EP1422479B1 - Chamber for the combustion of a fluid combustible mixture - Google Patents

Chamber for the combustion of a fluid combustible mixture Download PDF

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Publication number
EP1422479B1
EP1422479B1 EP02026101A EP02026101A EP1422479B1 EP 1422479 B1 EP1422479 B1 EP 1422479B1 EP 02026101 A EP02026101 A EP 02026101A EP 02026101 A EP02026101 A EP 02026101A EP 1422479 B1 EP1422479 B1 EP 1422479B1
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EP
European Patent Office
Prior art keywords
combustion chamber
liner
rail
coolant
elements
Prior art date
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EP02026101A
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German (de)
French (fr)
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EP1422479A1 (en
Inventor
Peter Tiemann
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Siemens AG
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Siemens AG
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Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to ES02026101T priority Critical patent/ES2307702T3/en
Priority to EP02026101A priority patent/EP1422479B1/en
Priority to DE50212643T priority patent/DE50212643D1/en
Priority to US10/672,506 priority patent/US7322196B2/en
Priority to CNB2003101156358A priority patent/CN100370177C/en
Priority to JP2003387648A priority patent/JP2004177108A/en
Publication of EP1422479A1 publication Critical patent/EP1422479A1/en
Application granted granted Critical
Publication of EP1422479B1 publication Critical patent/EP1422479B1/en
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    • 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/04—Supports for linings

Definitions

  • the present invention relates to a combustion chamber for combustion of a combustible fluid mixture with a burner arranged on the combustion chamber.
  • the invention further relates to a method for cooling a combustion chamber according to the invention.
  • Combustion chambers in particular for gas turbines, are generally provided in their interior with a flow guide body, which is referred to as a liner.
  • a flow guide body which is referred to as a liner.
  • combustion chamber arrangements are used which are composed of a plurality of individual combustion chambers, which open into a common opening.
  • the opening is preferably formed as an annular opening, which also represents the transition to the turbine room.
  • a burner which is provided in the combustion chamber, supplies a combustible fluid mixture, which ignites in the combustion chamber and is conducted through the liner in the direction of the outlet opening.
  • Another concept of a combustor assembly provides a single annular annular combustor instead of a plurality of individual combustors. In such an annular combustion chamber burned ignited combustible fluid mixture enters, burns therein and expands in the direction of the outlet opening.
  • a lining for an inner wall of an industrial furnace which comprises the oven wall upstream of the furnace interior ceramic fiber insulating molded parts. Between the ceramic fiber insulating molded parts and the furnace wall resilient elastomeric fiber mats are arranged. Between adjacent, spaced apart juxtaposed mold parts in each case a T-shaped profiled strip with a strip web and a strip flange is arranged. The strip web engages between the mold parts while the strip flange abuts the inside of the strip in a tight manner. Cooling of the bar or the molded parts by means of cooling fluid is not described.
  • a generic combustion chamber with an on the Combustor arranged burner, a combustion chamber arranged in the liner and an outlet opening proposed, wherein the liner has liner elements which are elastically fixed by means of rail elements on a combustion chamber housing, wherein the rail elements are arranged combustion chamber side and protrude between two adjacently arranged liner elements to the outside.
  • the rail element and the liner elements have coolant channels, which are fluidically connected with each other.
  • the liner element can be fixed by means of a fastening element provided on the outside of the rail element.
  • standard fastening means can thus be used to fix the liner elements to the rail elements. Costs and assembly costs can be reduced.
  • the fastening element is formed by a screw.
  • a releasable connection can be achieved, which can be carried out by means of conventional, known tools. Special tools to perform the attachment can be avoided.
  • the fastening element is formed by a clamping element, in particular a clamping spring.
  • a clamping spring With the use of clamping springs, a particularly simple and fast assembly or disassembly of liner elements can be achieved. This has an advantageous effect in particular when the service life of a system, such as a gas turbine, represents a significant cost factor. Low lifetimes can be achieved.
  • the rail element has a coating at least on the combustion chamber side.
  • the coating can lead both to reducing the physical stress during normal operation and to reducing wear. Maintenance intervals can be extended.
  • a coating may also be provided to form, for example, an inert surface with respect to the fluid in the combustion chamber.
  • the rail element can also be provided with a coating on its entire surface in order to simplify, for example, a coating process.
  • the rail element has liner-like toes for establishing a fluidic connection between a channel of the rail element and a channel of the liner element for a coolant. It can be advantageously achieved a cooling system, which also allows cooling of the liner elements and the rail elements.
  • the combustion chamber has a closed cooling.
  • the coolant can be supplied to the combustion chamber, wherein it feeds its energy absorbed in the context of the cooling function back to the process.
  • energy loss due to the cooling function can be reduced and on the other hand, the coolant can be used for combustion in the combustion chamber. A high efficiency can be achieved.
  • the combustion chamber is arranged in a turbomachine, in particular a gas turbine. Maintenance costs and service life of a gas turbine can be further reduced.
  • the invention further proposes a method for cooling a combustion chamber according to the invention, wherein a coolant flowing through the liner rail flows at least partially in the circumferential direction of the combustion chamber in the direction of the liner element and is deflected in or against the flow direction of the combustion chamber in a channel of the liner element.
  • a channel provided in a liner element which is provided, for example, for cooling the liner element, can be used for discharging the coolant flowing through the liner rail.
  • a closed cooling system for a combustion chamber so the design effort for the flow guidance of the coolant can be reduced.
  • components and assembly costs can be reduced if, for example, a separatedefluidab Entry can be saved.
  • air is used as the coolant.
  • the proportion of the air used for cooling fed back to the combustion chamber so that on the one hand, the heat absorbed by the cooling function and the energy for providing the cooling air can be at least partially recycled to the process. A further increase in the efficiency can be achieved.
  • Fig. 1 shows a section of a gas turbine with a combustion chamber 1 according to the invention, which is designed in the present case as an annular combustion chamber.
  • the combustion chamber 1 has a Housing 7, in which a liner 4 is arranged. At one end of the liner 4 opens a burner 2, via which a combustible fluid is supplied. At the opposite end of the liner, an outlet opening 3 is provided, which is connected to an inlet to a flow channel of a downstream gas turbine, which is not shown. In the middle, a rotor shaft 14 is arranged.
  • Fig. 2 the upper part of the combustion chamber 1 is shown enlarged in section. The combustible fluid supplied via the burner 2 is ignited in a combustion space 15 in the liner 4 and flows in the direction of the outlet opening 3 to the downstream turbine.
  • the liner 4 is constructed in a segment-like manner from liner elements 5, which are each connected adjacent to one another via rail elements 6 ( Fig. 3 ). Via the rail elements 6, the liner elements 5 are at the same time fixed elastically to the combustion chamber housing 7 of the combustion chamber 1. According to the invention, the rail elements 6 are arranged on the combustion chamber side and protrude between two adjacently arranged liner elements 5 to the outside. For attachment, the rail element 6 has openings 17 through which a fastening device 8 can be inserted, via which the rail element 6 is fixed elastically to the housing 7 of the combustion chamber 1. To compensate occurring expansions, the fastening devices 8 are formed elastically in their longitudinal extent. For sealing between the rail element 6 and the liner element 5, a sealing element 16 is provided in each case.
  • the rail element 6 is hot gas side between the two adjacent liners 5 on outer Linerverhakungen not shown on and clamps the liner elements 5 firmly.
  • the rail element 6 also has alternately over its longitudinal extent alternately staggered mounting areas and cooling areas.
  • openings 11 are provided in the rail element, via the one Coolant from the rail member 6 via a provided in an edge region of the liner member 5 channel 20 into the channel 13 of the liner member 5 flows.
  • the rail element 6 is provided with a coating 9, which causes thermal insulation in relation to the hot gas flow within the combustion chamber 1.
  • the coating 9 forms a protection by which the aging of the rail element 6 is reduced.
  • the rail element 6 has liner-like toes, in which the liner elements 5 are fastened to the housing 7 of the combustion chamber 1.
  • the coolant flow is removed in the circumferential direction in the liner elements 5.
  • the area to be cooled is thereby divided into fastening regions 19, which are flowed through in the circumferential direction, and into cooling regions 18, which are flowed through axially.
  • air is used as the coolant, which is taken behind an intake compressor of the gas turbine, not shown, and the cooling system of the gas turbine is supplied.
  • the gas turbine has a combustion chamber with a closed cooling system, so that the air taken from the process for cooling purposes in the combustion chamber can be fed back. The heat energy absorbed by the cooling function is thus returned to the process.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die vorliegende Erfindung betrifft eine Brennkammer zur Verbrennung eines brennbaren Fluidgemisches mit einem an der Brennkammer angeordneten Brenner. Die Erfindung betrifft ferner ein Verfahren zur Kühlung einer erfindungsgemäßen Brennkammer.The present invention relates to a combustion chamber for combustion of a combustible fluid mixture with a burner arranged on the combustion chamber. The invention further relates to a method for cooling a combustion chamber according to the invention.

Brennkammern, insbesondere für Gasturbinen, sind in der Regel in ihrem Inneren mit einem Strömungsführungskörper versehen, der als Liner bezeichnet wird. Grundsätzlich sind unterschiedliche Konzepte für Brennkammeranordnungen bekannt. So werden beispielsweise Brennkammeranordnungen verwendet, welche sich aus einer Vielzahl von Einzelbrennkammern zusammensetzen, die in einer gemeinsamen Öffnung münden. Im Falle einer Gasturbine ist die Öffnung vorzugsweise als Ringöffnung ausgebildet, die gleichzeitig den Übergang zum Turbinenraum darstellt. Ein über einen in der Brennkammer vorgesehenen Brenner wird ein brennbares Fluidgemisch zugeführt, welches in der Brennkammer zündet und den Liner durchströmend in Richtung Austrittsöffnung geführt wird. Ein anderes Konzept einer Brennkammeranordnung sieht anstelle einer Vielzahl von Einzelbrennkammern eine einzige ringförmige Ringbrennkammer vor. In eine solche Ringbrennkammer tritt in Brennern gezündetes brennbares Fluidgemisch ein, verbrennt darin und expandiert in Richtung der Austrittsöffnung.Combustion chambers, in particular for gas turbines, are generally provided in their interior with a flow guide body, which is referred to as a liner. In principle, different concepts for combustion chamber arrangements are known. For example, combustion chamber arrangements are used which are composed of a plurality of individual combustion chambers, which open into a common opening. In the case of a gas turbine, the opening is preferably formed as an annular opening, which also represents the transition to the turbine room. A burner, which is provided in the combustion chamber, supplies a combustible fluid mixture, which ignites in the combustion chamber and is conducted through the liner in the direction of the outlet opening. Another concept of a combustor assembly provides a single annular annular combustor instead of a plurality of individual combustors. In such an annular combustion chamber burned ignited combustible fluid mixture enters, burns therein and expands in the direction of the outlet opening.

Da die Wandungen der Brennkammer aufgrund der im Inneren der Brennkammer stattfindenden Verbrennung hohen thermischen Belastungen ausgesetzt sind, müssen diese Teile der Brennkammer gekühlt werden. Dies wird üblicherweise durch Spalträume erreicht, durch die ein Kühlmittel geleitet wird, welches die Brennkammer konvektiv kühlt.Since the walls of the combustion chamber are exposed to high thermal loads due to the combustion taking place inside the combustion chamber, these parts of the combustion chamber must be cooled. This is usually achieved by fissures, through which a coolant is passed, which cools the combustion chamber convectively.

Insbesondere der im Inneren der Brennkammer angeordnete Liner ist einer hohen physikalischen Beanspruchung ausgesetzt, weshalb dieser einem Verschleiss unterliegt. Daher ist eine Anordnung vorgesehen, die es ermöglicht, den Liner, insbesondere Teile davon, auszutauschen. Dazu sind im Stand der Technik schienenartige Stäbe angeordnet, über die einzelne Linerelemente mit der Brennkammerwandung verbunden sind. Die zwischen dem Liner und dem Gehäuse angeordneten Schienen sind zwar in einem vergleichsweise kühlen Bereich der Brennkammer angeordnet, so dass eine Demontage von innen nicht auf einfache Weise durchführbar ist. Insgesamt ist aber auch der Liner wegen der Befestigung nach innen nur sehr kompliziert herstellbar. Darüber hinaus ergeben sich Thermospannungen aufgrund der sehr hohen Seitenwände.In particular, the arranged inside the combustion liner is exposed to high physical stress, which is why this is subject to wear. Therefore, an arrangement is provided which makes it possible to replace the liner, in particular parts thereof. For this purpose, rail-like rods are arranged in the prior art, via which individual liner elements are connected to the combustion chamber wall. Although arranged between the liner and the housing rails are arranged in a relatively cool region of the combustion chamber, so that disassembly from the inside is not feasible in a simple manner. Overall, however, the liner is only very complicated to produce because of the attachment to the inside. In addition, thermoelectric voltages result due to the very high side walls.

Aus DE 86 03 826 U1 ist ein Auskleidung für eine Innenwand eines Industrieofens bekannt, die der Ofenwand zum Ofeninnenraum hin vorgelagerte Keramikfaser-Isolierstoff-Formteile umfasst. Zwischen den Keramikfaser-Isolierstoff-Formteilen und der Ofenwand sind federelastisch nachgiebige Fasermatten angeordnet. Zwischen benachbarten, mit Abstand nebeneinander angeordneten Formteilen ist jeweils eine T-förmig profilierte Leiste mit einem Leistensteg und einem Leistenflansch angeordnet. Der Leistensteg greift zwischen die Formteile während der Leistenflansch ofeninnenseitig dichtschließend an den Formteilen anliegt. Eine Kühlung der leiste oder der Formteile mittels Kühlfluid ist nicht beschrieben.Out DE 86 03 826 U1 a lining for an inner wall of an industrial furnace is known, which comprises the oven wall upstream of the furnace interior ceramic fiber insulating molded parts. Between the ceramic fiber insulating molded parts and the furnace wall resilient elastomeric fiber mats are arranged. Between adjacent, spaced apart juxtaposed mold parts in each case a T-shaped profiled strip with a strip web and a strip flange is arranged. The strip web engages between the mold parts while the strip flange abuts the inside of the strip in a tight manner. Cooling of the bar or the molded parts by means of cooling fluid is not described.

Der Erfindung liegt daher die Aufgabe zugrunde, eine Befestigung für Linerelemente einer Brennkammer vorzusehen, mit der nicht nur eine Montagevereinfachung von der Innenseite des Liners her erreichbar ist, sondern die auch eine Kühlung ermöglicht.The invention is therefore based on the object to provide an attachment for liner elements of a combustion chamber, with which not only a simplification of the assembly of the inside of the liner can be reached, but also allows cooling.

Als Lösung dieser Aufgabe wird mit der vorliegenden Erfindung eine gattungsgemäße Brennkammer mit einem an der Brennkammer angeordneten Brenner, einem in der Brennkammer angeordneten Liner und einer Auslassöffnung vorgeschlagen, wobei der Liner Linerelemente aufweist, die mittels Schienenelementen elastisch an einem Brennkammergehäuse festlegbar sind, wobei die Schienenelemente brennkammerseitig angeordnet sind und zwischen zwei benachbart angeordneten Linerelementen nach außen ragen. Das Schienenelement und die Linerelemente weisen Kühlmittelkanäle auf, die strömungstechnisch miteinander in Verbindung stehen.As a solution to this problem is with the present invention, a generic combustion chamber with an on the Combustor arranged burner, a combustion chamber arranged in the liner and an outlet opening proposed, wherein the liner has liner elements which are elastically fixed by means of rail elements on a combustion chamber housing, wherein the rail elements are arranged combustion chamber side and protrude between two adjacently arranged liner elements to the outside. The rail element and the liner elements have coolant channels, which are fluidically connected with each other.

Erstmals sind die Schienen auf der Heißgasseite angeordnet und bilden einen Teil der Brennkammerinnenwand. Dadurch können die Linerverbindungen nach außen zeigen, wodurch der Liner konstruktiv einfacher und darüber hinaus flacher ausgestaltet werden kann. Darüber hinaus können innere Spannungen reduziert werden. Eine Demontage nach innen sowie eine Montage von innen der Linerelemente kann erreicht werden.For the first time, the rails are arranged on the hot gas side and form part of the combustion chamber inner wall. As a result, the liner connections can point outward, which makes the liner structurally simpler and moreover flat. In addition, internal stresses can be reduced. Dismantling to the inside and mounting from inside the liner elements can be achieved.

Es wird ferner vorgeschlagen, dass das Linerelement mittels eines außenseitig am Schienenelement vorgesehenen Befestigungselements festlegbar ist. Vorteilhaft können so Standardbefestigungsmittel eingesetzt werden, um die Linerelemente an den Schienenelementen festzulegen. Kosten und Montageaufwand können reduziert werden.It is further proposed that the liner element can be fixed by means of a fastening element provided on the outside of the rail element. Advantageously, standard fastening means can thus be used to fix the liner elements to the rail elements. Costs and assembly costs can be reduced.

Weiterhin wird vorgeschlagen, dass das Befestigungselement durch eine Schraube gebildet ist. So kann eine lösbare Verbindung erreicht werden, die mittels konventioneller, bekannter Werkzeuge ausführbar ist. Spezialwerkzeuge zum Ausführen der Befestigung können vermieden werden.Furthermore, it is proposed that the fastening element is formed by a screw. Thus, a releasable connection can be achieved, which can be carried out by means of conventional, known tools. Special tools to perform the attachment can be avoided.

Daneben wird vorgeschlagen, dass das Befestigungselement durch ein Klemmelement, insbesondere eine Klemmfeder, gebildet ist. Mit dem Einsatz von Klemmfedern kann eine besonders einfache und schnelle Montage bzw. Demontage von Linerelementen erreicht werden. Dies wirkt sich insbesondere dann vorteilhaft aus, wenn die Standzeit einer Anlage wie z.B. einer Gasturbine, einen wesentlichen Kostenfaktor darstellt. Geringe Standzeiten können erreicht werden.In addition, it is proposed that the fastening element is formed by a clamping element, in particular a clamping spring. With the use of clamping springs, a particularly simple and fast assembly or disassembly of liner elements can be achieved. This has an advantageous effect in particular when the service life of a system, such as a gas turbine, represents a significant cost factor. Low lifetimes can be achieved.

In einer weiteren Ausgestaltung wird vorgeschlagen, dass das Schienenelement zumindest brennkammerseitig eine Beschichtung aufweist. Die Beschichtung kann einerseits sowohl zur Reduzierung der physikalischen Beanspruchung während des bestimmungsgemäßen Betriebs als auch zur Reduzierung des Verschleisses führen. Wartungsintervalle können verlängert werden. Es kann jedoch auch eine Beschichtung vorgesehen sein, um beispielsweise eine inerte Oberfläche in Bezug auf das in der Brennkammer befindliche Fluid zu bilden. Das Schienenelement kann auch auf seiner gesamten Oberfläche mit einer Beschichtung versehen sein, um beispielsweise einen Beschichtungsprozess zu vereinfachen.In a further embodiment, it is proposed that the rail element has a coating at least on the combustion chamber side. On the one hand, the coating can lead both to reducing the physical stress during normal operation and to reducing wear. Maintenance intervals can be extended. However, a coating may also be provided to form, for example, an inert surface with respect to the fluid in the combustion chamber. The rail element can also be provided with a coating on its entire surface in order to simplify, for example, a coating process.

Um eine Kühlung der Schienenelemente zu erreichen, wird vorgeschlagen, dass das Schienenelement linerartige Zehen zur Herstellung einer strömungstechnischen Verbindung zwischen einem Kanal des Schienenelements und einem Kanal des Linerelements für ein Kühlmittel aufweist. Es kann vorteilhaft ein Kühlsystem erreicht werden, welches zugleich eine Kühlung der Linerelemente als auch der Schienenelemente ermöglicht.In order to achieve a cooling of the rail elements, it is proposed that the rail element has liner-like toes for establishing a fluidic connection between a channel of the rail element and a channel of the liner element for a coolant. It can be advantageously achieved a cooling system, which also allows cooling of the liner elements and the rail elements.

Darüber hinaus wird vorgeschlagen, dass die Brennkammer eine geschlossene Kühlung aufweist. So kann vorteilhaft das Kühlmittel zur Brennkammer zugeführt werden, wobei es seine im Rahmen der Kühlfunktion aufgenommene Energie wieder dem Prozess zuführt. So kann einerseits Energieverlust aufgrund der Kühlfunktion reduziert werden und andererseits das Kühlmittel zur Verbrennung in der Brennkammer verwendet werden. Ein hoher Wirkungsgrad kann erreicht werden.In addition, it is proposed that the combustion chamber has a closed cooling. Thus, advantageously, the coolant can be supplied to the combustion chamber, wherein it feeds its energy absorbed in the context of the cooling function back to the process. Thus, on the one hand energy loss due to the cooling function can be reduced and on the other hand, the coolant can be used for combustion in the combustion chamber. A high efficiency can be achieved.

In einer weiteren Ausgestaltung wird vorgeschlagen, dass die Brennkammer in einer Strömungsmaschine, insbesondere einer Gasturbine angeordnet ist. Wartungsaufwand sowie Standzeiten einer Gasturbine können weiter reduziert werden.In a further embodiment, it is proposed that the combustion chamber is arranged in a turbomachine, in particular a gas turbine. Maintenance costs and service life of a gas turbine can be further reduced.

Mit der Erfindung wird ferner ein Verfahren zur Kühlung einer erfindungsgemäßen Brennkammer vorgeschlagen, wobei ein die Linerschiene durchströmendes Kühlmittel zumindest teilweise in Umfangsrichtung der Brennkammer in Richtung des Linerelements strömt und in einem Kanal des Linerelements in oder gegen die Strömungsrichtung der Brennkammer umgelenkt wird. Vorteilhaft kann ein in einem Linerelement vorgesehener Kanal, der beispielsweise zur Kühlung des Linerelements vorgesehen ist, für eine Abführung des die Linerschiene durchströmenden Kühlmittels verwendet werden. Gerade bei einem geschlossenen Kühlsystem für eine Brennkammer kann so der konstruktive Aufwand für die Strömungsführung des Kühlmittels reduziert werden. Auch können Bauteile und Montageaufwand reduziert werden, wenn beispielsweise eine separate Kühlfluidabführung eingespart werden kann.The invention further proposes a method for cooling a combustion chamber according to the invention, wherein a coolant flowing through the liner rail flows at least partially in the circumferential direction of the combustion chamber in the direction of the liner element and is deflected in or against the flow direction of the combustion chamber in a channel of the liner element. Advantageously, a channel provided in a liner element, which is provided, for example, for cooling the liner element, can be used for discharging the coolant flowing through the liner rail. Especially with a closed cooling system for a combustion chamber so the design effort for the flow guidance of the coolant can be reduced. Also, components and assembly costs can be reduced if, for example, a separate Kühlfluidabführung can be saved.

In einer vorteilhaften Weiterbildung der vorliegenden Erfindung wird vorgeschlagen, dass als Kühlmittel Luft verwendet wird. So kann vorteilhaft, beispielsweise bei einer Gasturbine, aus einer Ansaugluft ein Teil abgezweigt werden, der zur Kühlung verwendet wird. Besonders vorteilhaft der zur Kühlung verwendete Anteil der Luft wieder der Brennkammer zugeführt, so dass einerseits die durch die Kühlfunktion aufgenommene Wärme als auch die Energie zur Bereitstellung der Kühlluft dem Prozess zumindest teilweise wieder zugeführt werden kann. Eine weitere Erhöhung des Wirkungsgrads kann erreicht werden.In an advantageous development of the present invention, it is proposed that air is used as the coolant. Thus, it is advantageous, for example in the case of a gas turbine, to branch off a part of an intake air which is used for cooling. Particularly advantageously, the proportion of the air used for cooling fed back to the combustion chamber, so that on the one hand, the heat absorbed by the cooling function and the energy for providing the cooling air can be at least partially recycled to the process. A further increase in the efficiency can be achieved.

Weitere Einzelheiten, Merkmale und Vorteile der Erfindung sind der folgenden Beschreibung eines Ausführungsbeispiels zu entnehmen. Im wesentlichen gleichbleibende Bauteile sind mit den gleichen Bezugszeichen bezeichnet. Ferner wird bezüglich gleicher Merkmale und Funktionen auf die Beschreibung des Ausführungsbeispiels in Fig. 1 verwiesen.Further details, features and advantages of the invention will be apparent from the following description of an embodiment. Substantially identical components are designated by the same reference numerals. Furthermore, with regard to the same features and functions, reference is made to the description of the embodiment in FIG Fig. 1 directed.

Es zeigen:

Fig. 1
einen Querschnitt durch eine Ringbrennkammer einer nicht weiter dargestellten Gasturbine,
Fig. 2
eine vergrößerte Darstellung des oberen Teils der Ringbrennkammer aus Fig. 1,
Fig. 3
eine schematisch perspektivische Ansicht eines Schienenelements zur Verbindung zweier benachbart angeordneter Linerelemente und
Fig. 4
eine schematische Darstellung des Kühlmittelverlaufs zur Kühlung der erfindungsgemäßen Anordnung.
Show it:
Fig. 1
a cross section through an annular combustion chamber of a gas turbine not shown,
Fig. 2
an enlarged view of the upper part of the annular combustion chamber Fig. 1 .
Fig. 3
a schematic perspective view of a rail element for connecting two adjacently arranged liner elements and
Fig. 4
a schematic representation of the coolant flow for cooling the arrangement according to the invention.

Fig. 1 zeigt einen Ausschnitt einer Gasturbine mit einer erfindungsgemäßen Brennkammer 1, die im vorliegenden Fall als Ringbrennkammer ausgestaltet ist. Die Brennkammer 1 weist ein Gehäuse 7 auf, in welchem ein Liner 4 angeordnet ist. An einem Ende des Liners 4 mündet ein Brenner 2, über den ein brennbares Fluid zugeführt wird. Am gegenüberliegenden Ende des Liners ist eine Austrittsöffnung 3 vorgesehen, die mit einem Eingang zu einem Strömungskanal einer nachgeschalteten Gasturbine verbunden ist, die nicht weiter dargestellt ist. Mittig ist eine Rotorwelle 14 angeordnet. In Fig. 2 ist der obere Teil der Brennkammer 1 im Schnitt vergrößert dargestellt. Das über den Brenner 2 zugeführte brennbare Fluid wird in einem Brennraum 15 im Liner 4 gezündet und strömt in Richtung Auslassöffnung 3 zur nachfolgenden Turbine. Fig. 1 shows a section of a gas turbine with a combustion chamber 1 according to the invention, which is designed in the present case as an annular combustion chamber. The combustion chamber 1 has a Housing 7, in which a liner 4 is arranged. At one end of the liner 4 opens a burner 2, via which a combustible fluid is supplied. At the opposite end of the liner, an outlet opening 3 is provided, which is connected to an inlet to a flow channel of a downstream gas turbine, which is not shown. In the middle, a rotor shaft 14 is arranged. In Fig. 2 the upper part of the combustion chamber 1 is shown enlarged in section. The combustible fluid supplied via the burner 2 is ignited in a combustion space 15 in the liner 4 and flows in the direction of the outlet opening 3 to the downstream turbine.

Der Liner 4 ist segmentartig aus Linerelementen 5 aufgebaut, die über Schienenelemente 6 jeweils benachbart miteinander verbunden sind (Fig. 3). Über die Schienenelemente 6 sind die Linerelemente 5 zugleich elastisch mit dem Brennkammergehäuse 7 der Brennkammer 1 festgelegt. Erfindungsgemäß sind die Schienenelemente 6 brennkammerseitig angeordnet und ragen zwischen zwei benachbart angeordneten Linerelementen 5 nach außen. Zur Befestigung weist das Schienenelement 6 Öffnungen 17 auf, durch die eine Befestigungsvorrichtung 8 einführbar ist, über die das Schienenelement 6 elastisch mit dem Gehäuse 7 der Brennkammer 1 festgelegt ist. Zur Kompensation auftretender Ausdehnungen sind die Befestigungsvorrichtungen 8 in ihrer Längserstreckung elastisch ausgebildet. Zur Abdichtung zwischen dem Schienenelement 6 und dem Linerelement 5 ist jeweils ein Dichtungselement 16 vorgesehen.The liner 4 is constructed in a segment-like manner from liner elements 5, which are each connected adjacent to one another via rail elements 6 ( Fig. 3 ). Via the rail elements 6, the liner elements 5 are at the same time fixed elastically to the combustion chamber housing 7 of the combustion chamber 1. According to the invention, the rail elements 6 are arranged on the combustion chamber side and protrude between two adjacently arranged liner elements 5 to the outside. For attachment, the rail element 6 has openings 17 through which a fastening device 8 can be inserted, via which the rail element 6 is fixed elastically to the housing 7 of the combustion chamber 1. To compensate occurring expansions, the fastening devices 8 are formed elastically in their longitudinal extent. For sealing between the rail element 6 and the liner element 5, a sealing element 16 is provided in each case.

Das Schienenelement 6 liegt heißgasseitig zwischen den zwei benachbarten Linern 5 auf nicht weiter dargestellten außen liegenden Linerverhakungen auf und spannt die Linerelemente 5 fest. Das Schienenelement 6 weist ferner abwechselnd über seine Längserstreckung wechselnd gestaffelte Befestigungsbereiche und Kühlbereiche auf. Ferner sind im Schienenelement Öffnungen 11 vorgesehen, über die ein Kühlmittel vom Schienenelement 6 über einen in einem Randbereich des Linerelements 5 vorgesehenen Kanal 20 in den Kanal 13 des Linerelements 5 strömt. Durch in dieser Ausgestaltung gegen die Strömungsrichtung der Brennkammer strömendes Kühlmittel im Kanal 13 wird das durch den Kanal 20 eingeleitete Kühlmittel ebenfalls in Strömungsrichtung 21 umgelenkt (Fig. 4). Brennkammerseitig ist das Schienenelement 6 mit einer Beschichtung 9 versehen, welche gegenüber der Heißgasströmung innerhalb der Brennkammer 1 eine thermische Isolation bewirkt. Zugleich bildet die Beschichtung 9 einen Schutz, durch den die Alterung des Schienenelements 6 reduziert wird. Zur strömungstechnischen Verbindung zwischen dem Kühlmittelkanal 12 des Schienenelements 6 und dem Kühlmittelkanal 13 des Linerelements 5 weist das Schienenelement 6 linerartige Zehen auf, in denen die Linerelemente 5 am Gehäuse 7 der Brennkammer 1 befestigt werden. Von diesen wird der Kühlmittelstrom in Umfangsrichtung in die Linerelemente 5 abgeführt. Vorteilhaft ist dadurch die zu kühlende Fläche in Befestigungsbereiche 19, die in Umfangsrichtung durchströmt werden, und in Kühlbereiche 18, die axial durchströmt werden, aufgeteilt.The rail element 6 is hot gas side between the two adjacent liners 5 on outer Linerverhakungen not shown on and clamps the liner elements 5 firmly. The rail element 6 also has alternately over its longitudinal extent alternately staggered mounting areas and cooling areas. Furthermore, openings 11 are provided in the rail element, via the one Coolant from the rail member 6 via a provided in an edge region of the liner member 5 channel 20 into the channel 13 of the liner member 5 flows. By flowing in this embodiment against the flow direction of the combustion chamber coolant in the channel 13, the introduced through the channel 20 coolant is also deflected in the flow direction 21 ( Fig. 4 ). On the combustion chamber side, the rail element 6 is provided with a coating 9, which causes thermal insulation in relation to the hot gas flow within the combustion chamber 1. At the same time, the coating 9 forms a protection by which the aging of the rail element 6 is reduced. For the fluidic connection between the coolant channel 12 of the rail element 6 and the coolant channel 13 of the liner element 5, the rail element 6 has liner-like toes, in which the liner elements 5 are fastened to the housing 7 of the combustion chamber 1. Of these, the coolant flow is removed in the circumferential direction in the liner elements 5. Advantageously, the area to be cooled is thereby divided into fastening regions 19, which are flowed through in the circumferential direction, and into cooling regions 18, which are flowed through axially.

In dieser Ausgestaltung wird als Kühlmittel Luft verwendet, welche hinter einem Ansaugkompressor der nicht weiter dargestellten Gasturbine entnommen wird und dem Kühlsystem der Gasturbine zugeführt wird. Die Gasturbine weist eine Brennkammer mit einem geschlossenen Kühlsystem auf, so dass die dem Prozess entnommene Luft für Kühlungszwecke in der Brennkammer wieder zugeführt werden kann. Die durch die Kühlfunktion aufgenommene Wärmeenergie wird so dem Prozess wieder zugeführt.In this embodiment, air is used as the coolant, which is taken behind an intake compressor of the gas turbine, not shown, and the cooling system of the gas turbine is supplied. The gas turbine has a combustion chamber with a closed cooling system, so that the air taken from the process for cooling purposes in the combustion chamber can be fed back. The heat energy absorbed by the cooling function is thus returned to the process.

Das in den Figuren dargestellte Ausführungsbeispiel dient lediglich der Erläuterung der Erfindung und ist für diese nicht beschränkend. So können insbesondere die Form und Ausgestaltung der Linerelemente und der Schienenelemente variieren.The embodiment shown in the figures is only illustrative of the invention and is not limiting for this. In particular, the shape and configuration of the liner elements and the rail elements can vary.

Claims (11)

  1. Combustion chamber for combusting a combustible fluid mixture having a burner (2) disposed on the combustion chamber (1), a liner (4) disposed in the combustion chamber (1), and an outlet opening (3), wherein the liner (4) comprises liner elements (5) which are elastically fixable to a combustion chamber casing (7) by means of rail elements (6), wherein the rail elements (6) are disposed on the combustion chamber side and project outward between two adjacently disposed liner elements (5), characterised in that the rail element (6) and the liner elements (5) have coolant channels (12, 13) and said coolant channels (12, 13) are fluidically connected to one another.
  2. Combustion chamber according to claim 1, characterised in that the liner element (5) has a channel (20) in its edge area via which the coolant can flow from the rail element (6) into the coolant channel of the linear element (5).
  3. Combustion chamber according to claim 1 or claim 2, characterised in that the liner element (5) can be secured by means of a fixing element (8) provided on the outside of the rail element (6).
  4. Combustion chamber according to claim 3, characterised in that the fixing element (8) is formed by a screw.
  5. Combustion chamber according to claim 3,
    characterised in that the fixing element (8) is formed by a clamping element, particularly a clamping spring.
  6. Combustion chamber according to one of claims 1 to 5,
    characterised in that the rail element (6) has a coating (9) at least on the combustion chamber side.
  7. Combustion chamber according to one of claims 1 to 6,
    characterised in that the rail element (6) has liner-like lugs (10) for securing the liner elements (5) with openings (11) for providing a fluidic connection between a coolant channel (12) of the rail element (6) and a coolant channel (13) of the liner element (5).
  8. Combustion chamber according to one of claims 1 to 7,
    characterised by a closed-circuit cooling arrangement.
  9. Combustion chamber according to one of claims 1 to 8,
    characterised by being disposed in a fluid-flow machine, particularly a gas turbine.
  10. Method for cooling a combustion chamber (1) according to one of claims 1 to 9, wherein a coolant flowing through the rail element (6) flows at least partially in the circumferential direction of the combustion chamber (1) in the direction of the liner element (5) and is redirected in a channel (13) of the liner element (5) into or against the flow direction of the combustion chamber (1).
  11. Method according to claim 10, characterised in that air is used as the coolant.
EP02026101A 2002-11-22 2002-11-22 Chamber for the combustion of a fluid combustible mixture Expired - Lifetime EP1422479B1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
ES02026101T ES2307702T3 (en) 2002-11-22 2002-11-22 COMBUSTION CHAMBER FOR THE COMBUSTION OF A FUEL FLUID MIX.
EP02026101A EP1422479B1 (en) 2002-11-22 2002-11-22 Chamber for the combustion of a fluid combustible mixture
DE50212643T DE50212643D1 (en) 2002-11-22 2002-11-22 Combustion chamber for combustion of a combustible fluid mixture
US10/672,506 US7322196B2 (en) 2002-11-22 2003-09-26 Combustion chamber for combusting a combustible fluid mixture
CNB2003101156358A CN100370177C (en) 2002-11-22 2003-11-10 Combustion chamber for firing one kind of combustable liquid mixed fuel
JP2003387648A JP2004177108A (en) 2002-11-22 2003-11-18 Combustor for burning inflammable fluid mixture

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02026101A EP1422479B1 (en) 2002-11-22 2002-11-22 Chamber for the combustion of a fluid combustible mixture

Publications (2)

Publication Number Publication Date
EP1422479A1 EP1422479A1 (en) 2004-05-26
EP1422479B1 true EP1422479B1 (en) 2008-08-13

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EP02026101A Expired - Lifetime EP1422479B1 (en) 2002-11-22 2002-11-22 Chamber for the combustion of a fluid combustible mixture

Country Status (6)

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US (1) US7322196B2 (en)
EP (1) EP1422479B1 (en)
JP (1) JP2004177108A (en)
CN (1) CN100370177C (en)
DE (1) DE50212643D1 (en)
ES (1) ES2307702T3 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2009216788B2 (en) * 2008-02-20 2014-09-25 General Electric Technology Gmbh Gas turbine having an improved cooling architecture
US8863527B2 (en) * 2009-04-30 2014-10-21 Rolls-Royce Corporation Combustor liner
DE102011076473A1 (en) * 2011-05-25 2012-11-29 Rolls-Royce Deutschland Ltd & Co Kg High temperature casting material segment component for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine, and method of manufacturing an annular combustion chamber
BR112017011472B1 (en) * 2014-12-15 2022-09-13 Nuovo Pignone Tecnologie Srl COMBUSTOR FOR A GAS TURBINE AND METHOD FOR ASSEMBLING A COMBUSTOR LINER
GB201501817D0 (en) * 2015-02-04 2015-03-18 Rolls Royce Plc A combustion chamber and a combustion chamber segment

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Publication number Priority date Publication date Assignee Title
US2155165A (en) * 1937-05-28 1939-04-18 Heuer Russell Pearce Furnace roof
US2463217A (en) * 1944-09-28 1949-03-01 Tonneson Paul Refractory brick lined furnace wall
NL69245C (en) * 1946-01-09
US2634694A (en) * 1948-08-18 1953-04-14 Detrick M H Co Suspended arch tile structure
US3328014A (en) * 1965-03-17 1967-06-27 Levi S Longenecker Veneer furnace wall construction
US4246852A (en) * 1979-06-21 1981-01-27 General Signal Corporation Industrial furnace with ceramic insulating modules
DE8603826U1 (en) * 1986-02-13 1986-05-07 Abicht, Roland, Ing.(grad.), 5828 Ennepetal Refractory lining for an industrial furnace
DE3625056C2 (en) * 1986-07-24 1997-05-28 Siemens Ag Refractory lining, in particular for combustion chambers of gas turbine plants
AU594814B2 (en) * 1986-09-13 1990-03-15 Foseco International Limited Furnaces
DE3940381A1 (en) * 1989-12-06 1991-06-13 Pks Engineering Duct for gas turbine exhaust gases - consists of outer and inner wall, insulating layer and cover plates and rails
DE4309200A1 (en) * 1993-03-22 1994-09-29 Abb Management Ag Device for the suspension and removal of parts subject to high thermal loads in turbine plants
DE59706557D1 (en) * 1997-07-28 2002-04-11 Alstom Ceramic lining
GB2368902A (en) * 2000-11-11 2002-05-15 Rolls Royce Plc A double wall combustor arrangement

Also Published As

Publication number Publication date
EP1422479A1 (en) 2004-05-26
ES2307702T3 (en) 2008-12-01
US7322196B2 (en) 2008-01-29
CN100370177C (en) 2008-02-20
DE50212643D1 (en) 2008-09-25
JP2004177108A (en) 2004-06-24
CN1506617A (en) 2004-06-23
US20050097894A1 (en) 2005-05-12

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