EP1149985A2 - Metallic shroud structure - Google Patents
Metallic shroud structure Download PDFInfo
- Publication number
- EP1149985A2 EP1149985A2 EP01110386A EP01110386A EP1149985A2 EP 1149985 A2 EP1149985 A2 EP 1149985A2 EP 01110386 A EP01110386 A EP 01110386A EP 01110386 A EP01110386 A EP 01110386A EP 1149985 A2 EP1149985 A2 EP 1149985A2
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- EP
- European Patent Office
- Prior art keywords
- wall
- hollow chamber
- housing structure
- segmented
- chamber structure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
Definitions
- the invention relates to a housing structure in metal construction for the rotor blade area axial flow through compressor and turbine stages, according to the generic term of claim 1.
- the housing structure should initially be sufficiently dimensionally stable and geometrically accurate. Thermal and mechanical influences should change the geometry as little as possible. The mostly hot working gas should generally only be applied to the inner wall of the structure; leakage losses through the structure should be minimized. In non-steady-state operation, it is advantageous if the changes in dimensions of the housing structure, in particular thermally induced, are matched in time and size to those of the bladed rotor.
- EP-B-0 728 258 relates to a cover band element of a turbine which, together with segments of the same type, forms the inner wall and part of the connecting structure to the outer wall of a wall structure.
- the segments In order to prevent the segments from getting into the blade tip raceway in places, they are connected to the outer area of the housing structure via a special hook-like geometry on the front and rear edges, which in some cases allow radial movement outwards. Since the inner contour often deviates from the circular shape with a tendency to form polygons, it is difficult to maintain a defined gap. The sealing of the segments with gaps and play is also structurally complex.
- EP-B-0 781 371 deals with an arrangement for the dynamic control of the blade tip play in gas turbines.
- the inner wall of the housing structure consists of radially outwardly movable, circumferentially overlapping, arc-shaped curved segments, the movement of which is limited radially inwardly by a circumferential housing structure holding its front and rear edges on one side in the manner of a hook.
- the segments are prestressed radially inwards against the stop by mechanical spring elements or by gas pressure.
- the rotor blades have wedge-shaped surfaces on the tip side, which generate a dynamic gas cushion during rapid rotation, the pressure of which should keep the wall segments at a defined, small distance from the blade tips.
- EP-B-0 616 113 relates to a gas turbine and a method for assembling a seal in this gas turbine. From this patent, it is known, inter alia, to use metallic honeycombs as inlet linings for labyrinth seals.
- honeycombs are soldered on one side to a flat, metallic support, usually in a closed, ring-shaped geometry, with their openings facing cutting-like, ring-shaped sealing tips.
- the deformation behavior of the ductile, thin, upright honeycomb walls accelerates any running-in process that may be necessary and protects the sealing tips.
- the open structure with a large number of chambers increases the sealing effect through flow deflection and swirling.
- Sandwich-like lightweight structures are preferably used in aircraft and boat construction, in which a relatively thick, light core with a high void volume, e.g. a honeycomb core, is connected and covered on both sides with thin, high-strength, closed walls.
- the walls When such a structure is bent, the walls become primarily open Loaded in tension or pressure in their plane, the core transfers the forces from wall to wall, especially thrust forces.
- the walls are preferably made of fiber composite, glued to the core and at least comparable in terms of their thickness and mechanical properties.
- the object of the invention in it, a housing structure in metal construction for the blade area of axial flow through compressor and turbine stages, which are characterized by a high Dimensional and shape accuracy under changing operating conditions and temperatures, high mechanical load bearing capacity, good thermal insulation as well as a minimal working fluid leakage due to the structure and through particularly small, little-changing gaps to the blade tips enables a high level of efficiency or a high level of load.
- connection structure arranged between the segmented inner wall and the closed, load-bearing outer wall and their integral integration.
- the connecting structure is designed as a filigree, light, hollow chamber structure that occupies practically the entire cavity between the inner and outer walls - for example as a honeycomb structure - and is connected to one or both walls by soldering.
- the "quasi-flat" connection of the walls makes it possible to impress the shape accuracy of the load-bearing outer wall in all operating states of the segmented inner wall. Warping or "polygonizing" of the inner contour can be avoided in this way.
- the solder joint Due to its "flat character", the solder joint is optimal in terms of mechanical strength and durability and has no negative influence on the material structure.
- the filigree connection structure is elastic enough to allow thermal expansion / contraction of the inner wall segments in the circumferential direction without critical constraining forces.
- the connection structure has a thermally insulating effect, which is due to its high void volume and can also be influenced by the selection of its material.Thus, the inner wall takes on the usually high temperature of the working gas, the outer wall can be kept significantly cooler, which is beneficial for its mechanical properties . Of course, the insulation effect is also good for the thermodynamic efficiency of the machine.
- the filigree connection structure is practically impermeable to gas in the circumferential and axial direction, so that additional sealing measures are not required. The leakage through the few, small expansion joints of the inner wall is of no importance.
- Preferred embodiments of the housing structure are characterized in the subclaims.
- the housing structure according to FIG. 1 is part of an axial compressor which runs from left to right to be flowed through on the right.
- the radially outer part of a guide vane can be seen 21 and a shroud-less blade 20.
- the outer wall 3 of the Housing structure extends over both blade areas, with the suspension the guide blade 21 in a form-fitting manner, i.e. is conventional.
- the housing structure according to the invention 1 is on the right in the figure, i.e. in the area of the blade 20, and comprises an inner wall 5, a hollow chamber structure 10 and that of the inner wall 5 opposite part of the outer wall 3, i.e. the right part by Flange.
- the inner wall 5 is to protect the blade tips when brushing provided with an inlet covering 9.
- the inner wall 5 including the inlet covering 9 is segmented, i.e. it has several, at least distributed over the circumference predominantly axially extending expansion joints 7 (see Fig. 2).
- the housing structure 1 represents an integral structure with a material connection of its elements 3, 5 and 10.
- the hollow chamber structure 10 is with the outer wall 3 and with the inner wall 5 soldered. It is also possible to use one of the hollow chamber structures to manufacture both walls in one piece and then to solder them to the other wall.
- FIG. 2 shows two different housing structures 1, 2 according to the invention in partial cross section, on the right or left side of a vertical, dash-dotted line in the middle of the drawing.
- the right housing structure 1 corresponds to that from FIG. 1, an expansion joint 7 running through the inner wall 5 and the inlet covering 9 being evident.
- the left housing structure 2 initially differs from the right one in that its inner wall 6 consists of a material that is easily deformable or removable by the blade tips over the entire thickness. This can be a porous metal without or with embedded plastic, graphite or other substances, for example in the form of a sintered structure.
- the outer wall 4 and the hollow chamber structure 11 have no special features compared to the corresponding positions 3 and 10.
- the inner wall 6 is provided with geometrically defined openings 8 distributed uniformly over the circumference.
- recesses 19 interact with the openings 8 and form recirculation chambers for part of the compressor flow in the area of the blade tips.
- the openings 8 and recesses 19 extend upstream in front of the blade entry edges, downstream they end behind the axial center of the blade and in front of the blade exit edges. This is familiar to the person skilled in the art and is therefore not shown separately.
- the recesses in the hollow chamber structure do not necessarily have to extend radially to the outer wall. It is conceivable to level the partially recessed hollow chamber structure with a filling material, ie to smooth it out in terms of flow technology. It may also be favorable to orient the longitudinal center planes of the openings and cutouts not radially, but rather inclined in the circumferential direction. All of this is clear to the person skilled in the art even without a separate illustration.
- FIG. 3 shows an example of three different hollow chamber structures 12, 13 and 14 in sections parallel to the inner and outer wall of the housing structure.
- On the left is a honeycomb structure with equilateral, hexagonal honeycombs, the coherent wall elements 15 of which are geometrically the same size and are at 120 ° angles to one another.
- the middle structure 13 has rectangular chambers, which are delimited by smaller wall elements 16 and larger wall elements 17 in a rectangular arrangement.
- the right structure 14 is similar to the left structure 12, but at 14 the hollow chambers have a round - instead of a hexagonal - shape. This results in wall elements 18 with locally different thicknesses.
- the hollow chamber structure 14 can be produced, for example, by mechanical or electrochemical drilling in an initially thick-walled solid material.
- the inner or outer wall can be produced in one piece with the hollow chamber structure, the other wall being integrated by soldering.
- the more delicate structures 12 and 13 are rather manufactured separately from sheet metal strips, expanded metal or the like.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Joining Of Building Structures In Genera (AREA)
Abstract
Description
Die Erfindung betrifft eine Gehäusestruktur in Metallbauweise für den Laufschaufelbereich
von axial durchströmten Verdichter- und Turbinenstufen, gemäß dem Oberbegriff
des Patentanspruchs 1.The invention relates to a housing structure in metal construction for the rotor blade area
axial flow through compressor and turbine stages, according to the generic term
of
Für die strömungstechnischen Eigenschaften von Verdichter- und Turbinenstufen ist
es sehr wichtig, dass der Radialspalt zwischen den Laufschaufelspitzen und dem
Gehäuse möglichst klein und möglichst konstant gehalten wird. Dafür sollte die Gehäusestruktur
zunächst ausreichend formstabil und geometrisch genau sein. Thermische
und mechanische Einflüsse sollten die Geometrie möglichst wenig verändern.
Mit dem zumeist heißen Arbeitsgas sollte i.w. nur die Innenwand der Struktur beaufschlagt
sein, Leckageverluste durch die Struktur sind zu minimieren. Im instationären
Betrieb ist es vorteilhaft, wenn die insbesondere thermisch induzierte Maßänderungen
der Gehäusestruktur zeitlich und größenmäßig an diejenigen des beschaufelten
Rotors angeglichen sind. Da sich mechanische Kontakte zwischen den Schaufelspitzen
und dem Gehäuse unter besonderen Belastungen kaum vermeiden lassen,
sollte die Innenwand der Gehäusestruktur zumindest schaufelspitzenseitig verformbar/nachgiebig
bzw. abradierbar ausgeführt sein.
Die EP-B-0 728 258 betrifft ein Deckbandsement einer Turbine, welches zusammen
mit gleichartigen Segmenten die Innenwand und einen Teil der Verbindungsstruktur
zur Außenwand einer Wandstruktur bildet. Infolge von Temperaturunterschieden zwischen
Innen- und gekühlter Außenseite der Segmente im Betrieb sowie infolge von
unterschiedlichem Materialverhalten des Grundmaterials und einer in der Regel vorhandenen
Beschichtung tendieren die Segmente dazu, ihre Krümmung zu verändern.
Um zu verhindern, dass die Segmente dabei stellenweise in die Laufbahn der Schaufelspitzen
geraten, sind sie über eine spezielle, hakenartige Geometrie an Vorder-
und Hinterkante mit dem Außenbereich der Gehäusestruktur verbunden, welche
stellenweise eine Radialbewegung nach außen zulässt. Da die Innenkontur somit
häufig von der Kreisform mit Tendenz zur Polygonbildung abweicht, ist eine definierte
Spalthaltung schwierig. Die Abdichtung der spalt- und spielbehafteten Segmente ist
konstruktiv ebenfalls aufwendig. For the fluidic properties of compressor and turbine stages, it is very important that the radial gap between the blade tips and the housing is kept as small and constant as possible. For this, the housing structure should initially be sufficiently dimensionally stable and geometrically accurate. Thermal and mechanical influences should change the geometry as little as possible. The mostly hot working gas should generally only be applied to the inner wall of the structure; leakage losses through the structure should be minimized. In non-steady-state operation, it is advantageous if the changes in dimensions of the housing structure, in particular thermally induced, are matched in time and size to those of the bladed rotor. Since mechanical contacts between the blade tips and the housing can hardly be avoided under special loads, the inner wall of the housing structure should at least be designed to be deformable / resilient or abradable on the blade tip side.
EP-B-0 728 258 relates to a cover band element of a turbine which, together with segments of the same type, forms the inner wall and part of the connecting structure to the outer wall of a wall structure. As a result of temperature differences between the inside and the cooled outside of the segments during operation, as well as due to different material behavior of the base material and a coating which is usually present, the segments tend to change their curvature. In order to prevent the segments from getting into the blade tip raceway in places, they are connected to the outer area of the housing structure via a special hook-like geometry on the front and rear edges, which in some cases allow radial movement outwards. Since the inner contour often deviates from the circular shape with a tendency to form polygons, it is difficult to maintain a defined gap. The sealing of the segments with gaps and play is also structurally complex.
Die EP-B-0 781 371 behandelt eine Anordnung zur dynamischen Kontrolle des
Schaufelspitzenspiels in Gasturbinen. Die Innenwand der Gehäusestruktur besteht
aus radial nach außen beweglichen, in Umfangsrichtung überlappenden, kreisbogenförmig
gekrümmten Segmenten, deren Bewegung radial nach innen durch eine ihre
Vorder- und Hinterkante hakenartig einseitig haltende, umlaufende Gehäusestruktur
begrenzt wird. Die Segmente werden durch mechanische Federelemente oder durch
Gasdruck radial nach innen gegen Anschlag vorgespannt. Die Laufschaufeln weisen
spitzenseitig Keilflächen auf, welche bei schneller Rotation ein dynamisches Gaspolster
erzeugen, dessen Druck die Wandsegmente in einem definierten, kleinen Abstand
zu den Schaufelspitzen halten soll. Dabei muss sich ein Gleichgewicht zwischen innerer
Gaskraft und äußerer Federkraft einstellen, das die Segmente in Balance hält.
Ein solches System erscheint sehr störanfällig, schwer kalkulierbar und schwingungsgefährdet.
Die Haltestruktur der Segmente ist dem Arbeitsgas ausgesetzt und
somit ggf. thermisch hoch belastet, wobei sie auch eine erhebliche Wärmemenge zur
Außenwand der Struktur leitet.
Die EP-B-0 616 113 betrifft eine Gasturbine und ein Verfahren zur Montage einer
Dichtung in dieser Gasturbine. Aus dieser Patentschrift ist es u.a. bekannt, metallische
Honigwaben als Einlaufbeläge für Labyrinthdichtungen zu verwenden. Die Waben
sind einseitig auf einen flächigen, metallischen Träger gelötet, in der Regel in
ringförmig geschlossener Geometrie, wobei ihre Öffnungen schneidenartigen, ringförmigen
Dichtspitzen zugewandt sind. Das Verformungsverhalten der duktilen, dünnen,
hochkant stehenden Wabenwände beschleunigt einen ggf. erforderlichen Einlaufvorgang
und schont die Dichtspitzen. Die offene Struktur mit einer Vielzahl von
Kammern erhöht die Dichtwirkung durch Strömungsumlenkung und -verwirbelung.
Vorzugsweise im Flugzeug- und Bootsbau werden sandwichartige Leichtbaustrukturen
verwendet, bei denen ein relativ dicker, leichter Kern mit einem hohen Leervolumenanteil,
z.B. ein Wabenkern, beidseitig mit dünnen, hochfesten, geschlossenen
Wänden verbunden und abgedeckt wird Bei Biegung einer solchen Struktur werden
die Wände primär auf Zug oder Druck in ihrer Ebene belastet, der Kern überträgt die
Kräfte von Wand zu Wand, insbesondere Schubkräfte. Die Wände sind bevorzugt in
Faserverbundbauweise ausgeführt, mit dem Kern verklebt und hinsichtlich ihrer Dicke
und mechanischen Eigenschaften zumindest vergleichbar.EP-B-0 781 371 deals with an arrangement for the dynamic control of the blade tip play in gas turbines. The inner wall of the housing structure consists of radially outwardly movable, circumferentially overlapping, arc-shaped curved segments, the movement of which is limited radially inwardly by a circumferential housing structure holding its front and rear edges on one side in the manner of a hook. The segments are prestressed radially inwards against the stop by mechanical spring elements or by gas pressure. The rotor blades have wedge-shaped surfaces on the tip side, which generate a dynamic gas cushion during rapid rotation, the pressure of which should keep the wall segments at a defined, small distance from the blade tips. A balance must be struck between the internal gas force and the external spring force that keeps the segments in balance. Such a system appears to be very susceptible to faults, difficult to calculate and prone to vibrations. The holding structure of the segments is exposed to the working gas and thus possibly subjected to high thermal loads, whereby it also conducts a considerable amount of heat to the outer wall of the structure.
EP-B-0 616 113 relates to a gas turbine and a method for assembling a seal in this gas turbine. From this patent, it is known, inter alia, to use metallic honeycombs as inlet linings for labyrinth seals. The honeycombs are soldered on one side to a flat, metallic support, usually in a closed, ring-shaped geometry, with their openings facing cutting-like, ring-shaped sealing tips. The deformation behavior of the ductile, thin, upright honeycomb walls accelerates any running-in process that may be necessary and protects the sealing tips. The open structure with a large number of chambers increases the sealing effect through flow deflection and swirling. Sandwich-like lightweight structures are preferably used in aircraft and boat construction, in which a relatively thick, light core with a high void volume, e.g. a honeycomb core, is connected and covered on both sides with thin, high-strength, closed walls. When such a structure is bent, the walls become primarily open Loaded in tension or pressure in their plane, the core transfers the forces from wall to wall, especially thrust forces. The walls are preferably made of fiber composite, glued to the core and at least comparable in terms of their thickness and mechanical properties.
Ausgehend von dem genannten Stand der Technik besteht die Aufgabe der Erfindung darin, eine Gehäusestruktur in Metallbauweise für den Laufschaufelbereich von axial durchströmten Verdichter- und Turbinenstufen zu schaffen, die sich durch eine hohe Maß- und Formgenauigkeit unter wechselnden Betriebsbedingungen und Temperaturen, eine hohe mechanische Lastaufnahmefähigkeit, eine gute thermische Isolationswirkung sowie eine minimale Arbeitsfluidleckage durch die Struktur auszeichnet und durch besonders kleine, sich wenig ändernde Spalte zu den Laufschaufelspitzen einen hohen Stufenwirkungsgrad bzw. eine hohe Stufenbelastung ermöglicht.Based on the prior art mentioned, the object of the invention in it, a housing structure in metal construction for the blade area of axial flow through compressor and turbine stages, which are characterized by a high Dimensional and shape accuracy under changing operating conditions and temperatures, high mechanical load bearing capacity, good thermal insulation as well as a minimal working fluid leakage due to the structure and through particularly small, little-changing gaps to the blade tips enables a high level of efficiency or a high level of load.
Diese Aufgabe wird durch die in Anspruch 1 gekennzeichneten Merkmale gelöst, in
Verbindung mit den gattungsbildenden Merkmalen in dessen Oberbegriff.
Die Erfindung ist somit in der zwischen der segmentierten Innenwand und der geschlossenen,
tragenden Außenwand angeordneten Verbindungsstruktur und deren
stoffschlüssiger Integration zu sehen. Die Verbindungsstruktur ist als filigrane, leichte,
praktisch den gesamten Hohlraum zwischen Innen- und Außenwand einnehmende
Hohlkammerstruktur ausgeführt - beispielsweise als Honigwabenstruktur - und mit
einer oder beiden Wänden durch Löten verbunden. Durch die "quasi-flächige" Verbindung
der Wände ist es möglich, die Formgenauigkeit der tragenden Außenwand in
allen Betriebszuständen der segmentierten Innenwand aufzuprägen. Ein Verwölben
bzw. "Polygonisieren" der Innenkontur lässt sich so vermeiden. Die Lötverbindung ist
durch ihren "flächigen Charakter" optimal hinsichtlich mechanischer Festigkeit sowie
Dauerhaftigkeit und hat keinen negativen Einfluss auf das Werkstoffgefüge. Andererseits
ist die filigrane Verbindungsstruktur elastisch genug, um thermische Dehnungen
/Kontraktionen der Innenwandsegmente in Umfangsrichtung ohne kritische
Zwangskräfte zuzulassen. Die Verbindungsstruktur wirkt thermisch isolierend, was
durch ihren hohen Leervolumenanteil bedingt ist und durch die Auswahl ihres Werkstoffes
ebenfalls beeinflussbar ist Somit nimmt die Innenwand etwa die meist hohe
Temperatur des Arbeitsgases an, die Außenwand kann deutlich kühler gehalten werden,
was günstig für ihre mechanischen Eigenschaften ist. Natürlich ist die Isolationswirkung
auch gut für den thermodynamischen Wirkungsgrad der Maschine. Die
filigrane Verbindungsstruktur ist in Umfangs- und Axialrichtung praktisch gasundurchlässig,
so dass zusätzliche Dichtungsmaßnahmen entfallen. Die Leckage durch
die wenigen, kleinen Dehnfugen der Innenwand ist dabei ohne jede Bedeutung.
In den Unteransprüchen sind bevorzugte Ausgestaltungen der Gehäusestruktur gekennzeichnet.This object is achieved by the features characterized in
The invention can thus be seen in the connection structure arranged between the segmented inner wall and the closed, load-bearing outer wall and their integral integration. The connecting structure is designed as a filigree, light, hollow chamber structure that occupies practically the entire cavity between the inner and outer walls - for example as a honeycomb structure - and is connected to one or both walls by soldering. The "quasi-flat" connection of the walls makes it possible to impress the shape accuracy of the load-bearing outer wall in all operating states of the segmented inner wall. Warping or "polygonizing" of the inner contour can be avoided in this way. Due to its "flat character", the solder joint is optimal in terms of mechanical strength and durability and has no negative influence on the material structure. On the other hand, the filigree connection structure is elastic enough to allow thermal expansion / contraction of the inner wall segments in the circumferential direction without critical constraining forces. The connection structure has a thermally insulating effect, which is due to its high void volume and can also be influenced by the selection of its material.Thus, the inner wall takes on the usually high temperature of the working gas, the outer wall can be kept significantly cooler, which is beneficial for its mechanical properties . Of course, the insulation effect is also good for the thermodynamic efficiency of the machine. The filigree connection structure is practically impermeable to gas in the circumferential and axial direction, so that additional sealing measures are not required. The leakage through the few, small expansion joints of the inner wall is of no importance.
Preferred embodiments of the housing structure are characterized in the subclaims.
Die Erfindung wird anschließend anhand der Figuren noch näher erläutert. Dabei
zeigen in vereinfachter, nicht maßstäblicher Darstellung:
Die Gehäusestruktur gemäß Figur 1 ist Teil eines Axialverdichters, der von links nach
rechts durchströmt werden soll. Man erkennt den radial äußeren Teil einer Leitschaufel
21 sowie einer -deckbandlosen- Laufschaufel 20. Die Außenwand 3 der
Gehäusestruktur erstreckt sich über beide Schaufelbereiche, wobei die Aufhängung
der Leitschaufel 21 formschlüssig, d.h. konventionell ist. Die erfindungsgemäße Gehäusestruktur
1 befindet sich in der Figur rechts, d.h. im Bereich der Laufschaufel
20, und umfasst eine Innenwand 5, eine Hohlkammerstruktur 10 sowie den der Innenwand
5 gegenüberliegenden Teil der Außenwand 3, d.h. den rechten Teil bis zum
Flansch. Die Innenwand 5 ist zur Schonung der Laufschaufelspitzen beim Anstreifen
mit einem Einlaufbelag 9 versehen. Die Innenwand 5 einschließlich des Einlaufbelages
9 ist segmentiert, d.h. sie weist über den Umfang verteilt mehrere, zumindest
vorwiegend axial verlaufende Dehnfugen 7 auf (siehe Fig. 2). Die Gehäusestruktur 1
stellt ein integrales Gebilde mit stoffschlüssiger Verbindung seiner Elemente 3, 5 und
10 dar. Die Hohlkammerstruktur 10 ist dabei mit der Außenwand 3 und mit der Innenwand
5 verlötet. Es ist ebenso möglich, die Hohlkammerstruktur mit einer der
beiden Wände einstückig zu fertigen und danach mit der anderen Wand zu verlöten. The housing structure according to FIG. 1 is part of an axial compressor which runs from left to right
to be flowed through on the right. The radially outer part of a guide vane can be seen
21 and a shroud-less blade 20. The
Figur 2 zeigt zwei unterschiedliche, erfindungsgemäße Gehäusestrukturen 1,2 im
Teilquerschnitt, auf der rechten bzw. linken Seite einer vertikalen, strichpunktierten
Linie in der Mitte der Zeichnung. Die rechte Gehäusestruktur 1 entspricht derjenigen
aus Figur 1, wobei eine durch die Innenwand 5 und den Einlaufbelag 9 verlaufende
Dehnfuge 7 zu erkennen ist.
Die linke Gehäusestruktur 2 unterscheidet sich von der rechten zunächst dadurch,
dass ihre Innenwand 6 über die gesamte Dicke aus einem von den Schaufelspitzen
problemlos verformbaren bzw. abtragbaren Material besteht. Dieses kann ein poröses
Metall ohne oder mit Einlagerungen von Kunststoff, Graphit oder anderen Stoffen
sein, beispielsweise in Form einer gesinterten Struktur. Die Außenwand 4 und die
Hohlkammerstruktur 11 weisen keine Besonderheiten gegenüber den entsprechenden
Positionen 3 und 10 auf. Allerdings ist als spezielle, konstruktive Maßnahme ein
sogenanntes "Casing Treatment" erkennbar, welches bei Verdichtern die Aerodynamik
verbessern kann im Sinne einer Erhöhung des Wirkungsgrades bzw. der Pumpgrenze.
Zu diesem Zweck ist die Innwand 6 mit gleichmäßig über den Umfang verteilten,
geometrisch definierten Durchbrüchen 8 versehen. In der Hohlkammerstruktur
11 wirken Aussparungen 19 mit den Durchbrüchen 8 zusammen und bilden Rezirkulationskammern
für einen Teil der Verdichterströmung im Schaufelspitzenbereich.
In axialer Richtung erstrecken sich die Durchbrüche 8 und Aussparungen 19 stromaufwärts
bis vor die Schaufeleintrittskanten, stromabwärts enden sie hinter der axialen
Schaufelmitte und vor den Schaufelaustrittskanten. Dies ist dem Fachmann
geläufig und daher nicht gesondert dargestellt. Die Aussparungen in der Hohlkammerstruktur
müssen nicht zwingend radial bis zur Außenwand reichen. Es ist denkbar,
die teilweise ausgesparte Hohlkammerstruktur mit einem Füllmaterial einzuebnen,
d.h. strömungstechnisch zu glätten. Es kann auch günstig sein, die Längsmittelebenen
der Durchbrüche und Aussparungen nicht radial, sondern in Umfangsrichtung
geneigt zu orientieren. All dies ist für den Fachmann auch ohne gesonderte
Darstellung klar.FIG. 2 shows two
The
Figur 3 zeigt beispielhaft drei verschiedene Hohlkammerstrukturen 12,13 und 14 in
Schnitten parallel zur Innen- bzw. Außenwand der Gehäusestruktur. Links ist eine
Honigwabenstruktur mit gleichseitigen, sechseckigen Waben zu sehen, deren zusammenhängende
Wandelemente 15 somit geometrisch gleich groß sind und in
120°-Winkeln zueinander stehen.
Die mittlere Struktur 13 weist rechteckige Kammern auf, welche von kleineren
Wandelementen 16 und größeren Wandelemente 17 in rechtwinkliger Anordnung
begrenzt werden.
Die rechte Struktur 14 ähnelt der linken Struktur 12, jedoch haben bei 14 die Hohlkammern
eine runde - statt einer sechseckigen - Form. Somit ergeben sich Wandelemente
18 mit örtlich unterschiedlicher Dicke. Die Hohlkammerstruktur 14 kann
beispielsweise durch mechanisches oder elektrochemisches Bohren in einem zunächst
dickwandigen Vollmaterial erzeugt werden. Bezogen auf die erfindungsgemäße
Gehäusestruktur kann auf diese Weise die innere oder äußere Wand einstückig
mit der Hohlkammerstruktur gefertigt werden, wobei die jeweils andere Wand durch
Löten integriert wird. Die filigraneren Strukturen 12 und 13 werden eher separat aus
Blechstreifen, Streckmetall o. ä. gefertigt.FIG. 3 shows an example of three different
The
The
Claims (6)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10020673 | 2000-04-27 | ||
DE10020673A DE10020673C2 (en) | 2000-04-27 | 2000-04-27 | Ring structure in metal construction |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1149985A2 true EP1149985A2 (en) | 2001-10-31 |
EP1149985A3 EP1149985A3 (en) | 2003-09-17 |
EP1149985B1 EP1149985B1 (en) | 2004-12-08 |
Family
ID=7640124
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01110386A Expired - Lifetime EP1149985B1 (en) | 2000-04-27 | 2001-04-26 | Metallic shroud structure |
Country Status (5)
Country | Link |
---|---|
US (1) | US6537020B2 (en) |
EP (1) | EP1149985B1 (en) |
JP (1) | JP4572042B2 (en) |
AT (1) | ATE284480T1 (en) |
DE (2) | DE10020673C2 (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
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GB2362432B (en) * | 2000-05-19 | 2004-06-09 | Rolls Royce Plc | Tip treatment bars in a gas turbine engine |
WO2008011864A1 (en) * | 2006-07-26 | 2008-01-31 | Mtu Aero Engines Gmbh | Gas turbine with a peripheral ring segment comprising a recirculation channel |
EP2050931A2 (en) * | 2007-10-16 | 2009-04-22 | United Technologies Corporation | Systems and methods involving abradable air seals |
EP2728124A1 (en) * | 2012-10-30 | 2014-05-07 | MTU Aero Engines GmbH | Turbine ring and turbomachine |
WO2014207054A1 (en) * | 2013-06-28 | 2014-12-31 | Siemens Aktiengesellschaft | Gas turbine and heat shield for a gas turbine |
US10760527B2 (en) | 2009-08-17 | 2020-09-01 | Pratt & Whitney Canada Corp. | Gas turbine engine exhaust mixer |
US11125101B2 (en) | 2017-07-04 | 2021-09-21 | MTU Aero Engines AG | Turbomachine sealing ring |
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GB0206136D0 (en) * | 2002-03-15 | 2002-04-24 | Rolls Royce Plc | Improvements in or relating to cellular materials |
US6935836B2 (en) * | 2002-06-05 | 2005-08-30 | Allison Advanced Development Company | Compressor casing with passive tip clearance control and endwall ovalization control |
DE102004010236A1 (en) * | 2004-03-03 | 2005-09-15 | Mtu Aero Engines Gmbh | Metal ring structure for sealing gap between rotor blade tips and stator in e.g. gas turbine, has inner wall formed by metal fabric or felt |
JP2008180149A (en) * | 2007-01-24 | 2008-08-07 | Mitsubishi Heavy Ind Ltd | Vane structure of gas turbine and gas turbine |
US8038388B2 (en) * | 2007-03-05 | 2011-10-18 | United Technologies Corporation | Abradable component for a gas turbine engine |
EP2075416B1 (en) * | 2007-12-27 | 2011-05-18 | Techspace Aero | Method for manufacturing a turboshaft engine element and device obtained using same |
US9062565B2 (en) * | 2009-12-31 | 2015-06-23 | Rolls-Royce Corporation | Gas turbine engine containment device |
JP4916560B2 (en) | 2010-03-26 | 2012-04-11 | 川崎重工業株式会社 | Gas turbine engine compressor |
GB201016335D0 (en) * | 2010-09-29 | 2010-11-10 | Rolls Royce Plc | Endwall component for a turbine stage of a gas turbine engine |
EP2679777A1 (en) * | 2012-06-28 | 2014-01-01 | Alstom Technology Ltd | Compressor for a gas turbine and method for repairing and/or changing the geometry of and/or servicing said compressor |
DE202013010937U1 (en) * | 2013-11-30 | 2015-03-02 | Oerlikon Leybold Vacuum Gmbh | Rotor disc and rotor for a vacuum pump |
DE102015224160A1 (en) | 2015-12-03 | 2017-06-08 | MTU Aero Engines AG | Inlet lining for an external air seal of a turbomachine |
US10422348B2 (en) * | 2017-01-10 | 2019-09-24 | General Electric Company | Unsymmetrical turbofan abradable grind for reduced rub loads |
DE102018208040A1 (en) * | 2018-05-23 | 2019-11-28 | MTU Aero Engines AG | Seal carrier and turbomachine |
US11674396B2 (en) | 2021-07-30 | 2023-06-13 | General Electric Company | Cooling air delivery assembly |
US11674405B2 (en) | 2021-08-30 | 2023-06-13 | General Electric Company | Abradable insert with lattice structure |
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EP0728258B1 (en) | 1993-11-08 | 1998-06-03 | United Technologies Corporation | Turbine shroud segment |
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EP0781371B1 (en) | 1994-08-31 | 1998-12-23 | United Technologies Corporation | Dynamic control of tip clearance |
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JP2820655B2 (en) * | 1995-04-28 | 1998-11-05 | 三菱重工業株式会社 | Segment type honeycomb brazing method and honeycomb brazing jig |
US5951892A (en) * | 1996-12-10 | 1999-09-14 | Chromalloy Gas Turbine Corporation | Method of making an abradable seal by laser cutting |
JPH1113404A (en) * | 1997-06-25 | 1999-01-19 | Mitsubishi Heavy Ind Ltd | Blade and sealing mechanism for moving blade |
-
2000
- 2000-04-27 DE DE10020673A patent/DE10020673C2/en not_active Expired - Fee Related
-
2001
- 2001-04-26 AT AT01110386T patent/ATE284480T1/en not_active IP Right Cessation
- 2001-04-26 DE DE2001504737 patent/DE50104737D1/en not_active Expired - Lifetime
- 2001-04-26 EP EP01110386A patent/EP1149985B1/en not_active Expired - Lifetime
- 2001-04-27 JP JP2001131882A patent/JP4572042B2/en not_active Expired - Fee Related
- 2001-04-27 US US09/844,012 patent/US6537020B2/en not_active Expired - Fee Related
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EP0616113B1 (en) | 1993-03-01 | 1998-07-01 | General Electric Company | Gas turbine engine and method of assembling a seal in said gas turbine engine |
EP0728258B1 (en) | 1993-11-08 | 1998-06-03 | United Technologies Corporation | Turbine shroud segment |
EP0781371B1 (en) | 1994-08-31 | 1998-12-23 | United Technologies Corporation | Dynamic control of tip clearance |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2362432B (en) * | 2000-05-19 | 2004-06-09 | Rolls Royce Plc | Tip treatment bars in a gas turbine engine |
WO2008011864A1 (en) * | 2006-07-26 | 2008-01-31 | Mtu Aero Engines Gmbh | Gas turbine with a peripheral ring segment comprising a recirculation channel |
US8092148B2 (en) | 2006-07-26 | 2012-01-10 | Mtu Aero Engines Gmbh | Gas turbine having a peripheral ring segment including a recirculation channel |
EP2050931A2 (en) * | 2007-10-16 | 2009-04-22 | United Technologies Corporation | Systems and methods involving abradable air seals |
EP2050931A3 (en) * | 2007-10-16 | 2009-12-02 | United Technologies Corporation | Systems and methods involving abradable air seals |
US10760527B2 (en) | 2009-08-17 | 2020-09-01 | Pratt & Whitney Canada Corp. | Gas turbine engine exhaust mixer |
EP2728124A1 (en) * | 2012-10-30 | 2014-05-07 | MTU Aero Engines GmbH | Turbine ring and turbomachine |
US9963993B2 (en) | 2012-10-30 | 2018-05-08 | MTU Aero Engines AG | Turbine ring and turbomachine |
WO2014207054A1 (en) * | 2013-06-28 | 2014-12-31 | Siemens Aktiengesellschaft | Gas turbine and heat shield for a gas turbine |
US11125101B2 (en) | 2017-07-04 | 2021-09-21 | MTU Aero Engines AG | Turbomachine sealing ring |
Also Published As
Publication number | Publication date |
---|---|
DE50104737D1 (en) | 2005-01-13 |
EP1149985A3 (en) | 2003-09-17 |
US20010048876A1 (en) | 2001-12-06 |
DE10020673C2 (en) | 2002-06-27 |
EP1149985B1 (en) | 2004-12-08 |
ATE284480T1 (en) | 2004-12-15 |
US6537020B2 (en) | 2003-03-25 |
JP4572042B2 (en) | 2010-10-27 |
JP2002004806A (en) | 2002-01-09 |
DE10020673A1 (en) | 2001-10-31 |
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