EP0848210B1 - Combustor with integrated guide vanes - Google Patents
Combustor with integrated guide vanes Download PDFInfo
- Publication number
- EP0848210B1 EP0848210B1 EP97810854A EP97810854A EP0848210B1 EP 0848210 B1 EP0848210 B1 EP 0848210B1 EP 97810854 A EP97810854 A EP 97810854A EP 97810854 A EP97810854 A EP 97810854A EP 0848210 B1 EP0848210 B1 EP 0848210B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling
- guide
- air
- combustion
- gas turbine
- 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 - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
- F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
Definitions
- the invention relates to a gas turbine with between the combustion chamber and turbine impeller arranged after the guide vanes Preamble of claim 1.
- a gas turbine has one between the combustion chamber and the turbine impeller guide vane group forming an independent unit, which are essentially functional and constructive from the neighboring ones Assemblies, such as combustion chamber and turbine impeller, is separated and also separate anchorings in the turbine housing having.
- Assemblies such as combustion chamber and turbine impeller, is separated and also separate anchorings in the turbine housing having.
- This has the disadvantage that each of these assemblies made separately and assembled separately and above all must also be adjusted to each other, which is very expensive caused.
- such a design requires one very large number of components with all the complex disadvantages, of the manufacturing and assembly processes, the transport weight up to in particular thermal operating behavior.
- DE 1 245 644 describes a gas turbine with a monolithic combustion chamber guide vane unit known.
- the combustor vane assembly is in a cold Support structure attached.
- the combustion chamber wall is in the flow direction from Air flows around the compressor to the turbine, which is guided into the guide vanes, and thence through mixed air openings into the hot gas flowing out of the combustion chamber flows.
- Monolithic combustor guide vane units with analog Air ducts around the combustion chamber and through the guide vanes are also from US 3,608,310, DE 11 08 516, DE 14 76 887, DE 14 76 892, US 3,353,351, and DE 12 40 706 became known. Airflow becomes primary according to the teachings disclosed as mixed air to dilute the hot gas flow before entering the turbine impeller used. Cooling problems are not the focus; in particular, the thermally highly stressed power blades are already on the Combustion chamber wall of heated air flows through.
- the present invention is based on the task of having a gas turbine between To specify the guide vanes arranged in the combustion chamber and turbine impeller, which the mentioned disadvantages of the prior art can avoid.
- the solution to this problem is with the characteristics of the license plate circumscribed by claim 1. Details of the embodiments Such a gas turbine are characterized by the characteristics of dependent claims.
- guide vanes 1.1 In a gas turbine with between each combustion chamber 1.2 and the turbine impeller 2 are arranged guide vanes 1.1 this integrated into the combustion chamber wall 1.2.1 according to the invention and formed as parts of the same. You put one in essential monolithic combustion chamber guide vane unit 1 The combustion chamber wall 1.2.1 goes into the wall of each associated one Guide vane 1.1 over, without being separated from it. This combustion chamber guide vane unit 1 is in a so-called cold support structure 3.1 of the gas turbine system used and is carried by this.
- This combustor guide vane unit 1 is a gas turbine system split formed, creating a radially outer and a radially inner segment 1.B or 1.A arises, in each Segment the guide vane halves through corresponding boundary walls 1.1.i are separated from each other, i.e. each Guide vane 1.1 a radially closed to the outside inner and radially outer part, each in a corresponding Segment 1.A or 1.B has.
- Each of these segments sits in an associated cold support structure 3.1 of the gas turbine system. Between each of these cold support structures 3.1 and their assigned segments 1.A and 1.B are cooling air ducts 4 is provided, which partially in the interior of the guide vanes 1.1 run.
- the inflow openings 4.1 are the Cooling air channels 4 in the cold support structure 3.1 in the area the guide vanes 1.1 arranged, whereby a counterflow cooling the combustion chamber wall 1.2.1 is realized.
- To the thermal conditions have to be met in the cooling air ducts 4 of the guide vanes 1.1 guide devices 4.2, e.g. Baffle plates or baffles, intended for the cooling air.
- the dividing the guide vane 1.1 in the radial direction and adjacent boundary walls 1.1.i each thus formed guide vane half of corresponding segments at least one with the adjacent boundary wall 1.1.i corresponding paragraph 1.1.k as a sealing element for reduction of leakage losses.
- segment 1.A or 1.B i.e. with optimal production [casting technology] and the cooling conditions between radially inside or radially are completely outside (0% and 100% of the channel height).
- the dividing the guide vanes 1.1 and adjacent to each other Boundary walls 1.1.i corresponding to each guide vane half Segments can be arranged at any inclination to the rotor axis.
- the cooling air is almost completely again Combustion cycle supplied, passing through the counterflow is already very well preheated.
- the integrated Design can greatly reduce the cooling air loss become.
- the countercurrent Cooling air ensures that the thermal loads are very high
- the fresh and colder cooling air is guided by guide vanes preserved, thus be cooled better.
- the Length of the combustion chamber with integrated guide vane by approx the axial extent of the first row of guide vanes has been shortened become.
- there is the advantage that the Cooling air for the first row of blades of the first turbine no longer through the guide vane row, but directly from Compressors coming into the row of blades can.
- the cooling air flows essentially in Series connected arise compared to the parallel connection the cooling air flows according to the prior art also significant advantages in terms of cooling efficiency.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Die Erfindung betrifft eine Gasturbine mit zwischen Brennraum und Turbinenlaufrad angeordneten Leitschaufeln nach dem Oberbegriff des Anspruchs 1.The invention relates to a gas turbine with between the combustion chamber and turbine impeller arranged after the guide vanes Preamble of claim 1.
Eine Gasturbine weist zwischen Brennraum und Turbinenlaufrad eine eine eigenständige Einheit bildende Leitschaufelgruppe auf, welche im wesentlichen funktionell und konstruktiv von den benachbarten Baugruppen, wie Brennkammer und Turbinenlaufrad, separiert ist und auch separate Verankerungen im Turbinengehäuse aufweist. Dies hat den Nachteil, dass jede dieser Baugruppen separat hergestellt und separat montiert und vor allem auch zueinander justiert werden muss, was sehr hohe Kosten verursacht. Insbesondere erfordert eine solche Bauweise eine sehr grosse Anzahl der Bauteile mit all den komplexen Nachteilen, von den Fertigungs- und Montagevorgängen, dem Transportgewicht bis zum insbesondere thermischen Betriebsverhalten. A gas turbine has one between the combustion chamber and the turbine impeller guide vane group forming an independent unit, which are essentially functional and constructive from the neighboring ones Assemblies, such as combustion chamber and turbine impeller, is separated and also separate anchorings in the turbine housing having. This has the disadvantage that each of these assemblies made separately and assembled separately and above all must also be adjusted to each other, which is very expensive caused. In particular, such a design requires one very large number of components with all the complex disadvantages, of the manufacturing and assembly processes, the transport weight up to in particular thermal operating behavior.
Aus DE 1 245 644 ist eine Gasturbine mit einer monolithischen Brennkammer-Leitschaufeleinheit bekannt. Die Brennkammer-Leitschaufeleinheit ist in einer kalten Tragstruktur befestigt. Die Brennkammerwand wird in Strömungsrichtung vom Verdichter zur Turbine von Luft umströmt, welche in die Leitschaufeln geführt wird, und von dort durch Mischluftöffnungen in das aus der Brennkammer abströmende Heissgas einströmt. Monolithische Brennkammer-Leitschaufeleinheiten mit analogen Luftführungen um die Brennkammer und durch die Leitschaufeln sind auch aus US 3,608,310, DE 11 08 516, DE 14 76 887, DE 14 76 892, US 3,353,351, sowie DE 12 40 706 bekanntgeworden. Die Luftströmung wird gemäss den offenbarten Lehren primär als Mischluft zur Verdünnung der Heissgasströmung vor dem Eintritt in das Turbinen-Laufrad genutzt. Probleme der Kühlung stehen dabei nicht im Vordergrund; insbesondere werden die thermisch hochbelasteten Leistschaufeln von bereits an der Brennkammerwand erwärmter Luft durchströmt. DE 1 245 644 describes a gas turbine with a monolithic combustion chamber guide vane unit known. The combustor vane assembly is in a cold Support structure attached. The combustion chamber wall is in the flow direction from Air flows around the compressor to the turbine, which is guided into the guide vanes, and thence through mixed air openings into the hot gas flowing out of the combustion chamber flows. Monolithic combustor guide vane units with analog Air ducts around the combustion chamber and through the guide vanes are also from US 3,608,310, DE 11 08 516, DE 14 76 887, DE 14 76 892, US 3,353,351, and DE 12 40 706 became known. Airflow becomes primary according to the teachings disclosed as mixed air to dilute the hot gas flow before entering the turbine impeller used. Cooling problems are not the focus; in particular, the thermally highly stressed power blades are already on the Combustion chamber wall of heated air flows through.
Der vorliegenden Erfindung liegt die Aufgabe zugrunde, eine Gasturbine mit zwischen Brennraum und Turbinenlaufrad angeordneten Leitschaufeln anzugeben, welche die genannten Nachteile des Standes der Technik zu vermeiden vermag. Die Lösung dieser Aufgabe wird mit den Merkmalen des Kennzeichens von Anspruch 1 umschrieben. Details der Ausführungsformen einer solchen Gasturbine sind durch die Merkmale der abhängigen Ansprüche angegeben.The present invention is based on the task of having a gas turbine between To specify the guide vanes arranged in the combustion chamber and turbine impeller, which the mentioned disadvantages of the prior art can avoid. The solution to this problem is with the characteristics of the license plate circumscribed by claim 1. Details of the embodiments Such a gas turbine are characterized by the characteristics of dependent claims.
Weitere Merkmale und Vorteile ergeben sich aus der Beschreibung von beispielsweisen Ausführungsformen anhand der Zeichnung.In dieser zeigt
- Fig. 1
- schematisch eine Leitschaufelanordnung nach dem Stand der Technik
- Fig. 2
- einen im wesentlichen Radialschnitt durch eine erfindungsgemässe Leitschaufelanordnung [Schnitt AA],
- Fig. 3
- den Schnitt BB durch zwei benachbarte Leitschaufeln einer Leitschaufelgruppe.
- Fig. 1
- schematically a guide vane arrangement according to the prior art
- Fig. 2
- an essentially radial section through an inventive guide vane arrangement [section AA],
- Fig. 3
- the section BB through two adjacent guide vanes of a guide vane group.
Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt; insbesondere ist nicht der an sich bekannte und unveränderte Teil der Gasturbine dargestellt.It is only essential for understanding the invention Elements shown; in particular, it is not the one known per se and unchanged part of the gas turbine shown.
Bei einer Gasturbine mit zwischen jeder Brennkammer 1.2 und
dem Turbinenlaufrad 2 angeordneten Leitschaufeln 1.1 sind
diese erfindugsgemäss in die Brennkammerwand 1.2.1 integriert
und als Teile derselben ausgebildet. Sie stellen eine im
wesentlichen monolithische Brennkammer-Leitschaufeleinheit 1
dar. Die Brennkammerwand 1.2.1 geht in die Wand jeder zugehörigen
Leitschaufel 1.1 über, ohne von ihr getrennt zu sein.
Diese Brennkammer-Leitschaufeleinheit 1 ist in eine sogenannte
kalte Tragstruktur 3.1 der Gasturbinenanlage eingesetzt und
wird von dieser getragen. Aus Gründen der Montage der ganzen
Gasturbinenanlage ist diese Brennkammer-Leitschaufeleinheit 1
geteilt ausgebildet, wodurch ein radial äusseres und ein
radial inneres Segment 1.B bzw. 1.A entsteht, wobei in jedem
Segment die Leitschaufelhälften durch korrespondierende Begrenzungswände
1.1.i voneinander getrennt sind, also jede
Leitschaufel 1.1 einen nach aussen abgeschlossenen radial
inneren und radial äusseren Teil, je in einem entsprechenden
Segment 1.A bzw. 1.B, aufweist. Jedes dieser Segmente sitzt in
einer zugeordneten kalten Tragstruktur 3.1 der Gasturbinenanlage.
Zwischen jeder dieser kalten Tragstrukturen 3.1 und
dem ihr zugeordneten Segment 1.A bzw. 1.B sind Kühlluftkanäle
4 vorgesehen, welche teilweise im Innern der Leitschaufeln 1.1
verlaufen. Dabei sind die Einströmöffnungen 4.1 der
Kuehlluftkanäle 4 in der kalten Tragstruktur 3.1 im Bereich
der Leitschaufeln 1.1 angeordnet, wodurch eine Gegenstromkühlung
der Brennkammerwand 1.2.1 verwirklicht wird. Um den
thermischen Gegebenheiten gerecht zu werden sind in den Kühlluftkanälen
4 der Leitschaufeln 1.1 Leiteinrichtungen 4.2,
z.B. Prallbleche oder Leitbleche, für die Kühlluft vorgesehen.
Die die Leitschaufel 1.1 in radialer Richtung teilenden
und einander benachbarten Begrenzungswände 1.1.i einer jeden
so gebildeten Leitschaufelhälfte ensprechender Segmente kann
wenigstens einen mit der benachbarten Begrenzungswand 1.1.i
korrespondierenden Absatz 1.1.k als Dichtelement zur Verringerung
von Leckageverlusten aufweisen. Ausserdem weist jede der
Leitschaufeln 1.1 an ihren Mantelseiten Kühlluftöffnungen
1.1.m auf, wobei diese vorzugsweise und je nach den thermischen
Gegebenheiten, laufradseitig [Hinterkante] oder im Bereich
der die Leitschaufel 1.1 in zwei radiale Segmente teilenden
Begrenzungswände 1.1.i angeordnet sind. Dabei sind
diese Kühlluftöffnungen 1.1.m in den Begrenzungswänden 1.1.i
von innerem Segment 1.A zu äusserem Segment 1.B zueinander
versetzt angeordnet.In a gas turbine with between each combustion chamber 1.2 and
the turbine impeller 2 are arranged guide vanes 1.1
this integrated into the combustion chamber wall 1.2.1 according to the invention
and formed as parts of the same. You put one in
essential monolithic combustion chamber guide vane unit 1
The combustion chamber wall 1.2.1 goes into the wall of each associated one
Guide vane 1.1 over, without being separated from it.
This combustion chamber guide vane unit 1 is in a so-called
cold support structure 3.1 of the gas turbine system used and
is carried by this. For the sake of assembling the whole
This combustor guide vane unit 1 is a gas turbine system
split formed, creating a radially outer and a
radially inner segment 1.B or 1.A arises, in each
Segment the guide vane halves through corresponding boundary walls
1.1.i are separated from each other, i.e. each
Guide vane 1.1 a radially closed to the outside
inner and radially outer part, each in a corresponding
Segment 1.A or 1.B has. Each of these segments sits in
an associated cold support structure 3.1 of the gas turbine system.
Between each of these cold support structures 3.1 and
their assigned segments 1.A and 1.B are
Die Höhe der Teilung in das radial innere und das radial äussere Segment 1.A bzw. 1.B kann je nach speziellen Anlagegegebenheiten, d.h. bei optimaler Fertigung [Giesstechnik] und den Kühlverhältnissen zwischen radial ganz innen oder radial ganz aussen (0% und 100% der Kanalhöhe) liegen.The height of the division into the radially inner and the radially outer Depending on the specific investment situation, segment 1.A or 1.B i.e. with optimal production [casting technology] and the cooling conditions between radially inside or radially are completely outside (0% and 100% of the channel height).
Die die Leitschaufeln 1.1 teilenden und einander benachbarten Begrenzungswände 1.1.i jeder Leitschaufelhälfte entsprechender Segmente kann zur Rotorachse beliebig geneigt angeordnet sein.The dividing the guide vanes 1.1 and adjacent to each other Boundary walls 1.1.i corresponding to each guide vane half Segments can be arranged at any inclination to the rotor axis.
Mit dieser integrierten Ausbildung der Leitschaufeln stellen sie eine Fortsetzung der Brennkammer dar mit der zusätzlichen Aufgabe, die Gasströmung zu den Laufschaufeln des Turbinenrades umzulenken. Damit kann die im allgemeinen sehr komplex strukturierte, separat aufgebaute und separat zu montierende Leitschaufelreihe entfallen. Dies bewirkt auch, dass Kühlluftverluste [Leckage] durch die montagebedingten Spalte reduziert bzw. eliminiert werden.With this integrated formation of the guide vanes they are a continuation of the combustion chamber with the additional one Task, the gas flow to the blades of the turbine wheel redirect. This can be very complex in general structured, separately constructed and to be assembled separately Guide vane row not required. This also causes loss of cooling air [Leakage] reduced by the assembly-related column or eliminated.
Ausserdem wird die Kühlluft wieder fast vollständig dem Verbrennungskreislauf zugeführt, wobei sie durch die Gegenstromführung schon sehr gut vorgewärmt ist. Durch die integrierte Bauweise können die Kühlluftverluste sehr stark reduziert werden. Ausserdem wird durch die Gegenstromführung der Külluft sichergestellt, dass die thermisch sehr hoch belasteten Leitschaufeln die frische und damit kältere Kühlluft erhalten, somit besser gekühlt werden. Ausserdem kann die Länge der Brennkammer mit integrierter Leitschaufel um etwa die axiale Erstreckung der ersten Leitschaufelreihe gekürzt werden. Ausserdem ergibt sich dadurch der Vorteil, dass die Külluft für die erste Laufschaufelreihe der ersten Turbine nicht mehr durch die Leitschaufelreihe, sondern direkt vom Verdichter kommend der Laufschaufelreihe zugeführt werden kann. Dies ergibt somit eine deutliche Verkürzung des Kühlluftweges und somit eine Verringerung der Strömungsverluste und der zu kühlenden Oberfläche; auch eine einfachere konstruktive Ausbildung der entsprechenden Anlageteile. Durch die Teilung in die beiden Segmente der Brennkammer-Leitschaufeleinheit 1 lässt sich zudem der Vorteil verwirklichen, dass die Kühllufterwärmung zwischen den radial äusseren und den radial inneren Segmenten etwa gleichmässig verteilt wird.In addition, the cooling air is almost completely again Combustion cycle supplied, passing through the counterflow is already very well preheated. Through the integrated Design can greatly reduce the cooling air loss become. In addition, the countercurrent Cooling air ensures that the thermal loads are very high The fresh and colder cooling air is guided by guide vanes preserved, thus be cooled better. In addition, the Length of the combustion chamber with integrated guide vane by approx the axial extent of the first row of guide vanes has been shortened become. In addition, there is the advantage that the Cooling air for the first row of blades of the first turbine no longer through the guide vane row, but directly from Compressors coming into the row of blades can. This results in a significant shortening of the cooling air path and thus a reduction in flow losses and the surface to be cooled; also a simpler constructive Training of the corresponding system parts. Through the Division into the two segments of the combustion chamber guide vane unit 1 can also realize the advantage that the cooling air heating between the radially outer and the radially inner segments is distributed approximately evenly.
Da die Kühlluftströme erfindungsgemäss im wesentlichen in Serie geschaltet sind, ergeben sich gegenüber der Parallelschaltung der Kühlluftströme nach dem Stand der Technik auch wesentliche Vorteile betreffend dem Wirkungsgrad der Kühlung. Ausserdem entfallen bei der integrierten Leitschaufelausbildung die Leckageverluste an Kühlluft durch die Spalten in der Umgebung der separat gefertigten und eingesetzten Leitschaufeln. According to the invention, the cooling air flows essentially in Series connected, arise compared to the parallel connection the cooling air flows according to the prior art also significant advantages in terms of cooling efficiency. In addition, there is no need for integrated guide vane training the leakage of cooling air through the gaps in the Surroundings of the separately manufactured and used guide vanes.
Claims (10)
- Gas turbine, comprising at least one cold supporting structure (3.1), a combustion chamber (1.2) defined by combustion-chamber walls (1.2.1), and guide blades (1.1), the guide blades (1.1) being integrated in a combustion-chamber wall (1.2.1) and being designed as parts of the same in such a way that they constitute an essentially monolithic combustion-chamber/guide-blade unit (1) which is fastened in the cold supporting structure (3.1), the combustion-chamber/guide-blade unit having at least one cooling-air passage (4) and/or forming at least one cooling-air passage (4) with the supporting structure, which cooling passage has at least one inflow opening (4.1), characterized in that the cooling-air passage has at least one first passage section running at least partly inside a guide blade and a second passage section which is arranged downstream of the first passage section in the direction of flow and runs on one side of the combustion-chamber wall (1.2.1), so that the cooling air is directed first through the guide blade and then in counterflow along the combustion-chamber wall.
- Gas turbine according to Claim 1, characterized in that the inflow openings (4.1) are integrated in the cold supporting structure (3.1).
- Gas turbine according to one of the preceding claims, characterized in that the guide blades (1.1) have guide devices (4.2) for the cooling air inside the cooling-air passages (4).
- Gas turbine according to one of the preceding claims, characterized in that the guide blades (1.1) have cooling-air openings (1.1.m) on their shell surfaces.
- Gas turbine according to Claim 4, characterized in that the cooling-air openings (1.1.m) are arranged on the trailing edges of the guide blades (1.1).
- Gas turbine according to one of the preceding claims, characterized in that the combustion-chamber/guide-blade unit (1) is split into a radially inner segment (1.A) and a radially outer segment (1.B), the guide blades being split by boundary walls (1.1.i) into outer and inner segments.
- Gas turbine according to Claim 6, characterized in that the boundary walls (1.1.i) have cooling-air openings.
- Gas turbine according to Claim 7, characterized in that the cooling-air openings (1.1.m) in the boundary walls (1.1.i) of inner segment (1.A) and outer segment (1.B) are staggered.
- Method of cooling a monolithic combustion-chamber/guide-blade unit of a gas turbine according to one of the preceding claims, characterized in that a cooling-air flow is directed through cooling-air openings (4.1) into a first passage section, running at least partly inside the guide blade, of a cooling-air passage (4), and in that at least one partial flow of the cooling-air flow is subsequently directed into a second passage section for counterflow cooling of the combustion chamber (1.2) along the combustion-chamber wall (1.2.1).
- Method according to Claim 9, characterized in that a first partial flow of the cooling-air flow flows off from the cooling-air passage (4) through cooling-air openings (1.1.m) of the guide blade (1.1.i), and a second partial flow is directed into the second passage section.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19651881A DE19651881A1 (en) | 1996-12-13 | 1996-12-13 | Combustion chamber with integrated guide vanes |
| DE19651881 | 1996-12-13 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP0848210A2 EP0848210A2 (en) | 1998-06-17 |
| EP0848210A3 EP0848210A3 (en) | 1999-11-17 |
| EP0848210B1 true EP0848210B1 (en) | 2003-04-16 |
Family
ID=7814598
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP97810854A Expired - Lifetime EP0848210B1 (en) | 1996-12-13 | 1997-11-11 | Combustor with integrated guide vanes |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US5953919A (en) |
| EP (1) | EP0848210B1 (en) |
| JP (1) | JPH10184387A (en) |
| CN (1) | CN1130522C (en) |
| CA (1) | CA2219421C (en) |
| DE (2) | DE19651881A1 (en) |
| TW (1) | TW374821B (en) |
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| US7930891B1 (en) | 2007-05-10 | 2011-04-26 | Florida Turbine Technologies, Inc. | Transition duct with integral guide vanes |
| DE602007007333D1 (en) * | 2007-09-24 | 2010-08-05 | Alstom Technology Ltd | Gasket in gas turbine |
| US8276389B2 (en) * | 2008-09-29 | 2012-10-02 | Siemens Energy, Inc. | Assembly for directing combustion gas |
| US8230688B2 (en) * | 2008-09-29 | 2012-07-31 | Siemens Energy, Inc. | Modular transvane assembly |
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| WO2011024242A1 (en) * | 2009-08-24 | 2011-03-03 | 三菱重工業株式会社 | Split ring cooling structure and gas turbine |
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| EP2613080A1 (en) * | 2012-01-05 | 2013-07-10 | Siemens Aktiengesellschaft | Combustion chamber of an annular combustor for a gas turbine |
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| US10024180B2 (en) * | 2014-11-20 | 2018-07-17 | Siemens Energy, Inc. | Transition duct arrangement in a gas turbine engine |
| US20170370583A1 (en) * | 2016-06-22 | 2017-12-28 | General Electric Company | Ceramic Matrix Composite Component for a Gas Turbine Engine |
| US11067277B2 (en) * | 2016-10-07 | 2021-07-20 | General Electric Company | Component assembly for a gas turbine engine |
| US10816199B2 (en) * | 2017-01-27 | 2020-10-27 | General Electric Company | Combustor heat shield and attachment features |
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| CN112484072B (en) * | 2020-11-24 | 2022-06-17 | 湖南省农友机械集团有限公司 | Hot-blast furnace hot blast heater and air inlet device thereof |
| US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
| CN112855617B (en) * | 2021-01-27 | 2022-07-08 | 山东亚通科技集团有限公司 | Fan blower |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2477683A (en) * | 1942-09-30 | 1949-08-02 | Turbo Engineering Corp | Compressed air and combustion gas flow in turbine power plant |
| US2630679A (en) * | 1947-02-27 | 1953-03-10 | Rateau Soc | Combustion chambers for gas turbines with diverse combustion and diluent air paths |
| FR1104644A (en) * | 1954-02-15 | 1955-11-22 | Thomson Houston Comp Francaise | Improvements to Fluid Flow Control Systems |
| US3088281A (en) * | 1956-04-03 | 1963-05-07 | Bristol Siddeley Engines Ltd | Combustion chambers for use with swirling combustion supporting medium |
| US3316714A (en) * | 1963-06-20 | 1967-05-02 | Rolls Royce | Gas turbine engine combustion equipment |
| GB1048968A (en) * | 1964-05-08 | 1966-11-23 | Rolls Royce | Combustion chamber for a gas turbine engine |
| GB1034260A (en) * | 1964-12-02 | 1966-06-29 | Rolls Royce | Aerofoil-shaped blade for use in a fluid flow machine |
| US3608310A (en) * | 1966-06-27 | 1971-09-28 | Gen Motors Corp | Turbine stator-combustor structure |
| GB2189553B (en) * | 1986-04-25 | 1990-05-23 | Rolls Royce | Cooled vane |
| US5239818A (en) * | 1992-03-30 | 1993-08-31 | General Electric Company | Dilution pole combustor and method |
-
1996
- 1996-12-13 DE DE19651881A patent/DE19651881A1/en not_active Withdrawn
-
1997
- 1997-10-24 CA CA002219421A patent/CA2219421C/en not_active Expired - Fee Related
- 1997-10-28 TW TW086115971A patent/TW374821B/en not_active IP Right Cessation
- 1997-11-10 US US08/966,865 patent/US5953919A/en not_active Expired - Fee Related
- 1997-11-11 EP EP97810854A patent/EP0848210B1/en not_active Expired - Lifetime
- 1997-11-11 DE DE59709849T patent/DE59709849D1/en not_active Expired - Fee Related
- 1997-12-12 CN CN97125541A patent/CN1130522C/en not_active Expired - Fee Related
- 1997-12-12 JP JP9343237A patent/JPH10184387A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| EP0848210A2 (en) | 1998-06-17 |
| DE59709849D1 (en) | 2003-05-22 |
| CN1130522C (en) | 2003-12-10 |
| CA2219421C (en) | 2007-04-24 |
| CA2219421A1 (en) | 1998-06-13 |
| US5953919A (en) | 1999-09-21 |
| TW374821B (en) | 1999-11-21 |
| EP0848210A3 (en) | 1999-11-17 |
| DE19651881A1 (en) | 1998-06-18 |
| JPH10184387A (en) | 1998-07-14 |
| CN1188210A (en) | 1998-07-22 |
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