EP0909924B1 - Suspension for an annular gas turbine combustor - Google Patents

Suspension for an annular gas turbine combustor

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Publication number
EP0909924B1
EP0909924B1 EP98117869A EP98117869A EP0909924B1 EP 0909924 B1 EP0909924 B1 EP 0909924B1 EP 98117869 A EP98117869 A EP 98117869A EP 98117869 A EP98117869 A EP 98117869A EP 0909924 B1 EP0909924 B1 EP 0909924B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
suspension
leg
arm structure
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
Application number
EP98117869A
Other languages
German (de)
French (fr)
Other versions
EP0909924A2 (en
EP0909924A3 (en
Inventor
Michael Ebel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP0909924A2 publication Critical patent/EP0909924A2/en
Publication of EP0909924A3 publication Critical patent/EP0909924A3/en
Application granted granted Critical
Publication of EP0909924B1 publication Critical patent/EP0909924B1/en
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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
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F01D25/164—Flexible supports; Vibration damping means associated with the bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the invention relates to the suspension of an annular gas turbine combustion chamber in the outlet area of the same on a housing wall, according to the preamble of the main claim.
  • Annular combustion chambers of gas turbines are usually located in their front End area through the projecting into the combustion chamber interior Burner carried while they are in the rear end area, the so-called exit area, suitable on a housing wall, the so-called “combustion chamber outer casing ", in particular in the case of an effusion-cooled Combustion chamber wall with a large number of cooling air through openings, the so-called effusion holes, care must be taken that the rear combustion chamber wall section also has sufficient cooling experiences.
  • the support structure for the combustion chamber suspension may be in thus do not hinder effective cooling in this area.
  • This ring-shaped, bent arm structure, related to the gas turbine longitudinal axis has an inner and an outer leg, is in Experts also known under the term "hair-pin" (hairpin).
  • the inner one Leg closes an acute angle with the outer leg one, as is the inner leg opposite the combustion chamber wall inclined at an acute angle, creating a wedge-shaped annular gap between the inner leg and the combustion chamber wall results in the flow direction of the along the outside of the outer combustion chamber wall Cooling air flow is considered open. In this way, optimal Way to get cooling air to the rear end of the combustion chamber wall.
  • An angled displacement of the arm structure of an annular combustion chamber also shows GB 1578474 A. On its outside leg points this arm structure has recesses.
  • the European patent application EP 521 687 A1 shows the storage of a annular gas turbine combustion chamber, in which an angled arm structure is integrally formed with the combustion chamber wall. The outer The edge of this arm structure is between two components of the housing wall clamped. An additional flange is not provided.
  • the invention is based on the object of a suspension of an annular To create gas turbine combustion chamber of the type mentioned at the outset, which is simple while avoiding the disadvantages of the prior art is constructed, can be used reliably and can be manufactured inexpensively can.
  • the object is characterized by the features of the main claim solved, the subclaims show further advantageous embodiments of the Invention.
  • Reference number 1 denotes an annular combustion chamber of a gas turbine, which is designed here as a stepped combustion chamber and thus next to one
  • a plurality of ring-shaped pilot burners 2 furthermore on the end side also has annularly arranged main burners 3.
  • the combustion chamber 1 is on a housing wall 7 surrounding the entire combustion chamber structure.
  • An annular, kinked design is provided for this Arm structure 8, located on the end portion of the outer combustion chamber wall 9a connects.
  • openings 13 in the arm structure 8 or in the legs 8a, 8b are so-called openings 13 in the arm structure 8 or in the legs 8a, 8b. If these openings or openings 13 in at least one the leg 8a, 8b, but preferably suitable in both legs 8a, 8b dimensioned and arranged, the arm structure 8 acts like one Leaf spring with customizable spring characteristics. Best results were with the design and arrangement explained below achieved by openings 13 in the arm structure 8.
  • the openings 13 are dovetail-shaped designed and distributed equally over the circumference of both legs 8a, 8b arranged, the narrowest sections of the openings of each Kink line 10 of the arm structure 8 are facing.
  • the breakthroughs 13 open to the crease line, so that - after these openings in the outer leg 8b and in the inner leg 8a in the illustration 1, as it were, one above the other - between each breakdown 13 in the outer leg 8b and the adjacent opening 13 there is a so-called connection gap 14 in the inner leg 8a.
  • openings 13 with respect to the burners 2 offset in the circumferential direction, so that the cutting planes 15 of the individual burners 2, 3, for example, exactly in the middle between two each other neighboring openings 13 would come to rest (not shown).
  • any other intermediate positions are also possible Openings 13 in the legs 8a and / or 8b with respect to the burner cutting planes 15th
  • each burner cutting plane 15 in the two legs 8a, 8b exactly one opening 13 provided, i.e. a quotient of the number of openings 13 in one of the legs 8a or 8b (counted over its entire circumference) and the total number of burners 2, 3 and gives exactly the value "1".
  • this quotient “(number of breakthroughs) / (total number the burner) "but also assume other meaningful values, for example 0.5 or 1.5 but also 2 or 2.5 or 3, the integer values of this Quotients have the advantage of simple periodic repetition.
  • different numerical values may be useful for the quotient mentioned, than for graded ones Combustion chambers (as shown here).
  • the inner combustion chamber wall 9b has a receptacle at the end 16 for the guide vane ring adjoining the combustion chamber 1 6, so that this over the combustion chamber 1 and its advantageous Suspension is also kept in an optimal manner.

Description

Die Erfindung betrifft die Aufhängung einer ringförmigen Gasturbinen-Brennkammer im Austrittsbereich derselben an einer Gehäusewand, gemäß dem Oberbegriff des Hauptanspruchs.The invention relates to the suspension of an annular gas turbine combustion chamber in the outlet area of the same on a housing wall, according to the preamble of the main claim.

Ring-Brennkammern von Gasturbinen werden üblicherweise in ihrem vorderen Endbereich durch die in den Brennkammer-Innenraum hineinragenden Brenner getragen, während sie im hinteren Endbereich, dem sog. Austrittsbereich, geeignet an einer Gehäusewand, dem sog. "combustion chamber outer casing", aufgehängt sind. Insbesondere im Falle einer effusionsgekühlten Brennkammerwand mit einer Vielzahl von Kühlluft-Durchtrittsöffnungen, den sog. Effusionslöchern, ist dafür Sorge zu tragen, daß auch der hintere Brennkammer-Wandabschnitt eine ausreichende Kühlung erfährt. Die Tragstruktur für die Aufhängung der Brennkammer darf in diesem Bereich somit die wirkungsvolle Kühlung nicht behindern. Eine Aufhängung bzw. eine Tragstruktur, die diesen Anforderungen gerecht wird, ist beispielsweise in der oben genannten EP 0 564 172 A1 gezeigt. Diese ringförmige, geknickt ausgebildete Armstruktur, die bezogen auf die Gasturbinen-Längsachse einen inneren und einen äußeren Schenkel aufweist, ist in Fachkreisen auch unter dem Begriff "hair-pin" (Haarnadel) bekannt. Der innere Schenkel schließt dabei mit dem äußeren Schenkel einen spitzen Winkel ein, ebenso ist der innere Schenkel gegenüber der Brennkammerwand unter einem spitzen Winkel geneigt, wodurch sich ein keilförmiger Ringspalt zwischen innerem Schenkel und Brennkammerwand ergibt, der in Anströmrichtung des an der Außenseite der äußeren Brennkammerwand entlanggeführten Kühlluftstromes betrachtet offen ist. Auf diese Weise kann auf optimale Weise Kühlluft bis zum hintersten Ende der Brennkammerwand gelangen.Annular combustion chambers of gas turbines are usually located in their front End area through the projecting into the combustion chamber interior Burner carried while they are in the rear end area, the so-called exit area, suitable on a housing wall, the so-called "combustion chamber outer casing ", in particular in the case of an effusion-cooled Combustion chamber wall with a large number of cooling air through openings, the so-called effusion holes, care must be taken that the rear combustion chamber wall section also has sufficient cooling experiences. The support structure for the combustion chamber suspension may be in thus do not hinder effective cooling in this area. A suspension or a supporting structure that meets these requirements shown for example in the above-mentioned EP 0 564 172 A1. This ring-shaped, bent arm structure, related to the gas turbine longitudinal axis has an inner and an outer leg, is in Experts also known under the term "hair-pin" (hairpin). The inner one Leg closes an acute angle with the outer leg one, as is the inner leg opposite the combustion chamber wall inclined at an acute angle, creating a wedge-shaped annular gap between the inner leg and the combustion chamber wall results in the flow direction of the along the outside of the outer combustion chamber wall Cooling air flow is considered open. In this way, optimal Way to get cooling air to the rear end of the combustion chamber wall.

Beim bekannten Stand der Technik, bei welchem diese geknickt ausgebildete Armstruktur bzw. die sog. Haarnadel/hair-pin an der Außenwand der ringförmigen Brennkammer vorgesehen ist, stützt sich diese Brennkammer über diese Armstruktur lediglich an der die Brennkammerwand umgebenden Gehäusewand ab, wohingegen die eigentliche Befestigung der Brennkammer über die innere Wand der Ring-Brennkammer erfolgt Dies kann zu unerwünscht großen Relativbewegungen im hinteren Endabschnitt der Brennkammer führen.In the known prior art, in which it is designed to be kinked Arm structure or the so-called hairpin on the outer wall of the annular combustion chamber is provided, this combustion chamber is supported via this arm structure only on the one surrounding the combustion chamber wall Housing wall, whereas the actual attachment of the combustion chamber This can be undesirable via the inner wall of the ring combustion chamber large relative movements in the rear end portion of the combustion chamber to lead.

Den nächstkommenden Stand der Technik zeigt die DE 196 00 837 A1. Aus dieser Druckschrift ist eine axial-gestufte Ring-Brennkammer einer Gasturbine bekannt, bei welcher die Aufhängung mittels einer geknickt ausgebildeten Armstruktur erfolgt, bei welcher sich an den äußeren Schenkel der Armstruktur ein Flansch anschliesst, der über ein lösbares Verbindungselement mit der Gehäusewand verbunden ist. DE 196 00 837 A1 shows the closest prior art. Out this publication is an axially stepped annular combustion chamber of a gas turbine known in which the suspension is designed by means of a kinked Arm structure takes place at which on the outer leg of the arm structure a flange connects, which has a detachable connecting element is connected to the housing wall.

Eine abgewinkelte Armstrukturverlagerung einer ringförmigen Brennkammer zeigt weiterhin die GB 1578474 A. An ihrem außenseitigen Schenkel weist diese Armstruktur Ausnehmungen auf.An angled displacement of the arm structure of an annular combustion chamber also shows GB 1578474 A. On its outside leg points this arm structure has recesses.

Aus dem US-Patent 5,323,605 ist ebenfall eine abgewinkelte Armstruktur vorbekannt. Diese ist allerdings an ihrem äußeren Randbereich nur geklemmt, nicht lösbar verschraubt.An angled arm structure is also known from US Pat. No. 5,323,605 previously known. However, this is only clamped on its outer edge area, screwed not detachable.

Die europäische Patentanmeldung EP 521 687 A1 zeigt die Lagerung einer ringförmigen Gasturbine-Brennkammer, bei welcher eine abgewinkelte Armstruktur einstückig mit der Brennkammerwand ausgebildet ist. Der äußere Rand dieser Armstruktur wird zwischen zwei Bauelementen der Gehäusewand geklemmt. Ein zusätzlicher Flansch ist nicht vorgesehen.The European patent application EP 521 687 A1 shows the storage of a annular gas turbine combustion chamber, in which an angled arm structure is integrally formed with the combustion chamber wall. The outer The edge of this arm structure is between two components of the housing wall clamped. An additional flange is not provided.

Der Erfindung liegt die Aufgabe zu Grunde, eine Aufhängung einer ringförmigen Gasturbinen-Brennkammer der eingangs genannten Art zu schaffen, welche unter Vermeidung der Nachteile des Standes der Technik einfach aufgebaut, betriebssicher einsetzbar ist und kostengünstig hergestellt werden kann.The invention is based on the object of a suspension of an annular To create gas turbine combustion chamber of the type mentioned at the outset, which is simple while avoiding the disadvantages of the prior art is constructed, can be used reliably and can be manufactured inexpensively can.

Erfindungsgemäß wird die Aufgabe durch die Merkmale des Hauptanspruchs gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung. According to the invention the object is characterized by the features of the main claim solved, the subclaims show further advantageous embodiments of the Invention.

Näher erläutert wird die Erfindung anhand eines bevorzugten Ausführungsbeispieles. Dabei zeigt

Fig. 1
einen Teilschnitt durch eine Gasturbinen-Ring-Brennkammer mit einer erfindungsgemäßen Aufhängung,
Fig. 2
die Ansicht X aus Fig. 1 als Teil-Abwicklung der ringförmigen Armstruktur, sowie
Fig. 3
wesentliche Elemente der Ansicht A aus Fig. 1.
The invention is explained in more detail with reference to a preferred exemplary embodiment. It shows
Fig. 1
2 shows a partial section through a gas turbine ring combustion chamber with a suspension according to the invention,
Fig. 2
the view X from Fig. 1 as a partial development of the annular arm structure, and
Fig. 3
essential elements of view A from FIG. 1.

Mit der Bezugsziffer 1 ist eine Ring-Brennkammer einer Gasturbine bezeichnet, die hier als gestufte Brennkammer ausgebildet ist und somit neben einer Vielzahl von ringförmig angeordneten Pilot-Brennern 2 stimseitig desweiteren ebenfalls ringförmig angeordnete Haupt-Brenner 3 aufweist. Im Austrittsbereich 4 der Brennkammer 1 - an diesen schließt sich ein eine Vielzahl von Leitschaufeln 5 tragender Leitschaufelring 6 an - ist die Brennkammer 1 an einer die gesamte Brennkammerstruktur umgebenden Gehäusewand 7 aufgehängt. Vorgesehen ist hierfür eine ringförmige, geknickt ausgebildete Armstruktur 8, die sich an den Endabschnitt der äußeren Brennkammerwand 9a anschließt. Aufgrund des Knickes entlang der ebenfalls ringförmigen sog. Knicklinie 10 besitzt diese Armstruktur 8 bezüglich der Gasturbinen-Längsachse 11 einen inneren Schenkel 8a sowie einen äußeren Schenkel 8b, die in der Knicklinie 10 aufeinandertreffen und zwischen sich einen spitzen Winkel einschließen. Ebenso liegt ein spitzer Winkel zwischen der äußeren Brennkammerwand 9a und dem inneren Schenkel 8a sowie zwischen der Gehäusewand 7 und dem äußeren Schenkel 8b vor.Reference number 1 denotes an annular combustion chamber of a gas turbine, which is designed here as a stepped combustion chamber and thus next to one A plurality of ring-shaped pilot burners 2 furthermore on the end side also has annularly arranged main burners 3. In the exit area 4 of the combustion chamber 1 - this is followed by a variety of Guide vanes 5 carrying guide vane ring 6 - the combustion chamber 1 is on a housing wall 7 surrounding the entire combustion chamber structure. An annular, kinked design is provided for this Arm structure 8, located on the end portion of the outer combustion chamber wall 9a connects. Due to the kink along the so-called ring-shaped Kink line 10 has this arm structure 8 with respect to the gas turbine longitudinal axis 11 an inner leg 8a and an outer leg 8b, which meet in the kink line 10 and point between them Include angles. There is also an acute angle between the outer one Combustion chamber wall 9a and the inner leg 8a and between the Housing wall 7 and the outer leg 8b.

An das der Knicklinie 10 abgewandte Ende des äußeren Schenkels 8b schließt sich ein in radialer Richtung erstreckender Flansch 8c an, der über ein lösbares Verbindungselement 12 (in Form einer Schraube-Mutter-Verbindung) mit einem ebenfalls in radialer Richtung, d. h. senkrecht zur Gasturbinen-Längsachse 11 verlaufenden Flansch 7a der Gehäusewand 7 verbunden ist. Nachdem über dem Umfang der Brennkammer 1 bzw. der Gehäusewand 7 verteilt eine Vielzahl derartiger Verbindungselemente 12 vorgesehen sind, ist eine sichere und insbesondere unerwünschte Relativbewegungen verhindernde Aufhängung der Brennkammer 1 in deren Austrittsbereich 4 sichergestellt.At the end of the outer leg 8b facing away from the kink line 10 is followed by a radially extending flange 8c, which over a releasable connecting element 12 (in the form of a screw-nut connection) with a radial direction, too. H. perpendicular to Gas turbine longitudinal axis 11 extending flange 7a of the housing wall 7 connected is. After over the circumference of the combustion chamber 1 or Housing wall 7 distributes a plurality of such connecting elements 12 are provided is a safe and in particular undesirable relative movements preventing the combustion chamber 1 from being suspended in its outlet area 4 ensured.

Dennoch soll eine gewisse Beweglichkeit der Brennkammer 1 gegenüber der Gehäusewand 7 gegeben sein. Ermöglicht wird diese Beweglichkeit mittels sog. Durchbrechnungen 13 in der Armstruktur 8 bzw. in den Schenkeln 8a, 8b. Werden diese Durchbrüche bzw. Durchbrechungen 13 in zumindest einem der Schenkel 8a, 8b, bevorzugt jedoch in beiden Schenkeln 8a, 8b geeignet dimensioniert und angeordnet, so wirkt die Armstruktur 8 ähnlich einer Blattfeder mit gezielt gestaltbarer Federcharakteristik. Beste Ergebnisse wurden dabei mit der im folgenden erläuterten Gestaltung und Anordnung von Durchbrechungen 13 in der Armstruktur 8 erzielt.Nevertheless, a certain mobility of the combustion chamber 1 with respect to the Housing wall 7 be given. This mobility is made possible by so-called openings 13 in the arm structure 8 or in the legs 8a, 8b. If these openings or openings 13 in at least one the leg 8a, 8b, but preferably suitable in both legs 8a, 8b dimensioned and arranged, the arm structure 8 acts like one Leaf spring with customizable spring characteristics. Best results were with the design and arrangement explained below achieved by openings 13 in the arm structure 8.

Wie Fig. 2 zeigt, sind die Durchbrechnungen 13 schwalbenschwanzförmig gestaltet und über dem Umfang beider Schenkel 8a, 8b gleichartig verteilt angeordnet, wobei die engsten Abschnitte der Durchbrechungen jeweils der Knicklinie 10 der Armstruktur 8 zugewandt sind. Zusätzlich sind die Durchbrechnungen 13 zur Knicklinie hin offen, so daß - nachdem diese Durchbrechungen im äußeren Schenkel 8b und im inneren Schenkel 8a bei der Darstellung nach Fig. 1 quasi übereinanderliegen - zwischen jeder Durchbrechnung 13 im äußeren Schenkel 8b und der benachbarten Durchbrechung 13 im inneren Schenkel 8a eine sog. Verbindungslücke 14 vorliegt. Mit dieser Gestaltung ergibt sich zum einen eine ausreichende Weichheit, um Dehnungen der Brennkammer 1 gegenüber der Gehäusewand 7 aufzunehmen, andererseits jedoch eine ausreichende Festigkeit, um die Brennkammer 1 sicher an der Gehäusewand 7 aufzuhängen.As shown in FIG. 2, the openings 13 are dovetail-shaped designed and distributed equally over the circumference of both legs 8a, 8b arranged, the narrowest sections of the openings of each Kink line 10 of the arm structure 8 are facing. In addition, the breakthroughs 13 open to the crease line, so that - after these openings in the outer leg 8b and in the inner leg 8a in the illustration 1, as it were, one above the other - between each breakdown 13 in the outer leg 8b and the adjacent opening 13 there is a so-called connection gap 14 in the inner leg 8a. With this Design results on the one hand a sufficient softness to stretch to record the combustion chamber 1 with respect to the housing wall 7, on the other hand however, sufficient strength to secure the combustion chamber 1 to hang on the housing wall 7.

Wie Fig. 3 zeigt sind bei der hier dargestellten gestuften Ring-Brennkammer 1 die Pilot-Brenner 2 und die Haupt-Brenner 3 in Umfangsrichtung versetzt zueinander angeordnet. Eine optimale erfindungsgemäße Brennkammer-Aufhängung ergibt sich bei dieser Anordnung dann, wenn in der Schnittebene 15 jedes Brenners (diese Schnittebene 15 verläuft wie üblich durch den Brenner 2 bzw. 3 selbst sowie durch die Gasturbinen-Längsachse 11) zumindest in einem der Schenkel 8a bzw. 8b, bevorzugt jedoch in beiden der Schenkel 8a, 8b eine Durchbrechung 13 vorgesehen ist, wobei in dieser Schnittebene 15 auch die sog. Verbindungslücke 14 zum Liegen kommt.3 shows are in the stepped ring combustion chamber shown here 1 the pilot burner 2 and the main burner 3 offset in the circumferential direction arranged to each other. An optimal combustion chamber suspension according to the invention this arrangement results when in the section plane 15 of each burner (this cutting plane 15 runs through the Burner 2 or 3 itself and at least through the gas turbine longitudinal axis 11) in one of the legs 8a or 8b, but preferably in both of the Leg 8a, 8b, an opening 13 is provided, in this Section plane 15 also the so-called connection gap 14 comes to rest.

Es ist jedoch auch möglich, die Durchbrechungen 13 gegenüber den Brennern 2 in Umfangsrichtung versetzt anzuordnen, so daß dann die Schnittebenen 15 der einzelnen Brenner 2, 3 bspw. exakt mittig zwischen zwei einander benachbarten Durchbrechungen 13 zum Liegen kämen (nicht gezeigt). Möglich sind jedoch auch sonstige beliebige Zwischenpositionen der Durchbrechungen 13 in den Schenkeln 8a und/oder 8b bezüglich der Brenner-Schnittebenen 15.However, it is also possible to have the openings 13 with respect to the burners 2 offset in the circumferential direction, so that the cutting planes 15 of the individual burners 2, 3, for example, exactly in the middle between two each other neighboring openings 13 would come to rest (not shown). However, any other intermediate positions are also possible Openings 13 in the legs 8a and / or 8b with respect to the burner cutting planes 15th

Beim hier dargestellten Ausführungsbeispiel ist bezüglich jeder Brenner-Schnittebene 15 in den beiden Schenkeln 8a, 8b exakt eine Durchbrechung 13 vorgesehen, d.h. ein Quotient aus der Anzahl von Durchbrechungen 13 in einem der Schenkel 8a bzw. 8b (über dessen gesamten Umfang gezählt) und der Gesamtzahl der Brenner 2, 3 und ergibt hier exakt den Wert "1". Alternativ kann dieser Quotient " (Anzahl der Durchbrechungen) / (Gesamtzahl der Brenner) " aber auch andere sinnvolle Werte annehmen, so bspw. 0,5 oder 1,5 aber auch 2 oder 2,5 oder 3, wobei die ganzzahligen Werte dieses Quotienten den Vorteil der einfachen periodischen Widerholung haben. In anderen Worten ausgedrückt bedeutet dies, daß alternativ nur halb soviele Durchbrechungen 13 in den Schenkeln 8a, 8b der Armstruktur 8 vorgesehen sind als Brenner 2, 3 vorhanden sind, oder daß dreimal soviele Durchbrechungen 13 vorhanden sind, als Brenner vorgesehen sind. Insbesondere sei darauf hingewiesen, daß bei nicht gestuften Brennkammern andere Zahlenwerte für den genannten Quotienten sinnvoll sein können, als bei gestuften Brennkammern (wie hier gezeigt).In the embodiment shown here is with respect to each burner cutting plane 15 in the two legs 8a, 8b exactly one opening 13 provided, i.e. a quotient of the number of openings 13 in one of the legs 8a or 8b (counted over its entire circumference) and the total number of burners 2, 3 and gives exactly the value "1". alternative can this quotient "(number of breakthroughs) / (total number the burner) "but also assume other meaningful values, for example 0.5 or 1.5 but also 2 or 2.5 or 3, the integer values of this Quotients have the advantage of simple periodic repetition. In In other words, this means that alternatively only half as many Openings 13 are provided in the legs 8a, 8b of the arm structure 8 are present as burners 2, 3, or that three times as many openings 13 are present as burners are provided. In particular pointed out that for non-stepped combustion chambers different numerical values may be useful for the quotient mentioned, than for graded ones Combustion chambers (as shown here).

Mit der beschriebenen Konstruktion bzw. Brennkammer-Aufhängung ist eine optimale Anpassung im Hinblick auf Funktion, Gewicht und Lebensdauer der Ring-Brennkammer 1 möglich. Ein Grund hierfür liegt darin, daß durch die periodische Kraftstoffeinspritzung über die Brenner 2, 3 eine periodische mechanische Belastung der Brennkammerwände (der äußeren Brennkammerwand 9a und der inneren Brennkammerwand 9b) vorliegt, die sich in die beschriebene Aufhängung der Brennkammer 1 hinein fortsetzt. Mit dieser beschriebenen Konstruktion kann jeder Belastungsspitze die entsprechend notwendige Struktur entgegengesetzt werden. Mit den im letzten Absatz genannten Teilungsverhältnissen bzw Quotienten im Hinblick auf die Zahl der Durchbrechungen 13 bezogen auf die Anzahl der Brenner ergibt sich eine feste sich wiederholende Beziehung von thermischer/mechanischer Belastung der Brennkammer-Aufhängung in ihrer Gesamtheit sowie jeder Durchbrechung in den Schenkeln 8a, 8b aufgrund der daraus folgenden mechanischen Zustandsbedingungen. With the construction or combustion chamber suspension described is one optimal adjustment with regard to function, weight and lifespan of the Ring combustion chamber 1 possible. One reason for this is that the periodic fuel injection via the burners 2, 3 a periodic mechanical load on the combustion chamber walls (the outer combustion chamber wall 9a and the inner combustion chamber wall 9b), which is in the described suspension of the combustion chamber 1 continues. With this described construction can each peak load accordingly necessary structure are opposed. With those mentioned in the last paragraph Division ratios or quotients with regard to the number of Openings 13 based on the number of burners results in a fixed repetitive relationship of thermal / mechanical load the combustion chamber suspension in its entirety and each opening in the legs 8a, 8b due to the resulting mechanical State conditions.

Wie Fig. 1 zeigt, weist die innere Brennkammerwand 9b endseitig eine Aufnahme 16 für den sich an die Brennkammer 1 anschließenden Leitschaufelring 6 auf, so daß dieser über die Brennkammer 1 sowie deren vorteilhafte Aufhängung gleichfalls in optimaler Weise gehalten ist. Femer erkennt man zwischen dem Endabschnitt der äußeren Brennkammerwand 9a, an welchen sich die erfindungsgemäße Armstruktur 8 anschließt, und dem äußeren Ring des Leitschaufelringes 6 eine umlaufende Dichtung 17, die über eine Vielzahl von Nieten 18 am Leitschaufelring 6 gehalten ist, jedoch kann dies sowie eine Vielzahl weiterer Details insbesondere konstruktiver Art durchaus abweichend vom gezeigten Ausführungsbeispiel gestaltet sein, ohne den Inhalt der Patentansprüche zu verlassen.1 shows, the inner combustion chamber wall 9b has a receptacle at the end 16 for the guide vane ring adjoining the combustion chamber 1 6, so that this over the combustion chamber 1 and its advantageous Suspension is also kept in an optimal manner. You can also see between the end portion of the outer combustion chamber wall 9a at which the arm structure 8 according to the invention connects, and the outer ring the vane ring 6 has a circumferential seal 17, which has a variety is held by rivets 18 on the guide vane ring 6, but this can as well a host of other details, particularly of a constructive nature be designed differently from the embodiment shown, without the Leave the content of the claims.

Bezugszeichenliste:LIST OF REFERENCE NUMBERS

11
Ring-BrennkammerAnnular combustor
22
Pilot-BrennerPilot burner
33
Haupt-BrennerMain burner
44
Austrittsbereichexit area
55
Leitschaufelvane
66
Leitschaufelringvane ring
77
Gehäusewandhousing wall
7a7a
Flanschflange
88th
Armstrukturarm structure
8a8a
innerer Schenkel von 8inner leg of 8
8b8b
äußerer Schenkel von 8outer leg of 8
8c8c
Flanschflange
9a9a
äußere Brennkammerwandouter combustion chamber wall
9b9b
innere Brennkammerwandinner combustion chamber wall
1010
Knickliniefold line
1111
Gasturbinen-LängsachseGas turbine longitudinal axis
1212
Verbindungselement: Schraube-Mutter-VerbindungConnection element: screw-nut connection
1313
Durchbrechungperforation
1414
Verbindungslückeconnecting gap
1515
Schnittebenecutting plane
1616
Aufnahmeadmission
1717
Dichtungpoetry
1818
Nietrivet

Claims (3)

  1. Suspension of a gas turbine annular combustor (1) in its exit area (4) at a casing wall (7) by way of an annular, bent arm structure (8) connecting to the outer combustion-chamber wall (9a) which features an outer and an inner leg (8b, 8a) relative to the gas turbine longitudinal axis, with a flange (8c) connecting to the outer leg (8b) which is firmly attached to the casing wall (7) by means of separable fastener (12),
    characterized in that both legs (8a, 8b) have recesses (13), designed in the form of dovetails, evenly distributed around the circumference whose narrowest sections face the bend line (10) of the arm structure (8) and are open towards the bend line (10), so that a connecting gap (14) is created between each recess (13) in the outer leg (8b) and the adjacent recess (13) in the inner leg (8a).
  2. Suspension of a gas turbine annular combustor according to Claim 1 with a multitude of burners (2, 3) evenly distributed around the combustor circumference, characterized in that - over the circumference of the arm structure (8) - the number of recesses (13) in at least one leg (8a, 8b) is n times the number of the burners (2, 3), with n = 0.5 or 1.0 or 1.5 or 2.0 or 2.5 or 3.0.
  3. Suspension of a gas turbine annular combustor according to Claim 1 with pilot burners (2) and main burners (3) evenly distributed around the combustor circumference and offset relative to each other,
    characterized in that a recess (13) is provided in the sectional plane (15) of each burner (2,3) in at last one of the legs (8a, 8b).
EP98117869A 1997-10-16 1998-09-21 Suspension for an annular gas turbine combustor Expired - Lifetime EP0909924B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19745683 1997-10-16
DE19745683A DE19745683A1 (en) 1997-10-16 1997-10-16 Suspension of an annular gas turbine combustion chamber

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EP0909924A2 EP0909924A2 (en) 1999-04-21
EP0909924A3 EP0909924A3 (en) 2000-08-02
EP0909924B1 true EP0909924B1 (en) 2003-07-16

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EP (1) EP0909924B1 (en)
DE (2) DE19745683A1 (en)

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FR2825781B1 (en) 2001-06-06 2004-02-06 Snecma Moteurs ELASTIC MOUNTING OF THIS COMBUSTION CMC OF TURBOMACHINE IN A METAL HOUSING
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FR2829228B1 (en) * 2001-08-28 2005-07-15 Snecma Moteurs ANNULAR COMBUSTION CHAMBER WITH DOUBLE HEADED HEAD
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US7909570B2 (en) * 2006-08-25 2011-03-22 Pratt & Whitney Canada Corp. Interturbine duct with integrated baffle and seal
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EP0909924A2 (en) 1999-04-21
DE59809015D1 (en) 2003-08-21
DE19745683A1 (en) 1999-04-22
US6131384A (en) 2000-10-17
EP0909924A3 (en) 2000-08-02

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