EP1960636A1 - Turbomachine - Google Patents

Turbomachine

Info

Publication number
EP1960636A1
EP1960636A1 EP06829956A EP06829956A EP1960636A1 EP 1960636 A1 EP1960636 A1 EP 1960636A1 EP 06829956 A EP06829956 A EP 06829956A EP 06829956 A EP06829956 A EP 06829956A EP 1960636 A1 EP1960636 A1 EP 1960636A1
Authority
EP
European Patent Office
Prior art keywords
insert
seal
turbine
carrier element
gap
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP06829956A
Other languages
German (de)
French (fr)
Other versions
EP1960636B1 (en
Inventor
Urs Benz
Jonas Hurter
Thorsten Motzkus
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1960636A1 publication Critical patent/EP1960636A1/en
Application granted granted Critical
Publication of EP1960636B1 publication Critical patent/EP1960636B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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, with at least one combustion chamber and at least one turbine located downstream thereof.
  • a lining element for example an inner liner
  • a membrane sealing groove for a membrane seal is formed on the carrier element.
  • the carrier element is surrounded during operation of the turbomachine, for example with a Kompressorendtemperatur and thus does not have very high demands on the oxidation resistance of the material. It is therefore usually sufficient if the support elements are made for example of Stg ⁇ OT, Stg41T, St530TS or GGG40.
  • a protective layer for example an Inconel625 layer, is usually welded onto the carrier elements, which, however, is expensive to produce and causes high costs.
  • the gap is flushed with cooling air via the platform-side diaphragm seal.
  • the invention is based on the general idea, in a turbomachine in a gap between a combustion chamber and a turbine located downstream thereto, to arrange a replaceable insert on the end face of a carrier element, which reliably protects the carrier element from hot gases and thus oxidation.
  • a replaceable insert on the end face of a carrier element, which reliably protects the carrier element from hot gases and thus oxidation.
  • the replaceable insert of an oxidation-resistant, especially a more oxidation-resistant material is formed as the carrier element itself.
  • the use effectively prevents unwanted oxidation of the support element and must, for example, in the same condition as the heat-resistant lining element only in one of the lining element appropriate maintenance interval replaced or maintained.
  • 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.
  • the replaceable insert can be formed from a plurality of circular segments or from two semicircular rings, it is also possible to replace only individual insert segments as needed, which also allows maintenance costs and maintenance costs to 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.
  • 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 half-circle rings, whereby an individual and needs-based maintenance of the turbomachine can be achieved.
  • 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. 2 is an enlarged perspective view of the area A of FIG. 1,
  • FIG. 3 shows a longitudinal section in the region of a gap between a first combustion chamber and a downstream high-pressure turbine with an insert according to the invention
  • Gap between a second combustion chamber and a downstream low-pressure turbine with the insert according to the invention Gap between a second combustion chamber and a downstream low-pressure turbine with the insert according to the invention.
  • a turbomachine 1 for example a gas turbine, has at least one combustion chamber 2 and at least one turbine 3 located downstream of the combustion chamber 2.
  • the Flow direction is indicated in FIG. 1 by the reference numeral 4.
  • a gap 5 is formed, which is sealed by a seal 6 (compare FIGS. 2 to 4).
  • the turbine 3 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 front side of the carrier element 7 in the gap 5 (cf., FIGS. 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 shorter 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 completely protected from collapsing 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 (compare Fig. 4) in which the replaceable insert 10 engages and / or via at least one attachment 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 / or temperature-resistant coating or formed entirely of a wear-resistant and / or temperature-resistant material.
  • a wear-resistant and / or temperature-resistant coating or formed entirely of a wear-resistant and / or temperature-resistant material.
  • the "handy" segments can thus be easily exchanged,
  • the higher compatible temperatures of the materials in the gap 5 make it possible to reduce the proportion of cooling air used to rinse the gap 5 and thereby to increase the efficiency of the turbine 3 or of the turbomachine 1.
  • An oxidation-resistant wear-resistant layer may, for example, take 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 T by means of a fastening means 12.
  • the insert 10 engages in an undercut 11 formed on the outer support element T and lies 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 off the gap 5 according to FIG. 3 in such a way that a hot gas which may penetrate from the outside can not reach the outer carrier element T and / or the turbine blade carrier 18 and thereby protect it from oxidation.
  • the insert 10 according to the invention can also be used in a gap 5 between a second combustion chamber and a low-pressure turbine located downstream thereof (compare FIG.
  • the seal 6 is arranged in an axially open stage 13 on the insert 10, wherein the seal 6 is held by releasable holding elements 14 axially in the stage 13.
  • 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 element 14 is in each case braced by the fastening means 12 against the insert 10 or the support member 7 and thereby prevent axial displacement of the seal 6.
  • each holding element 14 is arranged in each case in a recess 19 (see Fig. 2), the one Thickness of the insert 10 in the flow direction 4 at least reduced. 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 can optionally be made entirely of an oxidation-resistant and temperature-resistant material or have an oxidation-resistant and temperature-resistant coating, while a core of the insert 10 from the same material as the support member 7, T is formed and thereby a nearly identical temperature behavior between insert 10 and support member 7, T 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a turbomachine (1), in particular a gas turbine having at least one combustion chamber (2) and at least one turbine (3) which lies downstream thereof. Here, the turbine (3) has at least one carrier element (7) and a lining element (8) which is connected to it and is configured as a heat shield. 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 (5) a replaceable insert (10) which protects at least the carrier element (7) against hot gases which break into the gap (5) and associated oxidation is arranged on the end side of the carrier element (7). If required, the insert (10) or the seal (6) can be replaced simply and quickly.

Description

STROMUNGSMAS CHINE POWER MASK CHINE
Technisches GebietTechnical area
Die vorliegende Erfindung betrifft eine Strömungsmaschine, insbesondere eine Gasturbine, mit zumindest einer Brennkammer und wenigstens einer dazu stromab gelegenen Turbine.The present invention relates to a turbomachine, in particular a gas turbine, with at least one combustion chamber and at least one turbine located downstream thereof.
Stand der TechnikState of the art
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 Kompressorendtemperatur umgeben und stellt somit keine ausgesprochen hohen Anforderungen an die Oxidationsbeständigkeit des Materials. Es ist somit zumeist ausreichend, wenn die Trägerelemente beispielsweise aus StgδOT, 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 Inconel625-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 carrier element is surrounded during operation of the turbomachine, for example with a Kompressorendtemperatur and thus does not have very high demands on the oxidation resistance of the material. It is therefore usually sufficient if the support elements are made for example of StgδOT, Stg41T, St530TS or GGG40. In order to be able to further reduce a proportion of cooling air of a turbine platform in such turbomachines, this is carried out as short as possible, whereby However, increased by the aerodynamic resistance of a turbine blade, the static pressure before the leading edge of the turbine blade and causes a so-called bow wave effect. 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. In order to avoid this, a protective layer, for example an Inconel625 layer, is usually welded onto the carrier elements, which, however, is expensive to produce and causes 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.
Darstellung der ErfindungPresentation of the invention
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 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 from oxidation and on the other hand, the ease of maintenance of the turbomachine is significantly improved.
Dieses Problem wird durch die unabhängigen Ansprüche gelöst. Bevorzugte Ausführungsformen sind in den abhängigen Ansprüchen gezeigt. Die Erfindung beruht auf dem allgemeinen Gedanken, bei einer Strömungsmaschine in einem Spalt zwischen einer Brennkammer und einer dazu stromab gelegenen Turbine, stirnseitig an einem Trägerelement 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.This problem is solved by the independent claims. Preferred embodiments are shown in the dependent claims. The invention is based on the general idea, in a turbomachine in a gap between a combustion chamber and a turbine located downstream thereto, to arrange a replaceable insert on the end face of a carrier element, 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 so that it covers the complete end facing the gap of the support element. The insert is also releasably arranged on the support element and thereby easily replaced if necessary.
Entsprechend einer bevorzugten Ausführungsform der erfindungsgemäßen Lösung ist der austauschbare Einsatz aus einem oxidationsbeständigen, insbesondere einem oxidationsbeständigeren Material ausgebildet als das Trägerelement selbst. 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. Durch den Umstand, dass der austauschbare Einsatz 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.According to a preferred embodiment of the solution according to the invention, the replaceable insert of an oxidation-resistant, especially a more oxidation-resistant material is formed as the carrier element itself. Thus, the use effectively prevents unwanted oxidation of the support element and must, for example, in the same condition as the heat-resistant lining element only in one of the lining element appropriate maintenance interval replaced or maintained. 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 on the one hand is difficult to apply and on the other hand, especially in the case of maintenance is consuming to replace. Due to the fact that the replaceable insert can be formed from a plurality of circular segments or from two semicircular rings, it is also possible to replace only individual insert segments as needed, which also allows maintenance costs and maintenance costs to 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 Entirely dispensable throughout the support element, which reduces the downtime of the turbomachine on the one hand and on the other hand reduces the 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 half-circle 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. Kurze Beschreibung der ZeichnungenOther 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. Brief description of 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 explained in more detail in the following description. For features that are substantially or functionally the same or similar reference is made to the same reference numeral.
Dabei zeigen, jeweils schematischShow, each schematically
Fig. 1 einen Längsschnitt durch eine Turbineneingangsseite im Bereich eines Spaltes,1 shows a longitudinal section through a turbine inlet side in the region of a gap,
Fig. 2 eine vergrößerte perspektivische Darstellung des Bereiches A aus Fig. 1 ,2 is an enlarged perspective view of the area A of FIG. 1,
Fig. 3 einen Längsschnitt im Bereich eines Spaltes zwischen einer ersten Brennkammer und einer stromab gelegenen Hochdruckturbine mit einem erfindungsgemäßen Einsatz,3 shows a longitudinal section in the region of a gap between a first combustion chamber and a downstream high-pressure turbine with an insert according to the invention,
Fig. 4 einen Längsschnitt durch die Strömungsmaschine im Bereich eines4 shows a longitudinal section through the turbomachine in the region of
Spaltes zwischen einer zweiten Brennkammer und einer dazu stromab gelegenen Niederdruckturbine mit dem erfindungsgemäßen Einsatz.Gap between a second combustion chamber and a downstream low-pressure turbine with the insert according to the invention.
Detaillierte Beschreibung der ZeichnungenDetailed description of the drawings
Entsprechend Fig. 1 weist eine erfindungsgemäße Strömungsmaschine 1 , beispielsweise eine Gasturbine, zumindest eine Brennkammer 2 und wenigstens eine stromab der Brennkammer 2 gelegene Turbine 3 auf. Die Strömungsrichtung ist dabei gemäß Fig. 1 mit dem Bezugszeichen 4 gekennzeichnet. Zwischen der Brennkammer 2 und der stromab gelegenen Turbine 3 ist ein Spalt 5 ausgebildet, welcher über eine Dichtung 6 (vgl. Fig. 2 bis 4) abgedichtet ist. Wie in Fig. 1 weiter gezeigt, weist die Turbine 3 zumindest ein Trägerelement 7 und ein damit verbundenes und als Hitzeschutz ausgebildetes Auskleidungselement 8 auf.According to FIG. 1, a turbomachine 1 according to the invention, for example a gas turbine, has at least one combustion chamber 2 and at least one turbine 3 located downstream of the combustion chamber 2. The Flow direction is indicated in FIG. 1 by the reference numeral 4. Between the combustion chamber 2 and the turbine 3 located downstream, a gap 5 is formed, which is sealed by a seal 6 (compare FIGS. 2 to 4). As further shown in FIG. 1, the turbine 3 has at least one carrier element 7 and a lining element 8 connected thereto and designed as heat protection.
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. Fig. 1 bis 4). Der austauschbare Einsatz 10 ist aus einem oxidationsbeständigen Material ausgebildet, welches insbesondere eine höhere Oxidationsbeständigkeit besitzt als das für das Trägerelement 7 verwendete Material. Ein willkommener Nebeneffekt der kürzen Turbinen 3 ist auch ein reduzierter Kühlluftanteil, wodurch der Wirkungsgrad der Turbine 3 gesteigert werden kann. Aufgrund des kreisförmigen Querschnitts der Turbine 3 ist der austauschbare Einsatz 10 entweder aus mehreren Kreissegmenten oder aus zwei Halbkreisringen gebildet, wobei insbesondere die Kreissegmente aufgrund ihres geringen Gewichts ein verbessertes Handling erlauben. Darüber hinaus bietet sich dadurch der Vorteil, einzelne Kreissegmente des Einsatzes 10 bedarfsgerecht zu erneuern, wodurch insgesamt ein Wartungsaufwand und dadurch Wartungskosten eingespart werden können. Der stirnseitig an dem Trägerelement 7 angeordnete Einsatz 10 verdeckt eine Stirnseite des Trägerelementes 7 komplett, so dass dieses vollständig vor in den Spalt 5 einbrechenden Heißgasen geschützt ist. Eine Befestigung des Einsatzes 10 am Trägerelement 7 erfolgt dabei beispielsweise über einen trägerelementseitigen Hinterschnitt 11 (vgl. Fig. 4), in welchen der austauschbare Einsatz 10 eingreift und/oder über zumindest ein Befestigungsmittel 12 (vgl. Fig. 2 bis 4), beispielsweise eine Schraube. Dies gewährleistet eine leichte Lösbarkeit und damit einen schnellen Austausch des Einsatzes 10 beziehungsweise der Dichtung 6 im Wartungsfall.In order to achieve manufacturing advantages and advantages in terms of operational stability, 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. The support elements 7, however, oxidize very much due to too high a temperature. In order to prevent direct contact of the hot gases with the carrier element 7 in the gap 5 and thereby reduce the tendency to oxidation, an exchangeable insert 10 is arranged on the front side of the carrier element 7 in the gap 5 (cf., FIGS. 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 shorter turbines 3 is also a reduced proportion of cooling air, whereby the efficiency of the turbine 3 can be increased. Due to the circular cross-section of the turbine 3, 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. In addition, 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 completely protected from collapsing 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 (compare Fig. 4) in which the replaceable insert 10 engages and / or via at least one attachment 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.
Um einen möglichst hohen Widerstand gegen Oxidation beziehungsweise Temperatur zu erreichen, ist der austauschbare Einsatz 10 vorzugsweise mit einer verschleißresistenten und/oder temperaturbeständigen Beschichtung versehen oder gänzlich aus einem verschleißresistenten und/oder 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 replaceable insert 10 is preferably provided with a wear-resistant and / or temperature-resistant coating or formed entirely of a wear-resistant and / or temperature-resistant material. In the case of wear or oxidation of the insert 10, the "handy" segments can thus be easily exchanged, Moreover, the higher compatible temperatures of the materials in the gap 5 make it possible to reduce the proportion of cooling air used to rinse the gap 5 and thereby to increase the efficiency of the turbine 3 or of the turbomachine 1. An oxidation-resistant wear-resistant layer may, for example, take 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. In general, there is no limit to 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 zeigt einen Längsschnitt im Bereich eines Spaltes 5 zwischen einer ersten Brennkammer und einer Hochdruckturbine. Dabei ist der austauschbare Einsatz 10 an einem äußeren Trägerelement T mittels eines Befestigungsmittels 12 befestigt. Gleichzeitig greift der Einsatz 10 in einem an dem äußeren Trägerelement T ausgebildeten Hinterschnitt 11 ein und liegt an seiner dem Spalt abgewandten Seite 16 an einem äußeren Auskleidungselement 8' an. Der austauschbare Einsatz 10 grenzt mit einer weiteren Seite 17 an einen Turbinenschaufelträger 18 an. Der Einsatz 10 schließt den Spalt 5 gemäß Fig. 3 derart ab, dass ein eventuell von außen einbrechendes Heißgas nicht an das äußere Trägerelement T und/oder an den Turbinenschaufelträger 18 gelangen kann und dieses/diesen dadurch vor einer Oxidation schützt. Selbstverständlich ist der erfindungsgemäße Einsatz 10 auch in einem Spalt 5 zwischen einer zweiten Brennkammer und einer dazu stromab gelegenen Niederdruckturbine (vgl. Fig. 4) einsetzbar.3 shows a longitudinal section in the region of a gap 5 between a first combustion chamber and a high-pressure turbine. In this case, the replaceable insert 10 is fastened to an outer support element T by means of a fastening means 12. At the same time, the insert 10 engages in an undercut 11 formed on the outer support element T and lies 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 off the gap 5 according to FIG. 3 in such a way that a hot gas which may penetrate from the outside can not reach the outer carrier element T and / or the turbine blade carrier 18 and thereby protect it from oxidation. Of course, the insert 10 according to the invention can also be used in a gap 5 between a second combustion chamber and a low-pressure turbine located downstream thereof (compare FIG.
Wie in Fig. 4 gezeigt, ist die Dichtung 6 in einer axial offenen Stufe 13 am Einsatz 10 angeordnet, wobei die Dichtung 6 über lösbare Halteelemente 14 axial in der Stufe 13 gehalten wird. Der Einsatz 10 trägt somit die Dichtung 6, welche beispielsweise als Membrandichtung ausgebildet ist. Dabei kann die Dichtung 6 ähnlich dem Einsatz 10 mehrere Kreissegmente oder zwei Halbkreisringe aufweisen, welche sich in Umfangsrichtung überlappen. Das Halteelement 14 ist dabei jeweils von dem Befestigungsmittel 12 gegen den Einsatz 10 beziehungsweise das Trägerelement 7 verspannt und verhindern dadurch ein axiales Verschieben der Dichtung 6. Dabei ist jedes Halteelement 14 jeweils in einer Ausnehmung 19 angeordnet (vgl. Fig. 2), die eine Dicke des Einsatzes 10 in Strömungsrichtung 4 zumindest reduziert. Durch die Ausnehmung 19 wird die Lage des jeweils darin aufgenommenen Halteelements 14 vorbestimmt, wodurch sich die Montage der Halteelemente 14 vereinfacht.As shown in Fig. 4, the seal 6 is arranged in an axially open stage 13 on the insert 10, wherein the seal 6 is held by releasable holding elements 14 axially in the stage 13. The insert 10 thus carries the seal 6, which for example, is designed as a membrane seal. In this case, similar to the insert 10, the seal 6 may have a plurality of circle segments or two semicircular rings which overlap in the circumferential direction. The holding element 14 is in each case braced by the fastening means 12 against the insert 10 or the support member 7 and thereby prevent axial displacement of the seal 6. In this case, each holding element 14 is arranged in each case in a recess 19 (see Fig. 2), the one Thickness of the insert 10 in the flow direction 4 at least reduced. 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.
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 seal 6 at at least one point on the insert 10. When using two sealing membranes designed as semicircular rings, these are therefore preferably fixed at 12 o'clock and at 6 o'clock at one point on the carrier element 7. In the respective fixing point, 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.
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 kann der Einsatz 10 wahlweise gänzlich aus einem oxidations- und temperaturbeständigen Material ausgebildet sein oder eine oxidationsbeständige und temperaturbeständige Beschichtung aufweisen, während ein Kern des Einsatzes 10 aus dem gleichen Werkstoff wie das Trägerelement 7, T ausgebildet ist und dadurch ein nahezu identisches Temperaturverhalten zwischen Einsatz 10 und Trägerelement 7, T 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 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. In this case, the insert 10 can optionally be made entirely of an oxidation-resistant and temperature-resistant material or have an oxidation-resistant and temperature-resistant coating, while a core of the insert 10 from the same material as the support member 7, T is formed and thereby a nearly identical temperature behavior between insert 10 and support member 7, T can be achieved, which has a favorable effect on any expected gap widths. In addition, 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.
BezugszeichenlisteLIST OF REFERENCE NUMBERS
1 Stromungsmaschine1 flow machine
2 Brennkammer2 combustion chamber
3 Turbine3 turbine
4 Strömungsrichtung4 flow direction
5 Spalt5 gap
6 Dichtung6 seal
7 Trägerelement7 carrier element
T äußeres TrägerelementT outer support element
8 Auskleidungselement8 lining element
8' äußeres Auskleidungselement8 'outer lining element
9 Turbinenschaufel 0 Einsatz 1 Hinterschnitt 2 Befestigungsmittel 3 axial offene Stufe am Einsatz 10 4 Halteelemente 5 Fixierstift 6 eine dem Spalt 5 abgewandte Seite des Einsatzes 10 7 eine dem Turbinenschaufelträger 18 zugewandte Seite des9 turbine blade 0 insert 1 undercut 2 fastening means 3 axially open step on the insert 10 4 holding elements 5 fixing pin 6 a side of the insert 10 7 facing away from the gap 5 a side of the insert facing the turbine blade carrier 18
Einsatzes 10 8 Turbinenschaufelträger 9 Ausnehmung Insert 10 8 turbine blade carrier 9 recess

Claims

Patentansprüche claims
1. Strömungsmaschine (1 ), insbesondere eine Gasturbine, mit zumindest einer Brennkammer (2) und wenigstens einer dazu stromab gelegenen Turbine (3),1. turbomachine (1), in particular a gas turbine, with at least one combustion chamber (2) and at least one turbine (3) located downstream thereof,
- wobei die Turbine (3) zumindest ein Trägerelement (7) und ein damit verbundenes und als Hitzeschutz ausgebildetes Auskleidungselement (8) aufweist,- wherein the turbine (3) has at least one carrier element (7) and a lining element (8) connected thereto and designed as heat protection,
- wobei zwischen der zumindest einen Brennkammer (2) und der stromab gelegenen Turbine (3) ein mittels einer Dichtung (6) abgedichteter Spalt (5) ausgebildet ist, in dem stirnseitig am Trägerelement (7) ein austauschbarer Einsatz (10) angeordnet ist, der zumindest das Trägerelement (7) vor Heißgasen schützt.- wherein between the at least one combustion chamber (2) and the downstream turbine (3) by means of a seal (6) sealed gap (5) is formed in the front side on the carrier element (7) an exchangeable insert (10) is arranged, which protects at least the carrier element (7) from hot gases.
2. Strömungsmaschine nach Anspruch 1, dadurch gekennzeichnet,2. Turbomachine according to claim 1, characterized
- dass der austauschbare Einsatz (10) aus einem oxidationsbeständigeren Material ausgebildet ist als das Trägerelement (7), und/oder- That the replaceable insert (10) made of a more oxidation-resistant material is formed as the carrier element (7), and / or
- dass der austauschbare Einsatz (10) aus mehreren Kreissegmenten oder aus zwei Halbkreisringen gebildet ist, und/oder- That the replaceable insert (10) is formed of a plurality of circular segments or two semicircular rings, and / or
- dass der austauschbare Einsatz (10) in einen trägerelementseitigen Hinterschnitt (11) einreift und/oder über zumindest ein Befestigungsmittel (12) an der Stirnseite des Trägerelements (7) gehalten ist.- That the replaceable insert (10) engages in a carrier element-side undercut (11) and / or via at least one fastening means (12) on the end face of the support member (7) is held.
3. Strömungsmaschine nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der austauschbare Einsatz (10) eine verschleissresistente und/oder temperaturbeständige Beschichtung aufweist.3. Turbomachine according to claim 1 or 2, characterized the replaceable insert (10) has a wear-resistant and / or temperature-resistant coating.
4. Strömungsmaschine nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet,4. Turbomachine according to one of claims 1 to 3, characterized
- dass der Einsatz (10) im Spalt (5) zwischen einer ersten Brennkammer und einer stromab gelegenen Turbine (3), und/oder- That the insert (10) in the gap (5) between a first combustion chamber and a downstream turbine (3), and / or
- dass der Einsatz (10) im Spalt (5) zwischen einer zweiten Brennkammer und einer stromab gelegenen Turbine (3) angeordnet ist.- That the insert (10) in the gap (5) between a second combustion chamber and a downstream turbine (3) is arranged.
5. Strömungsmaschine nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet,5. Turbomachine according to one of claims 1 to 4, characterized
- dass der Einsatz (10) die Dichtung (6) trägt, und/oder- That the insert (10) carries the seal (6), and / or
- dass die Dichtung (6) als Membrandichtung ausgebildet ist.- That the seal (6) is designed as a membrane seal.
6. Strömungsmaschine nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Dichtung (6) mehrere Kreissegmente oder zwei Halbkreisringe aufweist, wobei sich die beiden Halbkreisringe in Umfangsrichtung überlappen.6. Turbomachine according to one of claims 1 to 5, characterized in that the seal (6) has a plurality of circular segments or two semicircular rings, wherein the two semicircular rings overlap in the circumferential direction.
7. Strömungsmaschine nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet,7. Turbomachine according to one of claims 1 to 6, characterized
- dass die Dichtung (6) in einer axial offenen Stufe (13) am Einsatz (10) angeordnet ist, und/oder- That the seal (6) in an axially open stage (13) on the insert (10) is arranged, and / or
- dass die Dichtung (6) über lösbare Halteelemente (14) in der Stufe (13) gehalten wird.- That the seal (6) via releasable holding elements (14) is held in the step (13).
8. Strömungsmaschine nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass jedes Kreissegment und/oder jeder Halbkreisring der Dichtung (6) an zumindest einem Punkt an dem Einsatz (10) festgelegt ist.8. 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 to the insert (10) at at least one point.
9. Austauschbarer Einsatz und/oder Dichtung für eine Strömungsmaschine nach einem der Ansprüche 1 bis 8. 9. Replaceable insert and / or seal for a turbomachine according to one of claims 1 to 8.
EP06829956.9A 2005-12-14 2006-11-08 Turbomachine Not-in-force EP1960636B1 (en)

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US8555655B2 (en) 2013-10-15

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