EP1960636B1 - Turbomachine - Google Patents
Turbomachine Download PDFInfo
- Publication number
- EP1960636B1 EP1960636B1 EP06829956.9A EP06829956A EP1960636B1 EP 1960636 B1 EP1960636 B1 EP 1960636B1 EP 06829956 A EP06829956 A EP 06829956A EP 1960636 B1 EP1960636 B1 EP 1960636B1
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- EP
- European Patent Office
- Prior art keywords
- insert
- seal
- gap
- turbine
- combustion chamber
- 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.)
- Not-in-force
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
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- 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 present invention relates to a turbomachine, in particular a gas turbine, having the features of the preamble of claim 1.
- a lining element for example an inner liner
- a membrane sealing groove for a membrane seal is formed on the carrier element.
- the support element is surrounded during operation of the turbomachine, for example, with a compressor end temperature and thus does not set very high demands on the oxidation resistance of the material. It is therefore usually sufficient if the support elements are made, for example, of Stg50T, Stg41T, St530TS or GGG40. In order to be able to further reduce a cooling air portion of a turbine platform in such turbomachines, this is made as short as possible, which, however, increases the static pressure before the leading edge of the turbine blade and causes a so-called bow wave effect by the aerodynamic resistance of a turbine blade.
- a turbomachine which has at least one combustion chamber and at least one turbine downstream thereto, wherein at least one support element and an associated therewith, designed as a heat protection lining element are provided. Between the at least one combustion chamber and the turbine downstream there is a gap sealed by means of a seal in which a replaceable insert is arranged on the end face on the carrier element, which protects at least the carrier element from hot gases.
- the invention is based on the general idea, in a turbomachine in a gap sealed by a seal between a combustion chamber and a turbine located downstream thereof, to arrange a replaceable insert on the end face on a carrier element of the combustion chamber, which reliably protects the carrier element from hot gases and thus oxidation.
- a replaceable insert on the end face on a carrier element of the combustion chamber, which reliably protects the carrier element from hot gases and thus oxidation.
- the exchangeable insert made of a material which is more resistant to oxidation is now designed as the carrier element itself or is coated with such a material.
- the use effectively prevents unwanted oxidation of the carrier element and, for example, must be replaced or maintained only in a maintenance interval corresponding to the lining element with the same properties as the heat-resistant lining element.
- this makes it possible to form the carrier element of a more favorable for the construction, for example, firmer, material and perform cheaper. It is therefore not necessary to produce the carrier element of a likewise oxidation-resistant material, resulting in significant savings.
- replaceable insert can be formed according to an advantageous embodiment of several circular segments or two semicircular rings, it is also possible to replace only individual insert segments as needed, which also maintenance costs and maintenance costs can be reduced,
- the replaceable insert is arranged in the gap between a first combustion chamber and a turbine located downstream thereof, and / or in the gap between a second combustion chamber and a low-pressure turbine located downstream thereof.
- the insert carries the seal and / or the seal is designed as a membrane seal.
- the seal can be easily removed by loosening the insert in the axial direction of the end face of the support element and just as easily be attached to it.
- an exchange of the entire support element is unnecessary, which on the one hand reduces the downtime of the turbomachine and on the other hand reduces costs.
- the seal is formed from a plurality of circular segments or from two semicircular rings, wherein the two semicircular rings overlap in the circumferential direction. This also allows the replacement of individual sealing segments or individual sealing semi-circular rings, whereby an individual and needs-based maintenance of the turbomachine can be achieved. At the same time, the segmentation of the gasket achieves better handling of the gasket, in particular during maintenance, which simplifies maintenance work and can thus reduce maintenance costs.
- each circle segment and / or each semicircular ring of the seal is fixed to at least one point on the insert. Due to the high temperatures, in particular caused by a hot gas break in the gap, there are significant deformations, which must be absorbed by the seal without damage.
- each of the segments or each of the half rings is, on the one hand, fixed, but, on the other hand, permits unhindered temperature expansion both in the radial and in the circumferential direction.
- Fig. 1 has a turbomachine 1 according to the invention, for example a gas turbine, at least one combustion chamber 2 and at least one turbine 3 located downstream of the combustion chamber 2.
- the flow direction is according to Fig. 1 denoted by the reference numeral 4.
- a gap 5 is formed, which via a seal 6 (see. Fig. 2 and 4 ) is sealed.
- the turbomachine 1 has at least one carrier element 7 and a lining element 8 connected thereto and designed as heat protection.
- the goal is to create a short turbine platform as possible. Due to the aerodynamic resistance of a blade 9, however, the static pressure increases in front of an inlet edge into the turbine blade 9, resulting in a so-called bow wave effect. As a result of the high static pressure in the region of a blade leading edge, hot gas penetration in the gap 5 between the combustion chamber 2 and the turbine 3 can thus occur.
- the acted upon with hot gas parts, such as the lining element 8, are preferably made of nickel-based alloys and therefore sufficiently protected even without a separate heat protection coating.
- an exchangeable insert 10 is arranged on the end side on the carrier element 7 in the gap 5 (cf. Fig. 1 to 4 ).
- the replaceable insert 10 is formed of an oxidation-resistant material, which in particular has a higher oxidation resistance than the material used for the carrier element 7.
- a welcome side effect of the short turbines 3 is also a reduced proportion of cooling air, whereby the efficiency of the turbine 3 can be increased.
- the exchangeable insert 10 is formed either from a plurality of circular segments or from two semicircular rings, wherein in particular the circular segments allow improved handling due to their low weight.
- this offers the advantage to renew individual circle segments of the insert 10 as needed, whereby a total of maintenance and thus maintenance costs can be saved.
- the end 10 arranged on the support element 7 insert 10 completely covers an end face of the carrier element 7, so that it is fully protected from entering into the gap 5 hot gases.
- An attachment of the insert 10 on the carrier element 7 takes place for example via a carrier element-side undercut 11 (see. Fig. 4 ), in which the replaceable insert 10 engages and / or via at least one fastening means 12 (see. Fig. 2 to 4 ), for example a screw. This ensures easy solubility and thus a quick replacement of the insert 10 and the seal 6 during maintenance.
- the replaceable insert 10 is preferably provided with a wear-resistant and temperature-resistant coating or formed entirely of a wear-resistant and temperature-resistant material.
- a wear-resistant and temperature-resistant coating or formed entirely of a wear-resistant and temperature-resistant material.
- An oxidation-resistant wear protection layer may, for example in the form of a Chromium carbide coating can be realized.
- Such a chromium carbide coating offers the advantage that the insert 11 per se can be formed from a material similar to the carrier element 7, whereby both the insert 10 and the carrier element 7 have a nearly identical thermal behavior, which is particularly favorable to gaps between individual Keep segments as small as possible.
- the choice of material so that in particular material pairings are used which, on the one hand, have a wear and oxidation-minimized behavior and, on the other hand, behave thermally similarly to the carrier element 7.
- Fig. 3 shows a longitudinal section in the region of a gap 5 between a first combustion chamber and a high-pressure turbine.
- the replaceable insert 10 is fastened to an outer support element 7 'by means of a fastening means 12.
- the insert 10 engages in an undercut 11 formed on the outer carrier element 7 'and rests against an outer lining element 8' on its side 16 facing away from the gap.
- the replaceable insert 10 adjoins a turbine blade carrier 18 with another side 17.
- the insert 10 closes the gap 5 according to Fig. 3 in such a way that any hot gas which may penetrate from the outside can not reach the outer carrier element 7 'and / or the turbine blade carrier 18 and thereby protect it from oxidation.
- the insert 10 is also in a gap 5 between a second combustion chamber and a low-pressure turbine located downstream thereof (see. Fig. 4 ) can be used.
- the seal 6 is arranged in an axially open stage 13 on the insert 10, wherein the seal 6 is held in the stage 13 via detachable holding elements 14 axially.
- the insert 10 thus carries the seal 6, which for example, is designed as a membrane seal.
- the seal 6 may have a plurality of circle segments or two semicircular rings which overlap in the circumferential direction.
- the holding member 14 is in each case braced by the attachment means 12 against the insert 10 and the support member 7 and thereby prevent axial displacement of the seal 6.
- each holding member 14 is arranged in each case in a recess 19 (see. Fig. 2 ), which at least reduces a thickness of the insert 10 in the flow direction 4. Through the recess 19, the position of each received therein holding member 14 is predetermined, whereby the assembly of the holding elements 14 is simplified.
- each circular segment and / or each semicircular ring of the seal 6 is fix at at least one point on the insert 10.
- these are therefore preferably fixed at 12 o'clock and at 6 o'clock at one point on the carrier element 7.
- the seal 6 is fixed in the circumferential direction via a fixing pin 15, whereas a radial clearance is possible in order to be able to absorb thermal expansions without damage.
- the solution according to the invention provides an easily exchangeable and thus cost-effective oxidation protection for a face 5 located in a gap 5 of the carrier element, resulting on the one hand lower maintenance costs and downtime of the turbomachine 1 and on the other hand, a cooling air flow, with which the gap 5 is flushed reduced can be, which has a favorable effect on the efficiency of the turbomachine 1.
- the insert 10 is optionally formed entirely of an oxidation-resistant and temperature-resistant material or has an oxidation-resistant and temperature-resistant coating, while a core of the insert 10 from the same material as the support member 7, 7 'is formed and thereby a nearly identical temperature behavior between insert 10 and support element 7, 7' can be achieved, which has a favorable effect on any expected gap widths.
- the insert 10 carries the seal 6, which may be formed for example as a membrane seal. Due to the circular segment-like or semicircular design of the insert 10 and the seal 6, a particularly favorable handling of both the seal 6 and the insert 10 is given, which can reduce the maintenance and thus the maintenance costs. In addition, this allows only those parts to be replaced, which must be replaced due to the oxidation or erosion, while other not so badly damaged sealing segments or insert segments can remain on the carrier element 7. A complete replacement of the support member 7, as he was required earlier, for example, and the associated long downtime and high maintenance or replacement costs can be effectively avoided. At the same time, the cooling air flow for cooling the gap 5 can be reduced, which increases the efficiency of the turbomachine 1.
Description
Die vorliegende Erfindung betrifft eine Strömungsmaschine, insbesondere eine Gasturbine, mit den Merkmalen des Oberbegriffs des Anspruchs 1.The present invention relates to a turbomachine, in particular a gas turbine, having the features of the preamble of
Bei herkömmlichen Strömungsmaschinen werden ein Auskleidungselement, beispielsweise ein Innenliner, an einem Trägerelement befestigt sowie eine Membrandichtungsnut für eine Membrandichtung am Trägerelement ausgebildet. Das Trägerelement ist im Betrieb der Strömungsmaschine beispielsweise mit einer Kompressor-endtemperatur umgeben und stellt somit keine ausgesprochen hohen Anforderungen an die Oxidationsbeständigkeit des Materials. Es ist somit zumeist ausreichend, wenn die Trägerelemente beispielsweise aus Stg50T, Stg41T, St530TS oder aus GGG40 gefertigt werden. Um bei derartigen Strömungsmaschinen des weiteren einen Kühlluftanteil einer Turbinenplattform reduzieren zu können, wird diese so kurz als möglich ausgeführt, wodurch sich jedoch durch den aerodynamischen Widerstand einer Turbinenschaufel der statische Druck vor der Eintrittskante der Turbinenschaufel erhöht und einen sogenannten Bugwelleneffekt bewirkt. In Folge des höheren statischen Druckes im Bereich der Schaufeleintrittskante kann es wiederum zum Heißgaseinbruch im Spalt zwischen einer Brennkammer und der Turbinenplattform kommen. Die mit Heißgas beaufschlagten Teile, wie beispielsweise der Innenliner oder die Membrandichtung, sind üblicherweise aus einer Nickel-Basislegierung gefertigt und sind somit auch ohne Wärmeschutzbeschichtung ausreichend geschützt. Die Trägerelemente hingegen oxidieren jedoch aufgrund der durch den Heißgaseinbruch erzeugten hohen Temperaturen relativ stark. Um dies zu vermeiden, wird auf die Trägerelemente üblicherweise eine Schutzschicht, beispielsweise eine InconeI625-Schicht, aufgeschweißt, welche jedoch aufwändig herzustellen ist und hohe Kosten verursacht. Zusätzlich wird der Spalt über die plattformseitige Membrandichtung mit Kühlluft gespült. Trotz dieser Schutzmaßnahmen kommt es jedoch im Bereich einer axialen Stirnseite im Spalt zu einem abrassiven Verschleiß am Trägerelement, was im schlimmsten Fall zu einer erhöhten Leckage bis hin zu einer Desintegration der Dichtungsmembran führen kann.In conventional turbomachines, a lining element, for example an inner liner, is fastened to a carrier element and a membrane sealing groove for a membrane seal is formed on the carrier element. The support element is surrounded during operation of the turbomachine, for example, with a compressor end temperature and thus does not set very high demands on the oxidation resistance of the material. It is therefore usually sufficient if the support elements are made, for example, of Stg50T, Stg41T, St530TS or GGG40. In order to be able to further reduce a cooling air portion of a turbine platform in such turbomachines, this is made as short as possible, which, however, increases the static pressure before the leading edge of the turbine blade and causes a so-called bow wave effect by the aerodynamic resistance of a turbine blade. As a result of the higher static pressure in the region of the blade leading edge, hot gas penetration in the gap between a combustion chamber and the turbine platform can again occur. The acted upon with hot gas parts, such as the inner liner or the membrane seal, are usually made of a nickel-based alloy and are therefore sufficiently protected even without heat protection coating. The support elements, however, oxidize relatively strong due to the high temperatures generated by the hot gas collapse. To avoid this, is on the Carrier elements usually a protective layer, such as an InconeI625 layer, welded, which, however, is complicated to manufacture and high costs. In addition, the gap is flushed with cooling air via the platform-side diaphragm seal. Despite these protective measures, however, abrasive wear on the carrier element occurs in the region of an axial end face in the gap, which in the worst case can lead to increased leakage up to disintegration of the sealing membrane.
Aus der
Weitere Strömungsmaschinen sind aus der
Es ist Aufgabe der vorliegenden Erfindung, eine verbesserte Strömungsmaschine bereitzustellen, bei welcher einerseits die Trägerelemente wirkungsvoll vor einer Oxidation geschützt sind und andererseits die Wartungsfreundlichkeit der Strömungsmaschine, z.B. durch längere Wartungsintervalle, deutlich verbessert ist.It is an object of the present invention to provide an improved turbomachine in which, on the one hand, the support elements are effectively protected against oxidation and, on the other hand, the ease of maintenance of the turbomachine, e.g. due to longer maintenance intervals, is significantly improved.
Dieses Problem wird durch den unabhängigen Anspruch gelöst. Bevorzugte Ausführungsformen sind in den abhängigen Ansprüchen gezeigt.This problem is solved by the independent claim. Preferred embodiments are shown in the dependent claims.
Die Erfindung beruht auf dem allgemeinen Gedanken, bei einer Strömungsmaschine in einem mittels einer Dichtung abgedichteten Spalt zwischen einer Brennkammer und einer dazu stromab gelegenen Turbine, stirnseitig an einem Trägerelement der Brennkammer einen austauschbaren Einsatz anzuordnen, welcher das Trägerelement zuverlässig vor Heißgasen und damit einem Oxidieren schützt. Durch die erfindungsgemäße Lösung kann ein frühzeitiges Oxidieren des Trägerelementes vermieden werden und gleichzeitig ist der Einsatz so ausgebildet, dass er einfach und schnell, das heißt ohne große Stillstandszeiten der Strömungsmaschine und ohne große Kosten auszuwechseln ist. Der Einsatz ist dabei so an der Stirnseite des Trägerelementes im Spalt angeordnet; dass er die komplette dem Spalt zugewandte Stirnseite des Trägerelementes überdeckt. Der Einsatz ist darüber hinaus lösbar am Trägerelement angeordnet und dadurch bei Bedarf leicht auszutauschen.The invention is based on the general idea, in a turbomachine in a gap sealed by a seal between a combustion chamber and a turbine located downstream thereof, to arrange a replaceable insert on the end face on a carrier element of the combustion chamber, which reliably protects the carrier element from hot gases and thus oxidation. By the solution according to the invention, an early oxidation of the carrier element can be avoided and at the same time the insert is designed so that it is simple and fast, that is to replace without major downtime of the turbomachine and at no great cost. The insert is arranged on the front side of the carrier element in the gap; that it covers the entire end face of the carrier element facing the gap. The insert is also releasably arranged on the support element and thereby easily replaced if necessary.
Erfindungsgemäß ist nun der austauschbare Einsatz aus einem oxidationsbeständigeren Material ausgebildet als das Trägerelement selbst oder er ist mit einem derartigen Material beschichtet. Somit verhindert der Einsatz wirkungsvoll eine unerwünschte Oxidation des Trägerelementes und muss beispielsweise bei gleicher Beschaffenheit wie das hitzebeständige Auskleidungselement nur in einem dem Auskleidungselement entsprechenden Wartungsintervall ersetzt beziehungsweise gewartet werden. Gleichzeitig ist es dadurch möglich, das Trägerelement aus einem für die Konstruktion günstigeren, beispielsweise festeren, Werkstoff auszubilden und kostengünstiger auszuführen. Es ist also nicht erforderlich, das Trägerelement aus einem ebenfalls oxidationsbeständigen Material herzustellen, wodurch sich bedeutsame Einspareffekte ergeben. Gleichzeitig kann auf eine stirnseitige temperatur-und/oder verschleißbeständige Beschichtung des Trägerelementes verzichtet werden, welche zum einen schwierig aufzubringen ist und zum anderen insbesondere im Wartungsfall aufwändig zu ersetzen ist.According to the invention, the exchangeable insert made of a material which is more resistant to oxidation is now designed as the carrier element itself or is coated with such a material. Thus, the use effectively prevents unwanted oxidation of the carrier element and, for example, must be replaced or maintained only in a maintenance interval corresponding to the lining element with the same properties as the heat-resistant lining element. At the same time, this makes it possible to form the carrier element of a more favorable for the construction, for example, firmer, material and perform cheaper. It is therefore not necessary to produce the carrier element of a likewise oxidation-resistant material, resulting in significant savings. At the same time can be dispensed with an end-side temperature and / or wear-resistant coating of the support element, which is difficult to apply for one and on the other hand, in particular consuming to replace consuming.
Durch den Umstand, dass der austauschbare Einsatz entsprechend einer vorteilhaften Ausführungsform aus mehreren Kreissegmenten oder aus zwei Halbkreisringen gebildet sein kann, ist es auch möglich, lediglich einzelne Einsatzsegmente bei Bedarf auszuwechseln, wodurch ebenfalls Wartungskosten und Wartungsaufwand reduziert werden können,Due to the fact that the replaceable insert can be formed according to an advantageous embodiment of several circular segments or two semicircular rings, it is also possible to replace only individual insert segments as needed, which also maintenance costs and maintenance costs can be reduced,
Bei einer weiteren vorteilhaften Ausführungsform ist der austauschbare Einsatz im Spalt zwischen einer ersten Brennkammer und einer dazu stromab gelegenen Turbine, und/oder im Spalt zwischen einer zweiten Brennkammer und einer dazu stromab gelegenen Niederdruckturbine angeordnet. Dies macht deutlich, dass die erfindungsgemäße Lösung zum Schutz der Trägerelemente vor einem Heißgaseinbruch und damit vor einer vorzeitigen Oxidation vielfältig anwendbar ist und in vielerlei Strömungsmaschinen einsetzbar ist. Insbesondere soll dadurch herausgestellt werden, dass der erfindungsgemäße, austauschbare Einsatz in unterschiedlichen Spalten einer Strömungsmaschine zum Einsatz gelangt, insbesondere da, wo es gilt, oxidationsgefährdete Bauelemente wirkungsvoll zu schützen. Selbstverständlich kann ein derartiger Einsatz auch auf einer Innen- und/oder auf einer Außenseite einer Ringbrennkammer zum Einsatz kommen.In a further advantageous embodiment, the replaceable insert is arranged in the gap between a first combustion chamber and a turbine located downstream thereof, and / or in the gap between a second combustion chamber and a low-pressure turbine located downstream thereof. This makes it clear that the solution according to the invention for the protection of the carrier elements before a hot gas intrusion and thus against premature oxidation is widely applicable and can be used in many turbomachines. In particular, it should be emphasized that the inventive, replaceable insert is used in different columns of a turbomachine, especially where it is necessary to protect oxidation-endangered components effectively. Of course, such an insert can also be used on an inner and / or on an outer side of an annular combustion chamber.
Zweckmäßig trägt der Einsatz die Dichtung und/oder ist die Dichtung als Membrandichtung ausgebildet. Bei einem Verschleiß der Dichtung, welche bei einer herkömmlichen Bauweise oftmals fest am Trägerelement angeordnet war, musste bisher das komplette Trägerelement ausgetauscht werden, was lange Stillstandszeiten und damit hohe Kosten verursachte. Durch die erfindungsgemäße Lösung kann die Dichtung durch Lösen des Einsatzes einfach in axialer Richtung von der Stirnseite des Trägerelementes abgenommen werden und ebenso einfach wieder daran befestigt werden. Somit ist ein Austausch des gesamten Trägerelementes entbehrlich, was zum einen die Stillstandszeiten der Strömungsmaschine reduziert und zum anderen die Kosten senkt.Suitably, the insert carries the seal and / or the seal is designed as a membrane seal. In a wear of the seal, which was often arranged in a conventional design fixed to the carrier element, previously had the entire support member to be replaced, which caused long downtime and thus high costs. The solution according to the invention, the seal can be easily removed by loosening the insert in the axial direction of the end face of the support element and just as easily be attached to it. Thus, an exchange of the entire support element is unnecessary, which on the one hand reduces the downtime of the turbomachine and on the other hand reduces costs.
Bei einer weiteren bevorzugten Ausführungsform ist die Dichtung aus mehreren Kreissegmenten oder aus zwei Halbkreisringen gebildet, wobei sich die beiden Halbkreisringe in Umfangsrichtung überlappen. Dies ermöglicht auch den Austausch einzelner Dichtungssegmente beziehungsweise einzelner Dichtungs-Halbkreisringe, wodurch eine individuelle und bedarfsgerechte Wartung der Strömungsmaschine erreicht werden kann. Gleichzeitig wird durch die Segmentierung der Dichtung ein besseres Handling derselben, insbesondere bei der Wartung, erreicht, wodurch sich die Wartungstätigkeit vereinfacht und dadurch Wartungskosten gesenkt werden können.In a further preferred embodiment, the seal is formed from a plurality of circular segments or from two semicircular rings, wherein the two semicircular rings overlap in the circumferential direction. This also allows the replacement of individual sealing segments or individual sealing semi-circular rings, whereby an individual and needs-based maintenance of the turbomachine can be achieved. At the same time, the segmentation of the gasket achieves better handling of the gasket, in particular during maintenance, which simplifies maintenance work and can thus reduce maintenance costs.
Zweckmäßig ist jedes Kreissegment und/oder jeder Halbkreisring der Dichtung an zumindest einem Punkt an dem Einsatz festgelegt. Durch die hohen Temperaturen, insbesondere hervorgerufen durch einen Heißgaseinbruch in dem Spalt, kommt es zu erheblichen Verformungen, welche von der Dichtung schadensfrei aufgenommen werden müssen. Durch eine punktuelle Festlegung der Dichtungssegmente beziehungsweise Dichtungs-Halbkreisringe ist zum einen jedes der Segmente beziehungsweise jeder der Halbringe einerseits fixiert, erlaubt andererseits aber eine unbehinderte Temperaturausdehnung sowohl in radialer als auch in Umfangsrichtung.Suitably, each circle segment and / or each semicircular ring of the seal is fixed to at least one point on the insert. Due to the high temperatures, in particular caused by a hot gas break in the gap, there are significant deformations, which must be absorbed by the seal without damage. By a selective fixing of the sealing segments or sealing semi-circular rings, on the one hand, each of the segments or each of the half rings is, on the one hand, fixed, but, on the other hand, permits unhindered temperature expansion both in the radial and in the circumferential direction.
Weitere wichtige Merkmale und Vorteile der erfindungsgemäßen Strömungsmaschine ergeben sich aus den Unteransprüchen, aus den Zeichnungen und aus der zugehörigen Figurenbeschreibung anhand der Zeichnungen.Other important features and advantages of the turbomachine according to the invention will become apparent from the subclaims, from the drawings and from the associated description of the figures with reference to the drawings.
Bevorzugte Ausführungsformen der Erfindung werden in den Zeichnungen dargestellt und werden in der folgenden Beschreibung näher erläutert Auf Merkmale, die im Wesentlichen oder funktionell gleich oder ähnlich sind, wird mit dem (den) gleichen Bezugszeichen Bezug genommen.Preferred embodiments of the invention are illustrated in the drawings and will be described in more detail in the following description. Features substantially or functionally identical or similar are referred to by the same reference numeral.
Dabei zeigen, jeweils schematisch
- Fig. 1
- einen Längsschnitt durch eine Turbineneingangsseite im Bereich eines Spaltes,
- Fig. 2
- eine vergrößerte perspektivische Darstellung des Bereiches A aus
Fig. 1 , - Fig. 3
- einen Längsschnitt im Bereich eines Spaltes zwischen einer ersten Brennkammer und einer stromab gelegenen Hochdruckturbine mit einem austauschbaren Einsatz,
- Fig. 4
- einen Längsschnitt durch die Strömungsmaschine im Bereich eines Spaltes zwischen einer zweiten Brennkammer und einer dazu stromab gelegenen Niederdruckturbine mit dem erfindungsgemäßen Einsatz.
- Fig. 1
- a longitudinal section through a turbine inlet side in the region of a gap,
- Fig. 2
- an enlarged perspective view of the area A from
Fig. 1 . - Fig. 3
- a longitudinal section in the region of a gap between a first combustion chamber and a downstream high-pressure turbine with a replaceable insert,
- Fig. 4
- a longitudinal section through the turbomachine in the region of a gap between a second combustion chamber and a low-pressure turbine downstream thereto with the insert according to the invention.
Entsprechend
Um Fertigungsvorteile und Vorteile bezüglich der Betriebsfestigkeit erreichen zu können, ist es das Ziel, eine möglichst kurz bauende Turbinenplattform zu schaffen. Durch den aerodynamischen Widerstand einer Schaufel 9 erhöht sich jedoch der statische Druck vor einer Eintrittskante in die Turbinenschaufel 9, woraus ein sogenannter Bugwelleneffekt resultiert. Infolge des hohen statischen Drucks im Bereich einer Schaufeleintrittskante kann es somit zu einem Heißgaseinbruch im Spalt 5 zwischen der Brennkammer 2 und der Turbine 3 kommen. Die mit Heißgas beaufschlagten Teile, wie beispielsweise das Auskleidungselement 8, sind vorzugsweise aus Nickel-Basislegierungen gefertigt und daher auch ohne gesonderte Wärmeschutzbeschichtung ausreichend geschützt. Die Trägerelemente 7 hingegen oxidieren jedoch aufgrund einer zu hohen Temperatur sehr stark. Um einen direkten Kontakt der Heißgase mit dem Trägerelement 7 im Spalt 5 zu verhindern und dadurch eine Oxidationsneigung zu verringern, ist stirnseitig am Trägerelement 7 im Spalt 5 ein austauschbarer Einsatz 10 angeordnet (vgl.
Um einen möglichst hohen Widerstand gegen Oxidation beziehungsweise Temperatur zu erreichen, ist der austauschbare Einsatz 10 vorzugsweise mit einer verschleißresistenten und temperaturbeständigen Beschichtung versehen oder gänzlich aus einem verschleißresistenten und temperaturbeständigen Material ausgebildet. Bei einem Verschleiß beziehungsweise einer Oxidation des Einsatzes 10 können so die "handlichen" Segmente einfach ausgetauscht werden. Darüber hinaus ist es möglich, durch die höheren verträglichen Temperaturen der Werkstoffe im Spalt 5 den Kühlluftanteil, welcher zum Spülen des Spaltes 5 verwendet wird, zu reduzieren und dadurch den Wirkungsgrad der Turbine 3 beziehungsweise der Strömungsmaschine 1 zu erhöhen. Eine oxidationsresistente Verschleißschutzschicht kann beispielsweise in Form einer Chromcarbidbeschichtung realisiert werden. Eine derartige Chromcarbidbeschichtung bietet den Vorteil, dass der Einsatz 11 an sich aus einem dem Trägerelement 7 ähnlichen Material ausgebildet sein kann, wodurch sowohl der Einsatz 10 als auch das Trägerelement 7 ein nahezu identisches thermisches Verhalten aufweisen, was insbesondere günstig ist, um Spalte zwischen einzelnen Segmenten so klein wie möglich zu halten. Generell ist hierbei einer Werkstoffauswahl keine Grenze gesetzt, so dass insbesondere Materialpaarungen zum Einsatz kommen, welche einerseits ein verschleiß- und oxidationsminimiertes Verhalten aufweisen und andererseits sich thermisch ähnlich verhalten wie das Trägerelement 7.In order to achieve the highest possible resistance to oxidation or temperature, the
Wie in
In Umfangsrichtung ist vorgesehen, jedes Kreissegment und/oder jeden Halbkreisring der Dichtung 6 an zumindest einem Punkt an dem Einsatz 10 festzulegen. Bei der Verwendung zweier als Halbkreisringe ausgebildeter Dichtungsmembranen sind diese daher vorzugsweise bei 12 Uhr und bei 6 Uhr jeweils an einem Punkt am Trägerelement 7 festgelegt. Im jeweiligen Fixierpunkt ist die Dichtung 6 über einen Fixierstift 15 in Umfangsrichtung fixiert, wogegen ein radiales Spiel möglich ist, um Temperaturausdehnungen schadlos aufnehmen zu können.In the circumferential direction, it is provided to fix each circular segment and / or each semicircular ring of the
Durch die erfindungsgemäße Lösung wird ein leicht auszutauschender und dadurch kostengünstiger Oxidationsschutz für eine in einem Spalt 5 gelegene Stirnseite des Trägerelementes 7 geschaffen, wodurch sich einerseits geringere Wartungskosten und Stillstandszeiten der Strömungsmaschine 1 ergeben und andererseits ein Kühlluftstrom, mit welchem der Spalt 5 gespült wird, reduziert werden kann, was sich günstig auf den Wirkungsgrad der Strömungsmaschine 1 auswirkt. Dabei ist der Einsatz 10 wahlweise gänzlich aus einem oxidations-und temperaturbeständigen Material ausgebildet oder weist eine oxidationsbeständige und temperaturbeständige Beschichtung auf, während ein Kern des Einsatzes 10 aus dem gleichen Werkstoff wie das Trägerelement 7, 7' ausgebildet ist und dadurch ein nahezu identisches Temperaturverhalten zwischen Einsatz 10 und Trägerelement 7, 7' erreicht werden kann, was sich günstig auf eventuell zu erwartende Spaltweiten auswirkt. Darüber hinaus trägt der Einsatz 10 die Dichtung 6, welche beispielsweise als Membrandichtung ausgebildet sein kann. Durch die kreissegmentartige oder halbkreisringartige Ausbildung des Einsatzes 10 beziehungsweise der Dichtung 6 ist ein besonders günstiges Handling sowohl der Dichtung 6 als auch des Einsatzes 10 gegeben, wodurch sich der Wartungsaufwand und damit auch die Wartungskosten reduzieren lassen. Darüber hinaus ermöglicht dies, dass nur die Teile ausgetauscht werden, welche aufgrund der Oxidation oder Erosion ausgetauscht werden müssen, während andere nicht so stark geschädigte Dichtungssegmente beziehungsweise Einsatzsegmente am Trägerelement 7 verbleiben können. Ein völliger Austausch des Trägerelementes 7, wie er beispielsweise früher erforderlich war sowie die damit verbundenen langen Stillstandszeiten und hohen Wartungs- beziehungsweise Austauschkosten können dadurch wirkungsvoll vermieden werden. Gleichzeitig kann der Kühlluftstrom zum Kühlen des Spaltes 5 reduziert werden, was den Wirkungsgrad der Strömungsmaschine 1 erhöht.The solution according to the invention provides an easily exchangeable and thus cost-effective oxidation protection for a
- 11
- Strömungsmaschineflow machine
- 22
- Brennkammercombustion chamber
- 33
- Turbineturbine
- 44
- Strömungsrichtungflow direction
- 55
- Spaltgap
- 66
- Dichtungpoetry
- 77
- Trägerelementsupport element
- 7'7 '
- äußeres Trägerelementouter carrier element
- 88th
- Auskleidungselementlining member
- 8'8th'
- äußeres Auskleidungselementouter lining element
- 99
- Turbinenschaufelturbine blade
- 1010
- Einsatzcommitment
- 1111
- Hinterschnittundercut
- 1212
- Befestigungsmittelfastener
- 1313
-
axial offene Stufe am Einsatz 10axially open step on the
insert 10 - 1414
- Halteelementeretaining elements
- 1515
- Fixierstiftlocating pin
- 1616
-
eine dem Spalt 5 abgewandte Seite des Einsatzes 10a side facing away from the
gap 5 of the insert 10th - 1717
-
eine dem Turbinenschaufelträger 18 zugewandte Seite des Einsatzes 10a
turbine blade carrier 18 facing side of the insert 10th - 1818
- TurbinenschaufelträgerTurbine blade carrier
- 1919
- Ausnehmungrecess
Claims (8)
- Turbomachine (1), especially a gas turbine, with at least one combustion chamber (2) and at least one turbine (3) which lies downstream of it,- wherein the combustion chamber (2) has at least one support element (7), and a lining element (8) which is connected to the support element and formed as a heat shield,- wherein a gap (5), which is sealed by means of a seal (6), is formed between the at least one combustion chamber (2) and the turbine (3) which lies downstream, in which gap an exchangeable insert (10) is arranged on the end face on the support element (7), which insert bears the seal (6) and protects at least the support element (7) against hot gases,
characterized in that
the exchangeable insert (10) is formed from a material which is more oxidation-resistant than the support element (7), or is coated with such a material. - Turbomachine according to Claim 1,
characterized in that- the exchangeable insert (10) is formed from a plurality of circle segments or from two semicircular rings, and/or- the exchangeable insert (10) engages in an undercut (11) on the support element side, and/or is retained on the end face of the support element (7) via at least one fastening device (12). - Turbomachine according to either of Claims 1 or 2,
characterized in that
the exchangeable insert (10) has a wear-resistant and temperature-resistant coating. - Turbomachine according to one of Claims 1 to 3,
characterized in that- the insert (10) is arranged in the gap (5) between a first combustion chamber and a turbine (3) which lies downstream, and/or- the insert (10) is arranged in the gap (5) between a second combustion chamber and a turbine (3) which lies downstream. - Turbomachine according to one of Claims 1 to 4,
characterized in that- the insert (10) carries the seal (6), and/or- the seal (6) is formed as a membrane seal. - Turbomachine according to one of Claims 1 to 5,
characterized in that
the seal (6) has a plurality of circle segments or two semicircular rings, wherein the two semicircular rings overlap in the circumferential direction. - Turbomachine according to one of Claims 1 to 6,
characterized in that- the seal (6) is arranged in an axially open step (13) on the insert (10), and/or- the seal (6) is retained in the step (13) via detachable retaining elements (14). - Turbomachine according to one of Claims 1 to 7,
characterized in that
each circle segment and/or each semicircular ring of the seal (6) is fixed on at least one point on the insert (10).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH19772005 | 2005-12-14 | ||
PCT/EP2006/068226 WO2007068538A1 (en) | 2005-12-14 | 2006-11-08 | Turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1960636A1 EP1960636A1 (en) | 2008-08-27 |
EP1960636B1 true EP1960636B1 (en) | 2016-01-27 |
Family
ID=35929927
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06829956.9A Not-in-force EP1960636B1 (en) | 2005-12-14 | 2006-11-08 | Turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US8555655B2 (en) |
EP (1) | EP1960636B1 (en) |
ES (1) | ES2569521T3 (en) |
WO (1) | WO2007068538A1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4626714B2 (en) * | 2008-08-22 | 2011-02-09 | ダイキン工業株式会社 | Refrigeration equipment |
CH703105A1 (en) | 2010-05-05 | 2011-11-15 | Alstom Technology Ltd | Gas turbine with a secondary combustion chamber. |
US9316119B2 (en) * | 2011-09-15 | 2016-04-19 | United Technologies Corporation | Turbomachine secondary seal assembly |
US9249678B2 (en) * | 2012-06-27 | 2016-02-02 | General Electric Company | Transition duct for a gas turbine |
EP3421727B1 (en) * | 2017-06-30 | 2020-01-29 | Ansaldo Energia Switzerland AG | Gas turbine comprising a turbine vane carrier |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1259142B (en) | 1962-02-14 | 1968-01-18 | Licentia Gmbh | Ring flange of the tubular inner or outer housing of an axial gas or steam turbine |
US3224194A (en) * | 1963-06-26 | 1965-12-21 | Curtiss Wright Corp | Gas turbine engine |
US3965066A (en) * | 1974-03-15 | 1976-06-22 | General Electric Company | Combustor-turbine nozzle interconnection |
US4124737A (en) * | 1976-12-30 | 1978-11-07 | Union Carbide Corporation | High temperature wear resistant coating composition |
CH633351A5 (en) | 1978-11-09 | 1982-11-30 | Sulzer Ag | RESISTANT SEALING OF A RING COMBUSTION CHAMBER FOR A GAS TURBINE. |
US4379560A (en) * | 1981-08-13 | 1983-04-12 | Fern Engineering | Turbine seal |
US5337583A (en) | 1992-08-24 | 1994-08-16 | United Technologies Corporation | Replaceable clip |
DE4324035C2 (en) | 1993-07-17 | 2003-02-27 | Alstom | gas turbine |
US5749218A (en) * | 1993-12-17 | 1998-05-12 | General Electric Co. | Wear reduction kit for gas turbine combustors |
GB2373299B (en) * | 2001-03-12 | 2004-10-27 | Alstom Power Nv | Re-fired gas turbine engine |
FR2825783B1 (en) * | 2001-06-06 | 2003-11-07 | Snecma Moteurs | HANGING OF CMC COMBUSTION CHAMBER OF TURBOMACHINE BY BRAZED LEGS |
JP3600912B2 (en) * | 2001-09-12 | 2004-12-15 | 川崎重工業株式会社 | Combustor liner seal structure |
US6834507B2 (en) * | 2002-08-15 | 2004-12-28 | Power Systems Mfg., Llc | Convoluted seal with enhanced wear capability |
US7093440B2 (en) * | 2003-06-11 | 2006-08-22 | General Electric Company | Floating liner combustor |
US7527469B2 (en) * | 2004-12-10 | 2009-05-05 | Siemens Energy, Inc. | Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine |
-
2006
- 2006-11-08 ES ES06829956.9T patent/ES2569521T3/en active Active
- 2006-11-08 EP EP06829956.9A patent/EP1960636B1/en not_active Not-in-force
- 2006-11-08 WO PCT/EP2006/068226 patent/WO2007068538A1/en active Application Filing
-
2008
- 2008-06-16 US US12/140,094 patent/US8555655B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
ES2569521T3 (en) | 2016-05-11 |
US8555655B2 (en) | 2013-10-15 |
US20090071167A1 (en) | 2009-03-19 |
EP1960636A1 (en) | 2008-08-27 |
WO2007068538A1 (en) | 2007-06-21 |
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