EP0995881A2 - Sealing arrangement - Google Patents
Sealing arrangement Download PDFInfo
- Publication number
- EP0995881A2 EP0995881A2 EP99810907A EP99810907A EP0995881A2 EP 0995881 A2 EP0995881 A2 EP 0995881A2 EP 99810907 A EP99810907 A EP 99810907A EP 99810907 A EP99810907 A EP 99810907A EP 0995881 A2 EP0995881 A2 EP 0995881A2
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- EP
- European Patent Office
- Prior art keywords
- sealing arrangement
- arrangement according
- felt
- sealing
- blade
- 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.)
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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
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
Definitions
- the invention relates to a sealing arrangement for reducing leakage currents within a flow rotation machine according to the preamble of Claim 1.
- Seals consist of a sealing surface with or without a spring element exist and in a correspondingly provided in the rotor or guide blade root Sealing groove contour.
- the spring element generates one Contact pressure as well as the positioning of the sealing surface between those to be sealed Contours.
- Such seals are used in static gas turbine components carrying hot gas, such as turbine guide vanes, heat accumulation segments or combustion chamber segments to reduce cooling air consumption, to prevent axial gap flows with hot gas and for shielding against heat radiation.
- DE 195 20 268 A1 shows a surface seal
- the two sealing surfaces has, which each include an elastic corrugated surface.
- a U-shaped surface seal 11 along the inner contour of a hammer head trained vane root and serves to seal the cooling air flowing into the Guide vane is blown in as well as to protect the guide vane foot from hot Gases.
- the sealing arrangement to be designed in different surface shapes However, it needs flat, sealed contour surfaces on which they lie flat can. Is it the sealing of intermediate gaps, that of curved Surfaces are included, so the known sealing arrangement bumps to its limits.
- the invention has for its object a sealing arrangement for reduction leakage currents within a rotary flow machine, preferably an axial turbomachine, with rotor and guide vanes, each in at least a row of rotor blades or guide vanes are arranged and have blade feet, via which the individual rotor blades and guide vanes are connected with fastening contours are to be designed such that the sealing arrangement between any shape Gaps between spaces is adjustable.
- the sealing arrangement should consist of one Material that corresponds to the operating conditions prevailing in a gas turbine plant, with regard to the high temperatures and pressure conditions, without prejudice survives.
- a sealing arrangement according to the preamble of the claim 1 designed such that in the space between two adjacent Blade feet within a guide or blade row or between Guide and / or moving blades and adjacent components of the turbomachine a sealing element comprising a felt-like material is provided.
- Felt-like materials based on intermetallic fibers can be undamaged Temperatures of over 1000 ° C survive because of the intermetallic Fibers have a high heat resistance. They also have one high resistance to oxidation and advantageous thermal conductivity. These properties can also be specifically adjusted by the selected intermetallic fiber and be adapted to the respective conditions. Add to that that through appropriate Choice of the intermetallic used in the manufacture of the felt-like material Fibers a fine-grained structure with selectively adjustable porosity and thus associated elasticity is possible.
- the intermetallic fibers preferably consist of an intermetallic Aluminum-iron or nickel-based phase or an alloy of the above mentioned components.
- the sealing elements according to the invention are designed like a strand and have, depending on the cross-sectional shape of the space to be sealed between two adjacent blade feet, over different strand cross-sections, for example rectangular, angled or cross-shaped cross sections.
- the strand-like sealing element is preferably firmly attached to at least a blade root attached at a suitable point, for example by gluing, Soldering or welding.
- a suitable point for example by gluing, Soldering or welding.
- the felt-like material it is also possible to use the felt-like material to have a precise fit in the appropriate fitting grooves.
- Figure 1 there are two blade feet 1, 2 in a highly schematic manner opposite, arranged for example in a guide or moving blade row are.
- a sealing element 3 made of felt-like material.
- the sealing element 3 is true to shape the surface contours of both blade feet 1 and 2 adjusted so that the seal seals both blade feet 1 and 2 gas-tight against each other.
- the sealing element 3 is fixed with a Blade foot connected. This is preferably done with the aid of a soldering, adhesive or welded joint.
- the sealing element 3 is fixed with the blade root 1 along its contact contour 4.
- FIG. 2a two perspective views are shown Guide vanes 5 and 6 are shown, each having a headband 7, a guide vane blade 8 and have a guide blade root 9. Between the opposite Head bands 7 of the guide blades 5 and 6 and the opposite guide blade feet 9 is a sealing element which is suitably adapted to the intermediate space 3, consisting of felt-like material.
- FIG. 2a shows two blades 10, 11 arranged side by side -
- the blade is only for reasons of a clearer representation Blade 10 not shown - between those in the upper region of the blade feet likewise the sealing elements 3 according to the invention are provided.
- FIGS. 3a to 3e A large number of differently shaped sealing elements are shown in FIGS. 3a to 3e.
- the sealing element 3 in FIG. 3a protrudes into two opposite ones Grooves 12, 13 each have two adjacent blade feet.
- this includes Sealing element 3 both a vertical contact surface of the blade root shown as well as part of the lower horizontal contact surface.
- Figure 3c shows one Sheet metal structure 14 for fastening purposes, on the vertical flank of which Felt-like material provided sealing element 3 is attached.
- the sealing element 3 can also be made by means of soldered, adhesive and welded connections Detachable connections, such as screw connections, to corresponding Contact surfaces are attached.
- a side view is shown by a guide vane in the area of the guide vane foot 9 has a sealing element 3, which is blunt on a plane Side surface is soldered.
- the guide vane sits in the area of the headband 7 the felt-like sealing element 3 'in a corresponding groove-shaped recess within of the headband.
- Such grooves can also be in the form of a dovetail shape be carried out as shown in Figure 3e. Here it can Sealing element 3 inserted laterally into the dovetail-like recess or removed again.
- sealing elements 3 are provided the entry of hot gases into the space between the housing 17 and the first Prevent vane 18.
- Another sealing element 3 ' also seals the lateral space between the guide vane foot and housing 17 from gas-tight.
- the sealing arrangement according to the invention consisting of felt-like material, which in Kind of an intermetallic felt is basically in there anywhere Spaces are inserted in which a gas flow is prevented should. Due to the high oxidation resistance and high resistance against mechanical deformations this is suitable on aluminides or Intermetallic felts based on nickel aluminides are particularly preferred for use in gas turbines, where hot temperature conditions and high pressure ratios are predominant.
Abstract
Description
Die Erfindung bezieht sich auf eine Dichtungsanordnung zur Reduzierung von Leckströmen
innerhalb einer Strömungsrotationsmaschine gemäß dem Oberbegriff des
Anspruchs 1.The invention relates to a sealing arrangement for reducing leakage currents
within a flow rotation machine according to the preamble of
Gattungsgemäße Dichtungsanordnungen sind hinreichend bekannt und dienen einer weitgehend gasdichten Verbindung zwischen zwei fest nebeneinander angeordneten Laufschaufeln bzw. Leitschaufeln, die in Turborotationsmaschinen zur Verdichtung oder Entspannung gasförmiger Medien eingesetzt werden.Generic sealing arrangements are well known and serve one largely gas-tight connection between two fixed side by side Rotor blades or guide vanes used in turbo-rotary machines for compression or expansion of gaseous media can be used.
Es sind Dichtungen bekannt, die aus einer Dichtfläche mit oder ohne einem Federelement bestehen und in eine entsprechend im Lauf- oder Leitschaufelfuß vorgesehenen Dichtnutkontur eingelegt werden. Das Federelement erzeugt hierbei einen Anpreßdruck sowie die Positionierung der Dichtfläche zwischen den zu dichtenden Konturen. Derartige Dichtungen dienen bei Heißgas führenden statischen Gasturbinen-Komponenten, wie Turbinenleitschaufeln, Wärmestausegmenten oder Brennkammersegmenten zur Reduktion des Kühlluftverbrauches, zur Verhinderung von axialen Spaltströmungen mit Heißgas und zur Abschirmung gegenüber Wärmestrahlung.Seals are known which consist of a sealing surface with or without a spring element exist and in a correspondingly provided in the rotor or guide blade root Sealing groove contour. The spring element generates one Contact pressure as well as the positioning of the sealing surface between those to be sealed Contours. Such seals are used in static gas turbine components carrying hot gas, such as turbine guide vanes, heat accumulation segments or combustion chamber segments to reduce cooling air consumption, to prevent axial gap flows with hot gas and for shielding against heat radiation.
Aus der US 0 501 700 A1 geht eine Turbinenleitschaufelkonstruktion hervor, deren Leitschaufelfuß sowie Kopfband mittels Federdichtelementen 52, 54 (s. hierzu die Figur 3 der Druckschrift) gegen entsprechende Konturen der Gehäusekomponenten fixiert werden. Der Nachteil von mit Federelementen versehenen Dichtungen besteht u.a. darin, daß nicht ausgeschlossen werden kann, daß das Federmaterial aufgrund der überaus hohen Materialbeanspruchungen hinsichtlich der in Gasturbinen vorherrschenden Temperatur- und Druckbedingungen sehr rasch ermüdet, so daß es seine Federkraft und damit seine Dichtfunktion verliert.From US 0 501 700 A1 a turbine guide vane construction emerges, the Guide blade root and headband by means of spring sealing elements 52, 54 (see Figure 3 of the document) against corresponding contours of the housing components be fixed. The disadvantage of seals provided with spring elements is i.a. in that it cannot be excluded that the spring material due to the extremely high material loads with regard to those prevailing in gas turbines Temperature and pressure conditions tire very quickly, making it its spring force and thus its sealing function loses.
Ferner geht aus der DE 195 20 268 A1 eine Flächendichtung hervor, die zwei Dichtflächen
aufweist, die jeweils eine elastische Wellfläche einschließen. Im Ausführungsbeispiel
gemäß der Figur 5 der angegebenen Druckschrift erstreckt sich die zu
einem U geformte Flächendichtung 11 entlang der Innenkontur eines hammerkopfartig
ausgebildeten Leitschaufelfußes und dient der Abdichtung von Kühlluft, die in die
Leitschaufel eingeblasen wird sowie zum Schutz des Leitschaufelfußes vor heißen
Gasen. Die in unterschiedlichen Flächenformen auszubildende Dichtungsanordnung
benötigt jedoch ebene, abzudichtende Konturflächen, an denen sie flächig aufliegen
können. Handelt es sich um die Abdichtung von Zwischenspalten, die von gekrümmten
Oberflächen eingeschlossen sind, so stößt die bekannte Dichtungsanordnung
an ihre Grenzen.Furthermore, DE 195 20 268 A1 shows a surface seal, the two sealing surfaces
has, which each include an elastic corrugated surface. In the
Der Erfindung liegt die Aufgabe zugrunde, eine Dichtungsanordnung zur Reduzierung von Leckströmen innerhalb einer Strömungsrotationsmaschine, vorzugsweise einer axialen Turbomaschine, mit Lauf- und Leitschaufeln, die jeweils in wenigstens einer Lauf- bzw. Leitschaufelreihe angeordnet sind und Schaufelfüße aufweisen, über die die einzelnen Lauf- und Leitschaufeln mit Befestigungskonturen verbunden sind, derart auszubilden, daß die Dichtungsanordnung zwischen beliebig geformten Spaltzwischenräumen anpaßbar ist. Ferner soll die Dichtungsanordnung aus einem Material bestehen, das die in einer Gasturbinenanlage vorherrschenden Betriebsbedinungen, hinsichtlich der hohen Temperaturen und Druckverhältnisse, unbeschadet übersteht.The invention has for its object a sealing arrangement for reduction leakage currents within a rotary flow machine, preferably an axial turbomachine, with rotor and guide vanes, each in at least a row of rotor blades or guide vanes are arranged and have blade feet, via which the individual rotor blades and guide vanes are connected with fastening contours are to be designed such that the sealing arrangement between any shape Gaps between spaces is adjustable. Furthermore, the sealing arrangement should consist of one Material that corresponds to the operating conditions prevailing in a gas turbine plant, with regard to the high temperatures and pressure conditions, without prejudice survives.
Die Lösung der der Erfindung zugrundeliegenden Aufgabe ist Gegenstand des Anspruchs
1. Den Erfindungsgedanken vorteilhaft weiterbildende Merkmale sind Gegenstand
der Unteransprüche. The solution to the problem on which the invention is based is the subject of the
Erfindungsgemäß ist eine Dichtungsanordnung gemäß des Oberbegriffes des Anspruchs
1 derart ausgebildet, daß in den Zwischenraum zweier benachbart angebrachter
Schaufelfüße innerhalb einer Leit- oder Laufschaufelreihe oder zwischen
Leit- und/oder Laufschaufeln und benachbarten Komponenten der Strömungsmaschine
ein filzartiges Material aufweisendes Dichtelement vorgesehen ist.According to the invention is a sealing arrangement according to the preamble of the
Die der Erfindung zugrundeliegende Idee ist der Einsatz eines an sich bekannten filzartigen Materials, das aus zusammengepreßten, gesinterten intermetallischen Fasern besteht und gezielt in den Zwischenraum zweier Leit- bzw. Laufschaufelfüße zur Reduzierung des Gasaustausches zwischen zwei benachbarten Schaufelfüßen, eingebracht wird.The idea on which the invention is based is the use of a known one felt-like material made of compressed, sintered intermetallic fibers exists and specifically in the space between two guide or blade feet Reduction of gas exchange between two adjacent blade feet becomes.
Filzartige Materialien, die auf intermetallischen Fasern basieren, können unbeschadet Temperaturen von über 1000 ° C überstehen, da die intermetallischen Fasern eine hohe Hitzebeständigkeit aufweisen. Überdies verfügen sie über eine hohe Oxidationsbeständigkeit und vorteilhafte Wärmeleiteigenschaften. Diese Eigenschaften können zudem durch die gewählte intermetallische Faser gezielt eingestellt und den jeweiligen Bedingungen angepaßt werden. Hinzu kommt, daß durch geeignete Wahl der bei der Herstellung des filzähnlichen Materials verwendeten intermetallischen Fasern ein feinkörniges Gefüge mit gezielt einstellbarer Porösität und damit verbunden Elastizität möglich ist.Felt-like materials based on intermetallic fibers can be undamaged Temperatures of over 1000 ° C survive because of the intermetallic Fibers have a high heat resistance. They also have one high resistance to oxidation and advantageous thermal conductivity. These properties can also be specifically adjusted by the selected intermetallic fiber and be adapted to the respective conditions. Add to that that through appropriate Choice of the intermetallic used in the manufacture of the felt-like material Fibers a fine-grained structure with selectively adjustable porosity and thus associated elasticity is possible.
Vorzugsweise bestehen die intermetallischen Fasern aus einer intermetallischen Phase auf Aluminium-Eisen- oder Nickelbasis oder aus einer Legierung der vorstehend genannten Bestandteile.The intermetallic fibers preferably consist of an intermetallic Aluminum-iron or nickel-based phase or an alloy of the above mentioned components.
Bereits im Wege der Herstellung derartiger Materialien kann ihre Geometrie, mit der sie in den Zwischenraum zweier benachbarter Schaufelfüße oder im Zwischenraum zwischen Schaufelvorderkante und Brennkammersegment eingebracht werden, erzeugt werden. So sind die erfindungsgemäßen Dichtelemente strangartig ausgebildet und verfügen, je nach Querschnittsform des abzudichtenden Zwischenraumes zwischen zwei benachbarten Schaufelfüßen, über unterschiedliche Strangquerschnitte, beispielsweise rechteckig, abgewinkelt oder kreuzartig ausgebildete Querschnitte.Already in the way of the production of such materials, their geometry, with which them in the space between two adjacent blade feet or in the space are introduced between the front edge of the blade and the combustion chamber segment become. Thus, the sealing elements according to the invention are designed like a strand and have, depending on the cross-sectional shape of the space to be sealed between two adjacent blade feet, over different strand cross-sections, for example rectangular, angled or cross-shaped cross sections.
Das strangartig ausgebildete Dichtelement wird vorzugsweise fest an wenigstens einem Schaufelfuß an geeigneter Stelle angebracht, beispielsweise durch Kleben, Löten oder Schweißen. Es ist jedoch auch möglich, das filzartig ausgebildete Material in entsprechend vorgesehene Paßnuten paßgenau zu verfügen.The strand-like sealing element is preferably firmly attached to at least a blade root attached at a suitable point, for example by gluing, Soldering or welding. However, it is also possible to use the felt-like material to have a precise fit in the appropriate fitting grooves.
Die Erfindung wird nachstehend ohne Beschränkung des allgemeinen Erfindungsgedankens anhand von Ausführungsbeispielen unter Bezugnahme auf die Zeichnung exemplarisch. Es zeigen:
- Fig. 1
- Teilquerschnittsdarstellung durch zwei benachbarte Schaufelfüße mit in einen Zwischenraum eingebrachtes filzartiges Materia;
- Fig. 2a, b
- perspektivische Darstellung von jeweils zwei benachbarten Lauf- und Leitschaufeln;
- Fig. 3 a,b,c,d,e
- Material, beispielhafte Ausführungsformen des erfindungsgemäßen Dichtungselementes sowie
- Fig. 4
- Querschnittsdarstellung durch eine Gasturbinenanlage im Bereich des Brennkammeraustrittes sowie Turbineneintrittes.
- Fig. 1
- Partial cross-sectional view through two adjacent blade feet with felt-like material introduced into a space;
- 2a, b
- perspective view of two adjacent blades and vanes;
- 3 a, b, c, d, e
- Material, exemplary embodiments of the sealing element according to the invention and
- Fig. 4
- Cross-sectional view through a gas turbine system in the area of the combustion chamber outlet and turbine inlet.
In Figur 1 stehen sich in stark schematisierter Weise zwei Schaufelfüße 1, 2 benachbart
gegenüber, die beispielsweise in einer Leit- oder Laufschaufelreihe angeordnet
sind. Im Zwischenraum zwischen beiden Schaufelfüßen ist ein Dichtelement 3, bestehend
aus filzartigem Material vorgesehen. Das Dichtelement 3 ist formgetreu an
die Oberflächenkonturen beider Schaufelfüße 1 und 2 angepaßt, so daß die Dichtung
beide Schaufelfüße 1 und 2 gasdicht gegeneinander abdichtet.In Figure 1 there are two
Zu Zwecken einer erleichterten Montage von Schaufelfüßen in entsprechende Aussparungen
in Gehäuseteilen der Turbinenanlage ist das Dichtelement 3 fest mit einem
Schaufelfuß verbunden. Dies erfolgt vorzugsweise mit Hilfe einer Löt-, Kleb-
oder Schweißverbindung.For the purpose of facilitating the assembly of blade feet in corresponding recesses
in housing parts of the turbine system, the
Im Falle des Ausführungsbeispieles gemäß der Figur 1 ist das Dichtelement 3 fest
mit dem Schaufelfuß 1 entlang seiner Berührungskontur 4 verfügt.In the case of the exemplary embodiment according to FIG. 1, the
In Figur 2a sind in perspektivischer Darstellung zwei nebeneinander angeordnete
Leitschaufeln 5 und 6 dargestellt, die jeweils ein Kopfband 7, ein Leitschaufelblatt 8
sowie einen Leitschaufelfuß 9 aufweisen. Zwischen den sich gegenüberliegenden
Kopfbändern 7 der Leitschaufeln 5 und 6 sowie der sich gegenüberliegenden Leitschaufelfüße
9 ist jeweils ein geeignet an den Zwischenraum angepaßtes Dichtelement
3, bestehend aus filzartigem Material vorgesehen.In FIG. 2a two perspective views are shown
In Figur 2a sind zwei nebeneinander angeordnete Laufschaufeln 10, 11 dargestellt -
nur aus Gründen einer übersichtlicheren Darstellung ist das Laufschaufelblatt der
Laufschaufel 10 nicht dargestellt -, zwischen denen im oberen Bereich der Laufschaufelfüße
ebenso die erfindungsgemäßen Dichtelemente 3 vorgesehen sind.FIG. 2a shows two
In Figur 3a bis 3e ist eine Vielzahl unterschiedlich ausgeformter Dichtelemente gezeigt.
So ragt das Dichtelement 3 in der Figur 3a in zwei sich gegenüberliegende
Nuten 12, 13 jeweils zweier benachbarter Schaufelfüße ein. In Figur 3b umfaßt das
Dichtelement 3 sowohl eine vertikale Kontaktfläche des dargestellten Laufschaufelfußes
als auch einen Teil der unteren horizontalen Auflagefläche. Figur 3c zeigt eine
Blechstruktur 14 zu Befestigungszwecken, an deren vertikale Flanke ein aus dem
filzartigen Material vorgesehenes Dichtelement 3 angebracht ist. Neben den angegebenen
Löt-, Klebe- und Schweißverbindungen kann das Dichtelement 3 auch mittels
lösbarer Verbindungen, wie beispielsweise Schraubverbindungen, an entsprechende
Kontaktflächen angebracht werden.A large number of differently shaped sealing elements are shown in FIGS. 3a to 3e.
The
In Figur 3d ist eine Seitendarstellung durch eine Leitschaufel dargestellt, die im Bereich
des Leitschaufelfußes 9 ein Dichtelement 3 aufweist, das stumpf auf einer ebenen
Seitenfläche aufgelötet ist. Im Bereich des Kopfbandes 7 der Leitschaufel sitzt
das filzartige Dichtelement 3' in einer entsprechenden nutförmigen Aussparung innerhalb
des Kopfbandes. Derartige Nuten können auch in Form einer Schwalbenschwanzform
ausgeführt sein, wie es in Figur 3e dargestellt ist. Hierbei kann das
Dichtelement 3 seitlich in die schwalbenschwanzartige Ausnehmung eingeschoben
bzw. wieder entnommen werden.In Figure 3d, a side view is shown by a guide vane in the area
of the
In Figur 4 ist ein Querschnitt durch eine Turbinenanlage im Bereich des Brennkammeraustrittes
15 und Turbineneinlasses 16 dargestellt. Zwischen dem Turbinengehäuse
17 und dem Brennkammeraustritt 15 sind Dichtelemente 3 vorgesehen, die
den Eintritt von Heißgasen in den Zwischenraum zwischen Gehäuse 17 und der ersten
Leitschaufel 18 verhindern. Ebenso dichtet ein weiteres Dichtelement 3' den
seitlichen Zwischenraum zwischen Leitschaufelfuß und Gehäuse 17 gasdicht ab.4 shows a cross section through a turbine system in the region of the
Die erfindungsgemäße Dichtanordnung, bestehend aus filzartigem Material, das in Art eines intermetallischen Filzes ausgebildet ist, kann grundsätzlich überall dort in Zwischenräumen eingefügt werden, in denen eine Gasströmung unterbunden werden soll. Aufgrund der hohen Oxidationsresistenz und hohen Widerstandsfähigkeit gegenüber mechanischen Deformationen eignet sich dieses auf Aluminiden oder Nickelaluminiden basierende intermetallische Filze besonders bevorzugt für den Einsatz in Gasturbinen, in denen heiße Temperaturbedingungen und hohe Druckverhältnisse vorherrschend sind.The sealing arrangement according to the invention, consisting of felt-like material, which in Kind of an intermetallic felt is basically in there anywhere Spaces are inserted in which a gas flow is prevented should. Due to the high oxidation resistance and high resistance against mechanical deformations this is suitable on aluminides or Intermetallic felts based on nickel aluminides are particularly preferred for use in gas turbines, where hot temperature conditions and high pressure ratios are predominant.
- 1 , 21, 2
- SchaufelfußBlade root
- 3, 3'3, 3 '
- DichtelementSealing element
- 44th
- KonturverlaufContour course
- 5, 65, 6
- LeitschaufelnGuide vanes
- 77
- KopfbandHeadband
- 88th
- LeitschaufelblattVane blade
- 99
- LeitschaufelfußGuide blade root
- 10, 1110, 11
- LaufschaufelnBlades
- 12, 1312, 13
- NutenGrooves
- 1414
- BlechstrukturSheet metal structure
- 1515
- BrennkammeraustrittCombustion chamber outlet
- 1616
- TurbineneinlaßTurbine inlet
- 1717th
- TurbinengehäuseTurbine casing
- 1818th
- Leitschaufelvane
Claims (8)
dadurch gekennzeichnet, daß zwischen wenigstens zwei benachbarten Schaufelfüßen (1, 2) innerhalb einer Leit- oder Laufschaufelreihe oder zwischen Leit- und/oder Laufschaufeln und benachbarten Komponenten der Strömungsmaschine ein filzartiges Material aufweisendes Dichtelement (3) vorgesehen ist.Sealing arrangement for reducing leakage currents within a flow rotation machine, preferably an axial turbomachine, with rotor and guide vanes, which are each arranged in at least one row of rotor or guide vanes and have blade roots (1, 2) via which the individual rotor and guide vanes also Fastening contours are connected,
characterized in that a felt-like material sealing element (3) is provided between at least two adjacent blade feet (1, 2) within a row of guide or moving blades or between guide and / or blades and adjacent components of the turbomachine.
dadurch gekennzeichnet, daß das Dichtelement (3) beidseitig formschlüssig an Außenkonturen der benachbarten Schaufelfüsse (1, 2) angepaßt ist.Sealing arrangement according to claim 1,
characterized in that the sealing element (3) is adapted on both sides in a form-fitting manner to the outer contours of the adjacent blade roots (1, 2).
dadurch gekennzeichnet, daß das Dichtelement (3) wenigstens mit einem Schaufelfuß (1) fest verbunden ist.Sealing arrangement according to claim 1 or 2,
characterized in that the sealing element (3) is fixedly connected to at least one blade root (1).
dadurch gekennzeichnet, daß die Verbindung eine Löt- oder Klebverbindung ist.Sealing arrangement according to claim 3,
characterized in that the connection is a solder or adhesive connection.
dadurch gekennzeichnet, daß das filzartige Material ein intermetallischer Filz ist, der aus zusammengepreßten und gesinterten intermetallischen Fasern zusammengesetzt ist. Sealing arrangement according to one of claims 1 to 4,
characterized in that the felt-like material is an intermetallic felt, which is composed of compressed and sintered intermetallic fibers.
dadurch gekennzeichnet, daß die intermetallischen Fasern aus einer intermetallischen Phase auf Aluminium-, Eisen oder Nickelbasis oder eine Legierung aus diesen Bestandteilen besteht.Sealing arrangement according to claim 5,
characterized in that the intermetallic fibers consist of an intermetallic phase based on aluminum, iron or nickel or an alloy of these components.
dadurch gekennzeichnet, daß das filzartige Material über eine Porösität verfügt, so daß das Material von Kühlluft durchdringbar ist.Sealing arrangement according to one of claims 1 to 6,
characterized in that the felt-like material has a porosity so that the material can be penetrated by cooling air.
dadurch gekennzeichnet, daß die benachbarten Komponenten der Strömungsmaschine Gehäuseteile oder Brennkammer sind.Sealing arrangement according to one of claims 1 to 7,
characterized in that the adjacent components of the turbomachine are housing parts or combustion chamber.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19848103 | 1998-10-19 | ||
| DE19848103A DE19848103A1 (en) | 1998-10-19 | 1998-10-19 | Sealing arrangement |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP0995881A2 true EP0995881A2 (en) | 2000-04-26 |
| EP0995881A3 EP0995881A3 (en) | 2002-03-13 |
| EP0995881B1 EP0995881B1 (en) | 2004-01-07 |
Family
ID=7884914
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP99810907A Expired - Lifetime EP0995881B1 (en) | 1998-10-19 | 1999-10-06 | Sealing arrangement |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US6312218B1 (en) |
| EP (1) | EP0995881B1 (en) |
| JP (1) | JP4465067B2 (en) |
| DE (2) | DE19848103A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7175387B2 (en) | 2001-09-25 | 2007-02-13 | Alstom Technology Ltd. | Seal arrangement for reducing the seal gaps within a rotary flow machine |
| EP1914389A1 (en) * | 2006-10-20 | 2008-04-23 | Siemens Aktiengesellschaft | Turbine blade with separated seal element |
| FR2998610A1 (en) * | 2012-11-29 | 2014-05-30 | Snecma | Rectifier for use in turboshaft engine, has suction groove forming area for maintaining seal when groove of platform cooperates with inner casing, where concave and suction grooves are positioned on respective sides of another platform |
| FR3092867A1 (en) * | 2019-02-19 | 2020-08-21 | Safran Aircraft Engines | PART OF TURBOMACHINE FOR AIRCRAFT WITH SEALING TABS |
| US10851661B2 (en) | 2017-08-01 | 2020-12-01 | General Electric Company | Sealing system for a rotary machine and method of assembling same |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19937577A1 (en) * | 1999-08-09 | 2001-02-15 | Abb Alstom Power Ch Ag | Frictional gas turbine component |
| DE10047307A1 (en) | 2000-09-25 | 2002-08-01 | Alstom Switzerland Ltd | sealing arrangement |
| JP2003035105A (en) * | 2001-07-19 | 2003-02-07 | Mitsubishi Heavy Ind Ltd | Gas turbine separating wall |
| US6854960B2 (en) * | 2002-06-24 | 2005-02-15 | Electric Boat Corporation | Segmented composite impeller/propeller arrangement and manufacturing method |
| WO2004016819A1 (en) * | 2002-08-16 | 2004-02-26 | Alstom Technology Ltd | Intermetallic material and use of said material |
| US6733234B2 (en) | 2002-09-13 | 2004-05-11 | Siemens Westinghouse Power Corporation | Biased wear resistant turbine seal assembly |
| US6883807B2 (en) | 2002-09-13 | 2005-04-26 | Seimens Westinghouse Power Corporation | Multidirectional turbine shim seal |
| US6893217B2 (en) * | 2002-12-20 | 2005-05-17 | General Electric Company | Methods and apparatus for assembling gas turbine nozzles |
| US20070048140A1 (en) * | 2005-08-24 | 2007-03-01 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
| US9133720B2 (en) * | 2007-12-28 | 2015-09-15 | United Technologies Corporation | Integrally bladed rotor with slotted outer rim |
| US9273563B2 (en) | 2007-12-28 | 2016-03-01 | United Technologies Corporation | Integrally bladed rotor with slotted outer rim |
| US8206087B2 (en) | 2008-04-11 | 2012-06-26 | Siemens Energy, Inc. | Sealing arrangement for turbine engine having ceramic components |
| GB2462810B (en) * | 2008-08-18 | 2010-07-21 | Rolls Royce Plc | Sealing means |
| US8322977B2 (en) * | 2009-07-22 | 2012-12-04 | Siemens Energy, Inc. | Seal structure for preventing leakage of gases across a gap between two components in a turbine engine |
| US9926790B2 (en) * | 2014-07-21 | 2018-03-27 | Rolls-Royce Corporation | Composite turbine components adapted for use with strip seals |
| US10107127B2 (en) * | 2014-07-31 | 2018-10-23 | United Technologies Corporation | Gas turbine engine with axial compressor having improved air sealing |
| US9759079B2 (en) | 2015-05-28 | 2017-09-12 | Rolls-Royce Corporation | Split line flow path seals |
| US10890078B1 (en) | 2017-06-12 | 2021-01-12 | Technetics Group Llc | Flexible seal assembly |
| US10718226B2 (en) | 2017-11-21 | 2020-07-21 | Rolls-Royce Corporation | Ceramic matrix composite component assembly and seal |
| CN113252246B (en) * | 2021-06-18 | 2021-11-05 | 中国科学院武汉岩土力学研究所 | Recoverable underground continuous wall seam crossing leakage detection device |
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|---|---|---|---|---|
| GB1580884A (en) * | 1977-08-03 | 1980-12-10 | Rolls Royce | Sealing means |
| GB2189253A (en) * | 1986-04-17 | 1987-10-21 | Central Electr Generat Board | Method of sealing joints and jointing compound therefor |
| EP0357984B1 (en) * | 1988-08-31 | 1993-05-05 | Westinghouse Electric Corporation | Gas turbine with film cooling of turbine vane shrouds |
| US5385760A (en) * | 1992-12-09 | 1995-01-31 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Process for the production of a composite coating of a functional substance in a metal matrix on the surface of an article |
| US5421704A (en) * | 1993-06-10 | 1995-06-06 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Inter-blade platform for a bladed disc of a turbomachine rotor |
| EP1013974A2 (en) * | 1998-12-25 | 2000-06-28 | Nichias Corporation | Sealing structure of a joint for three members |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE2108176A1 (en) * | 1971-02-20 | 1972-08-31 | Motoren Turbinen Union | Fastening of ceramic turbine blades |
| US4422827A (en) * | 1982-02-18 | 1983-12-27 | United Technologies Corporation | Blade root seal |
| US5104286A (en) * | 1991-02-08 | 1992-04-14 | Westinghouse Electric Corp. | Recirculation seal for a gas turbine exhaust diffuser |
| US5149250A (en) | 1991-02-28 | 1992-09-22 | General Electric Company | Gas turbine vane assembly seal and support system |
| FR2691749B1 (en) * | 1992-05-27 | 1994-07-22 | Snecma | SEALING DEVICE BETWEEN STAGES OF BLADES AND A TURNING DRUM IN PARTICULAR TO AVOID LEAKS AROUND THE STAGES OF RECTIFIER BLADES. |
| DE4432685C1 (en) * | 1994-09-14 | 1995-11-23 | Mtu Muenchen Gmbh | Starting cover for turbo=machine casing |
| US5531457A (en) * | 1994-12-07 | 1996-07-02 | Pratt & Whitney Canada, Inc. | Gas turbine engine feather seal arrangement |
| DE19520268A1 (en) | 1995-06-02 | 1996-12-05 | Abb Management Ag | Seal for contact faces of static elements |
| US5509669A (en) * | 1995-06-19 | 1996-04-23 | General Electric Company | Gas-path leakage seal for a gas turbine |
| US5586773A (en) * | 1995-06-19 | 1996-12-24 | General Electric Company | Gas-path leakage seal for a gas turbine made from metallic mesh |
| JP2941698B2 (en) * | 1995-11-10 | 1999-08-25 | 三菱重工業株式会社 | Gas turbine rotor |
| US5820338A (en) * | 1997-04-24 | 1998-10-13 | United Technologies Corporation | Fan blade interplatform seal |
-
1998
- 1998-10-19 DE DE19848103A patent/DE19848103A1/en not_active Withdrawn
-
1999
- 1999-10-06 EP EP99810907A patent/EP0995881B1/en not_active Expired - Lifetime
- 1999-10-06 DE DE59908238T patent/DE59908238D1/en not_active Expired - Lifetime
- 1999-10-12 US US09/414,968 patent/US6312218B1/en not_active Expired - Lifetime
- 1999-10-19 JP JP29691899A patent/JP4465067B2/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1580884A (en) * | 1977-08-03 | 1980-12-10 | Rolls Royce | Sealing means |
| GB2189253A (en) * | 1986-04-17 | 1987-10-21 | Central Electr Generat Board | Method of sealing joints and jointing compound therefor |
| EP0357984B1 (en) * | 1988-08-31 | 1993-05-05 | Westinghouse Electric Corporation | Gas turbine with film cooling of turbine vane shrouds |
| US5385760A (en) * | 1992-12-09 | 1995-01-31 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Process for the production of a composite coating of a functional substance in a metal matrix on the surface of an article |
| US5421704A (en) * | 1993-06-10 | 1995-06-06 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Inter-blade platform for a bladed disc of a turbomachine rotor |
| EP1013974A2 (en) * | 1998-12-25 | 2000-06-28 | Nichias Corporation | Sealing structure of a joint for three members |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7175387B2 (en) | 2001-09-25 | 2007-02-13 | Alstom Technology Ltd. | Seal arrangement for reducing the seal gaps within a rotary flow machine |
| EP1914389A1 (en) * | 2006-10-20 | 2008-04-23 | Siemens Aktiengesellschaft | Turbine blade with separated seal element |
| FR2998610A1 (en) * | 2012-11-29 | 2014-05-30 | Snecma | Rectifier for use in turboshaft engine, has suction groove forming area for maintaining seal when groove of platform cooperates with inner casing, where concave and suction grooves are positioned on respective sides of another platform |
| US10851661B2 (en) | 2017-08-01 | 2020-12-01 | General Electric Company | Sealing system for a rotary machine and method of assembling same |
| FR3092867A1 (en) * | 2019-02-19 | 2020-08-21 | Safran Aircraft Engines | PART OF TURBOMACHINE FOR AIRCRAFT WITH SEALING TABS |
Also Published As
| Publication number | Publication date |
|---|---|
| DE19848103A1 (en) | 2000-04-20 |
| EP0995881A3 (en) | 2002-03-13 |
| JP4465067B2 (en) | 2010-05-19 |
| US6312218B1 (en) | 2001-11-06 |
| JP2000120401A (en) | 2000-04-25 |
| DE59908238D1 (en) | 2004-02-12 |
| EP0995881B1 (en) | 2004-01-07 |
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