind. Die geteilten Auskleidungssegmente 16, 17 haben
in etwa die gleiche (axiale) Länge und sind dort getrennt, wo auch die zugehörigen
Segmentträger 19, 20 und 18, 21 aneinanderstossen. Die Stelle, an der die
geteilten Auskleidungssegmente 16, 17 aneinanderstossen (Zwischenraum 24 in
Fig. 2), liegt dort, wo die Strömungsgeschwindigkeit der heissen Gase niedrig ist.
Die geteilten Auskleidungssegmente 16, 17 sind in der gleichen Weise konvektionsgekühlt,
wie dies bereits bei den ungeteilten Auskleidungssegmente der Fall
ist.In Fig. 1 is a section through a combustion chamber arranged in a gas turbine
with lining segments subdivided in the axial direction according to a preferred
Embodiment of the invention reproduced. The
Durch die Teilung der Segmentträger 18,..,21 wird erreicht, dass der Zusammenbau
vereinfacht wird. Dies gilt insbesondere für die innere (untere) Auskleidung.
Wenn die innere Auskleidung aus zwei Teilen zusammengebaut wird, kann der
Trennungsspalt über die gesamte Länge verschraubt werden. Die Trennungslinie
der Segmentträger 18, 21 für die zweiten Auskleidungssegmente 17 sind dabei für
Schraubbolzen zugänglich, so dass ein Keil nicht länger benötigt wird.The division of the
Durch die erfindungsgemässe Aufteilung der Auskleidungssegmente wird es möglich,
grössere Brennkammern zu verwirklichen, ohne dass entsprechend grosse
Segmente konstruiert werden müssen. Auf diese Weise kann man auf bereits bewährte
Segmentgrössen zurückgreifen. Die Erfindung ermöglicht es auch, in unterschiedlichen
Gasturbinen dieselben Brenner 14, 15 und ersten Auskleidungssegmente
16 zu verwenden. Angepasst an unterschiedliche Turbineneinlassgeometrien
wird dann nur der Brennkammeraustritt 33 mit den zweiten Auskleidungssegmenten
17 und deren Segmentträgern 18, 21.The division of the lining segments according to the invention makes it possible to
to realize larger combustion chambers without having correspondingly large ones
Segments must be constructed. This way you can look at already proven ones
Use segment sizes. The invention also makes it possible in different
Gas turbines have the
Die Konfiguration der Auskleidungssegmente 16, 17 ist so wie bei den EV- und
SEV-Brennkammern der bekannten Gasturbinen der Anmelderin vom Typ GT24B
und GT26B (siehe dazu den Artikel von D. K. Mukherjee "State-of-the-art gas turbines
- a brief update", ABB review 2/1997, S. 4-14 (1997)). Eine Besonderheit ist
das Vorsehen von Verbindungskanälen 22, 23 (Fig. 1 und Fig. 2) zwischen den
zweiten Auskleidungssegmenten 17 und den ersten Auskleidungssegmenten 16.
Durch diese Verbindungskanäle 22, 23 kann die für die konvektive Kühlung der
Auskleidungssegmente 16, 17 verwendete Kühlluft von den zweiten Auskleidungssegmenten
17 in die ersten Auskleidungssegmente 16 strömen und dort zur
Kühlung beitragen. Das Kühlsystem der zweiten Auskleidungssegmente 17 wird
nur mit einem Teil des gesamten Kühlmassenstromes betrieben, um die Strömungsgeschwindigkeiten
zur Vermeidung von Druckabfällen in den Verbindungskanälen
22, 23 klein zu halten. Für die Kühlung der ersten Auskleidungssegmente
16 wird ein zusätzlichert Teilstrom 25 benötigt (Fig. 2). Der Uebergangsbereich
zwischen den inneren zweiten und ersten Auskleidungssegmenten 17 und 16 ist in
Fig. 2 vergrössert dargestellt.The configuration of the
Es ist aber auch denkbar, auf die Verbindungskanäle 22, 23 zu verzichten und die
Kühlungssysteme der ersten und zweiten Auskleidungssegmente 16,17 getrennt
auszubilden. Die Kühlluft aus den zweiten Auskleidungssegmenten 17 wird dann
in den Heissgasstrom ausgelassen. Die zweiten Auskleidungssegmente 17 sind
dabei deutlich kürzer und sind für einen minimalen Kühlluftverbrauch optimiert.
Der Vorteil der getrennten Kühlung liegt darin, dass auf die herstellungstechnisch
aufwendigen Verbindungskanäle 22, 23 verzichtet werden kann, und dass Luft zur
Beeinflussung der Heissgas-Temperaturverteilung und zur Kühlung des Spaltes
zwischen Brennkammer und Turbine zur Verfügung steht. Erkauft wird dieser
Vorteil durch einen reduzierten Luftmassenfluss im Brenner und eine geringe
Höhe der Kühlkanäle in den zweiten Auskleidungssegmenten 17. But it is also conceivable to dispense with the connecting
- 1010
- Gasturbinegas turbine
- 1111
- äusseres Turbinengehäuseouter turbine housing
- 1212
- Plenumplenum
- 13,2613.26
- Brennkammer (ringförmig)Combustion chamber (ring-shaped)
- 14,15,2714,15,27
- Brennerburner
- 16,1716.17
- Auskleidungssegmentliner segment
- 18,..,2118, .., 21
- Segmentträgersegment carrier
- 22,2322.23
- Verbindungskanalconnecting channel
- 2424
- Zwischenraumgap
- 2525
- Teilstrompartial flow
- 2828
- Auskleidungssegmentliner segment
- 2929
- Brennkammerwandcombustion chamber wall
- 30,3230.32
- Primärzoneprimary zone
- 31,3331.33
- Brennkammeraustrittcombustor exit
Claims (10)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10233805 | 2002-07-25 | ||
DE10233805A DE10233805B4 (en) | 2002-07-25 | 2002-07-25 | Annular combustion chamber for a gas turbine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1384950A2 true EP1384950A2 (en) | 2004-01-28 |
EP1384950A3 EP1384950A3 (en) | 2007-04-04 |
EP1384950B1 EP1384950B1 (en) | 2012-10-17 |
Family
ID=29796562
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03405504A Expired - Lifetime EP1384950B1 (en) | 2002-07-25 | 2003-07-07 | Annular combustion chamber for a gas turbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US7350360B2 (en) |
EP (1) | EP1384950B1 (en) |
DE (1) | DE10233805B4 (en) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2282124A1 (en) * | 2009-08-03 | 2011-02-09 | Alstom Technology Ltd | Method for retrofitting a combustion chamber of a gas turbine |
US9255484B2 (en) * | 2011-03-16 | 2016-02-09 | General Electric Company | Aft frame and method for cooling aft frame |
US9612017B2 (en) | 2014-06-05 | 2017-04-04 | Rolls-Royce North American Technologies, Inc. | Combustor with tiled liner |
US10465907B2 (en) | 2015-09-09 | 2019-11-05 | General Electric Company | System and method having annular flow path architecture |
US10598380B2 (en) | 2017-09-21 | 2020-03-24 | General Electric Company | Canted combustor for gas turbine engine |
US11047575B2 (en) | 2019-04-15 | 2021-06-29 | Raytheon Technologies Corporation | Combustor heat shield panel |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4446693A (en) | 1980-11-08 | 1984-05-08 | Rolls-Royce Limited | Wall structure for a combustion chamber |
EP0321809A1 (en) | 1987-12-21 | 1989-06-28 | BBC Brown Boveri AG | Process for combustion of liquid fuel in a burner |
US5363643A (en) | 1993-02-08 | 1994-11-15 | General Electric Company | Segmented combustor |
EP1363075A2 (en) | 2002-05-16 | 2003-11-19 | United Technologies Corporation | Heat shield panels for use in a combustor for a gas turbine engine |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CH257279A (en) | 1946-01-14 | 1948-09-30 | Hunziker Reinhold | Catching device for small animals such as mice. |
CH428324A (en) * | 1964-05-21 | 1967-01-15 | Prvni Brnenska Strojirna | Combustion chamber |
US4567730A (en) * | 1983-10-03 | 1986-02-04 | General Electric Company | Shielded combustor |
US4628694A (en) * | 1983-12-19 | 1986-12-16 | General Electric Company | Fabricated liner article and method |
US5435127A (en) * | 1993-11-15 | 1995-07-25 | General Electric Company | Method and apparatus for boosting ram airflow to an ejection nozzle |
GB2298267B (en) * | 1995-02-23 | 1999-01-13 | Rolls Royce Plc | An arrangement of heat resistant tiles for a gas turbine engine combustor |
US6301877B1 (en) * | 1995-11-13 | 2001-10-16 | United Technologies Corporation | Ejector extension cooling for exhaust nozzle |
DE59706065D1 (en) * | 1996-09-26 | 2002-02-21 | Siemens Ag | HEAT SHIELD COMPONENT WITH COOL FLUID RETURN AND HEAT SHIELD ARRANGEMENT FOR A HOT GAS CONTAINING COMPONENT |
DE19727407A1 (en) * | 1997-06-27 | 1999-01-07 | Siemens Ag | Gas-turbine combustion chamber heat shield with cooling arrangement |
US6606861B2 (en) * | 2001-02-26 | 2003-08-19 | United Technologies Corporation | Low emissions combustor for a gas turbine engine |
-
2002
- 2002-07-25 DE DE10233805A patent/DE10233805B4/en not_active Expired - Fee Related
-
2003
- 2003-07-07 EP EP03405504A patent/EP1384950B1/en not_active Expired - Lifetime
- 2003-07-23 US US10/625,467 patent/US7350360B2/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4446693A (en) | 1980-11-08 | 1984-05-08 | Rolls-Royce Limited | Wall structure for a combustion chamber |
EP0321809A1 (en) | 1987-12-21 | 1989-06-28 | BBC Brown Boveri AG | Process for combustion of liquid fuel in a burner |
US5363643A (en) | 1993-02-08 | 1994-11-15 | General Electric Company | Segmented combustor |
EP1363075A2 (en) | 2002-05-16 | 2003-11-19 | United Technologies Corporation | Heat shield panels for use in a combustor for a gas turbine engine |
Non-Patent Citations (1)
Title |
---|
D. K. MUKHERJEE: "State-of-the-art gas turbines - a brief update", ABB REVIEW, vol. 2, 1997, pages 4 - 14 |
Also Published As
Publication number | Publication date |
---|---|
EP1384950A3 (en) | 2007-04-04 |
DE10233805B4 (en) | 2013-08-22 |
US20040154308A1 (en) | 2004-08-12 |
DE10233805A1 (en) | 2004-02-05 |
US7350360B2 (en) | 2008-04-01 |
EP1384950B1 (en) | 2012-10-17 |
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