EP1149985B1 - Metallic shroud structure - Google Patents
Metallic shroud structure Download PDFInfo
- Publication number
- EP1149985B1 EP1149985B1 EP01110386A EP01110386A EP1149985B1 EP 1149985 B1 EP1149985 B1 EP 1149985B1 EP 01110386 A EP01110386 A EP 01110386A EP 01110386 A EP01110386 A EP 01110386A EP 1149985 B1 EP1149985 B1 EP 1149985B1
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- EP
- European Patent Office
- Prior art keywords
- wall
- hollow chamber
- segmented
- chamber structure
- structure according
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- 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
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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
- F01D11/08—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 ring structure in metal construction for the blade area axial flow through compressor and turbine stages, according to the generic term of claim 1.
- the wall structure should initially be sufficiently dimensionally stable and be geometrically accurate. Thermal and mechanical influences should affect the geometry change as little as possible. With the mostly hot working gas, i.w. only the inside of the structure must be acted on, leakage losses through the structure are to be minimized. In transient operation, it is advantageous if the particular thermally induced dimensional changes in the wall structure in terms of time and size those of the bladed rotor are aligned. Because there are mechanical contacts between the blade tips and the wall structure under special loads can hardly be avoided, the inside of the wall structure should at least blade tip deformable / resilient or abradable.
- EP-B-0 728 258 relates to a shroud element of a turbine, which together with similar segments the inner wall and part of the connecting structure to the outer wall of a wall structure. Due to temperature differences between Inside and cooled outside of the segments in operation and as a result of different material behavior of the base material and one as a rule The existing coating tends to change the curvature of the segments. To prevent the segments from getting into the blade tip raceway they have a special, hook-like geometry on the front and Trailing edge connected to the outer area of the housing structure, which radial outward movement in places. Because the inner contour often deviates from the circular shape with a tendency to form polygons, is a defined one Difficult to keep gaps. The sealing of the segments with gaps and play is constructively also complex.
- EP-B-0 781 371 deals with an arrangement for dynamic control of the Blade tip play in gas turbines.
- the inner wall of the housing structure is there from radially outward-moving, circular arc-shaped overlapping in the circumferential direction curved segments whose movement radially inwards through one of their Front and rear edge hook-like, surrounding housing structure on one side is limited.
- the segments are made by mechanical spring elements or by Gas pressure biased radially inwards against the stop.
- the blades have wedge surfaces on the tip side, which, when rotating faster, a dynamic gas cushion generate, the pressure of the wall segments at a defined, small distance should stick to the blade tips.
- the holding structure of the segments is exposed to the working gas and thus possibly subjected to high thermal loads, whereby they also contain a considerable amount of heat leads to the outer wall of the structure.
- EP-B-0 616 113 relates to a gas turbine and a method for assembling one Seal in this gas turbine. From this patent, it is i.a. known, metallic Honeycombs to be used as inlet coverings for labyrinth seals.
- the honeycomb are soldered on one side to a flat, metallic carrier, usually in ring-shaped closed geometry, its openings being cutting-like, ring-shaped Sealing tips are facing.
- the deformation behavior of the ductile, thin, Upright honeycomb walls accelerate any necessary running-in process and protects the sealing tips.
- the open structure with a variety of Chambers increase the sealing effect through flow deflection and swirling.
- Sandwich-like lightweight structures are preferred in aircraft and boat construction uses a relatively thick, light core with a high empty volume, e.g. a honeycomb core, with thin, high-strength, closed on both sides Walls connected and covered
- a relatively thick, light core with a high empty volume e.g. a honeycomb core
- thin, high-strength closed on both sides Walls connected and covered
- the walls are preferred in Fiber composite construction, glued to the core and in terms of its thickness and mechanical properties at least comparable.
- DE-A-15 51 183 relates to composite sealing components for gas turbine engines. Such components are also used in specialist circles as jacket rings or liners referred to and are arranged around blade rings, in particular with the function of the blade tip seal. With regard to easy assembly and unimpeded thermal expansion, the liners are mostly segmented and left unchanged arranged by expansion joints.
- the sealing components according to this published specification are in sandwich construction with a metallic honeycomb core and with these metallic walls / sheets covering on both sides, hence the expression "Composed”.
- the inner, abradable wall (layer 58 ') can on the Angled edges of the sealing component up to the outer wall (rear layer 50 ') and connected to the latter by soldering (60) (see page 9 from the eighth last line).
- the sealing components form either curved segments, such as shown in the figures, or complete rings (see page 10, lines 1 to 6).
- the outer and inner walls are inevitably interrupted, i.e. segmented, in the second case none of the walls is segmented.
- the Indicates a direct soldering of the outer and inner wall in the edge area there is no evidence of the type of connection between the walls and the Honeycomb core.
- the outer wall is with flanges (52,53) so that they can be hung on the engine housing (11).
- the outer wall (rear layer) of each sealing component is therefore not a housing wall.
- the design of the core layer is limited to honeycomb material.
- the object of the invention is based on the cited prior art in it, a ring structure in metal construction for the blade area from 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.
- the invention is thus in the combination of a segmented inner wall, one closed, formed by a housing wall, supporting outer wall, one connecting structure arranged between the walls and from their material connection See integration by soldering.
- the connection structure is in itself known as filigree, light, practically the entire cavity between Hollow chamber structure occupying inner and outer wall - for example as a honeycomb structure - and connected to one or both walls by soldering. Due to the "quasi-flat" connection of the walls, it is possible to achieve dimensional accuracy the load-bearing outer wall in all operating states of the segmented Imprint on the inner wall. A warping or "polygonizing" of the inner contour leaves avoid yourself.
- the solder connection is optimal due to its "flat character" in terms of mechanical strength and durability and has no negative Influence on the material structure.
- the filigree connection structure elastic enough to accommodate thermal expansions / contractions of the inner wall segments in the circumferential direction without allowing critical constraining forces.
- the connection structure has a thermally insulating effect, which is due to its high empty volume and can also be influenced by the selection of its material the inner wall assumes the mostly high temperature of the working gas, the outer wall can be kept significantly cooler, which is beneficial for their mechanical Properties is. 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 on the inner wall are 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 can be easily deformed or removed 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 cutouts 19 extend upstream to 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 can 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.
Abstract
Description
Die Erfindung betrifft eine Ringstruktur in Metallbauweise für den Laufschaufelbereich
von axial durchströmten Verdichter- und Turbinenstufen, gemäß dem Oberbegriff
des Patentanspruchs 1.The invention relates to a ring structure in metal construction for the blade area
axial flow through compressor and turbine stages, according to the generic term
of
Für die strömungstechnischen Eigenschaften von axial durchströmten Verdichterund Turbinenstufen ist es sehr wichtig, dass der Radialspalt zwischen den Laufschaufelspitzen und der äußeren Strömungskanalwand möglichst klein und möglichst konstant gehalten wird. Dafür sollte die Wandstruktur 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 Innenseite der Struktur beaufschlagt sein, Leckageverluste durch die Struktur sind zu minimieren. Im instationären Betrieb ist es vorteilhaft, wenn die insbesondere thermisch induzierte Maßänderungen der Wandstruktur zeitlich und größenmäßig an diejenigen des beschaufelten Rotors angeglichen sind. Da sich mechanische Kontakte zwischen den Schaufelspitzen und der Wandstruktur unter besonderen Belastungen kaum vermeiden lassen, sollte die Innenseite der Wandstruktur zumindest schaufelspitzenseitig verformbar/nachgiebig bzw. abradierbar ausgeführt sein.For the fluidic properties of compressors with axial flow At turbine stages it is very important that the radial gap between the blade tips and the outer flow channel wall as small and constant as possible is held. For this, the wall structure should initially be sufficiently dimensionally stable and be geometrically accurate. Thermal and mechanical influences should affect the geometry change as little as possible. With the mostly hot working gas, i.w. only the inside of the structure must be acted on, leakage losses through the structure are to be minimized. In transient operation, it is advantageous if the particular thermally induced dimensional changes in the wall structure in terms of time and size those of the bladed rotor are aligned. Because there are mechanical contacts between the blade tips and the wall structure under special loads can hardly be avoided, the inside of the wall structure should at least blade tip deformable / resilient or abradable.
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 vor handenen 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 Vorderund 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. EP-B-0 728 258 relates to a shroud element of a turbine, which together with similar segments the inner wall and part of the connecting structure to the outer wall of a wall structure. Due to temperature differences between Inside and cooled outside of the segments in operation and as a result of different material behavior of the base material and one as a rule The existing coating tends to change the curvature of the segments. To prevent the segments from getting into the blade tip raceway they have a special, hook-like geometry on the front and Trailing edge connected to the outer area of the housing structure, which radial outward movement in places. Because the inner contour often deviates from the circular shape with a tendency to form polygons, is a defined one Difficult to keep gaps. The sealing of the segments with gaps and play is constructively also 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.EP-B-0 781 371 deals with an arrangement for dynamic control of the Blade tip play in gas turbines. The inner wall of the housing structure is there from radially outward-moving, circular arc-shaped overlapping in the circumferential direction curved segments whose movement radially inwards through one of their Front and rear edge hook-like, surrounding housing structure on one side is limited. The segments are made by mechanical spring elements or by Gas pressure biased radially inwards against the stop. The blades have wedge surfaces on the tip side, which, when rotating faster, a dynamic gas cushion generate, the pressure of the wall segments at a defined, small distance should stick to the blade tips. There must be a balance between internal gas force and external spring force adjust that the segments in balance holds. Such a system appears to be very prone to failure, difficult to calculate and vibration risk. The holding structure of the segments is exposed to the working gas and thus possibly subjected to high thermal loads, whereby they also contain a considerable amount of heat leads to the outer wall of the structure.
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-0 616 113 relates to a gas turbine and a method for assembling one Seal in this gas turbine. From this patent, it is i.a. known, metallic Honeycombs to be used as inlet coverings for labyrinth seals. The honeycomb are soldered on one side to a flat, metallic carrier, usually in ring-shaped closed geometry, its openings being cutting-like, ring-shaped Sealing tips are facing. The deformation behavior of the ductile, thin, Upright honeycomb walls accelerate any necessary running-in process and protects the sealing tips. The open structure with a variety of Chambers increase the sealing effect through flow deflection and swirling. Sandwich-like lightweight structures are preferred in aircraft and boat construction uses a relatively thick, light core with a high empty volume, e.g. a honeycomb core, with thin, high-strength, closed on both sides Walls connected and covered When bending such a structure the walls are primarily subjected to tension or pressure in their plane, the core transmits them Wall-to-wall forces, especially thrust. The walls are preferred in Fiber composite construction, glued to the core and in terms of its thickness and mechanical properties at least comparable.
Die DE-A-15 51 183 betrifft zusammengesetzte Dichtungsbauteile für Gasturbinentriebwerke.
Derartige Bauteile werden in Fachkreisen auch als Mantelringe bzw. Liner
bezeichnet und sind rund um Laufschaufelkränze angeordnet, insbesondere mit
der Funktion der Laufschaufelspitzenabdichtung. Im Hinblick auf einfache Montage
und ungehinderte Wärmedehnung sind die Liner meist segmentiert und unter Belassung
von Dehnfugen angeordnet. Die Dichtungsbauteile nach dieser Offenlegungsschrift
sind in Sandwichbauweise mit einem metallischen Wabenkern und mit diesen
beidseitig abdeckenden, metallischen Wänden/Blechen ausgeführt, daher der Ausdruck
"zusammengesetzt". Die innere, abreibbare Wand (Schicht 58') kann an den
Kanten des Dichtungsbauteils abgewinkelt, bis zur äußeren Wand (hinteren Schicht
50') verlängert und mit letzterer durch Verlötung (60) verbunden sein (siehe Seite 9
ab achtletzter Zeile). Die Dichtungsbauteile bilden entweder gewölbte Segmente, wie
in den Figuren dargestellt, oder vollständige Ringe (siehe Seite 10, Zeilen 1 bis 6). Im
ersten Fall sind somit zwangsläufig die Außen- und die Innenwand unterbrochen, d.h.
segmentiert, im zweiten Fall ist keine der Wände segmentiert. Mit Ausnahme des
Hinweises auf ein direktes Verlöten von Außen- und Innenwand im Kantenbereich
gibt es keine Hinweise auf die Art der Verbindung zwischen den Wänden und dem
Wabenkern. Wie aus den Figuren 2 bis 5 ersichtlich, ist die Außenwand mit Flanschen
(52,53) versehen, um sie am Triebwerksgehäuse (11) aufhängen zu können.
Somit ist die Außenwand (hintere Schicht) jedes Dichtungsbauteils keine Gehäusewand.
Die Ausführung der Kernschicht ist auf Wabenmaterial beschränkt.DE-A-15 51 183 relates to composite sealing components for gas turbine engines.
Such components are also used in specialist circles as jacket rings or liners
referred to and are arranged around blade rings, in particular with
the function of the blade tip seal. With regard to easy assembly
and unimpeded thermal expansion, the liners are mostly segmented and left unchanged
arranged by expansion joints. The sealing components according to this published specification
are in sandwich construction with a metallic honeycomb core and with these
metallic walls / sheets covering on both sides, hence the expression
"Composed". The inner, abradable wall (layer 58 ') can on the
Angled edges of the sealing component up to the outer wall (rear layer
50 ') and connected to the latter by soldering (60) (see
Ausgehend von dem genannten Stand der Technik besteht die Aufgabe der Erfindung darin, eine Ringstruktur 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. The object of the invention is based on the cited prior art in it, a ring structure in metal construction for the blade area from 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.This object is achieved by the features characterized in
Die Erfindung ist somit in der Kombination aus einer segmentierten Innenwand, einer geschlossenen, von einer Gehäusewand gebildeten, tragenden Außenwand, einer zwischen den Wänden angeordneten Verbindungsstruktur und aus deren stoffschlüssiger Integration durch Löten zu sehen. Die Verbindungsstruktur ist in an sich bekannter Weise 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.The invention is thus in the combination of a segmented inner wall, one closed, formed by a housing wall, supporting outer wall, one connecting structure arranged between the walls and from their material connection See integration by soldering. The connection structure is in itself known as filigree, light, practically the entire cavity between Hollow chamber structure occupying inner and outer wall - for example as a honeycomb structure - and connected to one or both walls by soldering. Due to the "quasi-flat" connection of the walls, it is possible to achieve dimensional accuracy the load-bearing outer wall in all operating states of the segmented Imprint on the inner wall. A warping or "polygonizing" of the inner contour leaves avoid yourself. The solder connection is optimal due to its "flat character" in terms of mechanical strength and durability and has no negative Influence on the material structure. On the other hand is the filigree connection structure elastic enough to accommodate thermal expansions / contractions of the inner wall segments in the circumferential direction without allowing critical constraining forces. The connection structure has a thermally insulating effect, which is due to its high empty volume and can also be influenced by the selection of its material the inner wall assumes the mostly high temperature of the working gas, the outer wall can be kept significantly cooler, which is beneficial for their mechanical Properties is. 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 on the inner wall are 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 Rezirkulationskarnmern
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)
- Annular metallic structure (1, 2) for the rotor blade area of axial through-flow compressor and turbine stages, in particular in gas turbine engines, having a circular outer wall (3, 4), with a circular inner wall (5, 6) a small radial distance away from the rotor blade tips, and with a connecting structure which is load-transferring at least in the radial direction between the inner and outer walls, such that as the said connecting structure a multiply-subdivided, hollow chamber structure (10, 11, 12, 13, 14) is arranged between and extends at least over most of the surface areas of the inner and outer walls that face one another,
characterised in that
the outer wall (3, 4) is a closed, mechanically stable housing wall of the compressor or turbine stage,
the inner wall (5, 6) is interrupted, i.e. segmented over its circumference by a plurality of axially or substantially axially extending expansion joints (7), and
the hollow chamber structure (10, 11, 12, 13, 14) is connected to the inner wall (5, 6) and/or to the outer wall (3, 4) by brazing. - Annular structure according to Claim 1,
characterised in that
on the side facing the blades the segmented inner wall (5) is provided with a coating in the form of an inlet lining (9) that can be mechanically deformed or abraded on contact with the rotor blade tips. - Annular structure according to Claim 1,
characterised in that
the segmented inner wall (6) is made completely, i.e. throughout its material cross-section, as an inlet lining, preferably designed as a porous metallic body with or without inclusions of another material such as plastic or carbon. - Annular structure according to Claims 1 to 3,
characterised in that
apart from the at least substantially axially extending expansion joints (7), the segmented inner wall (6)is provided with geometrically defined perforations (8) distributed around its circumference, and in the area of the said perforations (8) the hollow chamber structure (11) is set back or recessed (19). - Annular structure according to any of Claims 1 to 4,
characterised in that
the hollow chamber structure (12) is made as a honeycomb structure. - Annular structure according to any of Claims 1 to 5,
characterised in that
the hollow chamber structure (14) is produced as an integral part of the inner wall (5, 6) or the outer wall (3,4) by a material-removing production method, for example by milling, drilling or electrochemical machining.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10020673A DE10020673C2 (en) | 2000-04-27 | 2000-04-27 | Ring structure in metal construction |
| DE10020673 | 2000-04-27 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1149985A2 EP1149985A2 (en) | 2001-10-31 |
| EP1149985A3 EP1149985A3 (en) | 2003-09-17 |
| EP1149985B1 true 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) |
Families Citing this family (23)
| 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 |
| 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 |
| DE102006034424A1 (en) | 2006-07-26 | 2008-01-31 | Mtu Aero Engines Gmbh | gas turbine |
| 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 |
| US8061978B2 (en) * | 2007-10-16 | 2011-11-22 | United Technologies Corp. | Systems and methods involving abradable air seals |
| EP2075416B1 (en) * | 2007-12-27 | 2011-05-18 | Techspace Aero | Method for manufacturing a turboshaft engine element and device obtained using same |
| US8734085B2 (en) | 2009-08-17 | 2014-05-27 | Pratt & Whitney Canada Corp. | Turbine section architecture for gas turbine engine |
| 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 |
| EP2728124B1 (en) | 2012-10-30 | 2018-12-12 | MTU Aero Engines AG | Turbine ring and turbomachine |
| DE102013212741A1 (en) * | 2013-06-28 | 2014-12-31 | Siemens Aktiengesellschaft | Gas turbine and heat shield for a gas turbine |
| 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 |
| DE102017211316A1 (en) | 2017-07-04 | 2019-01-10 | MTU Aero Engines AG | Turbomachinery sealing ring |
| 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 |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3126149A (en) * | 1964-03-24 | Foamed aluminum honeycomb motor | ||
| US3425665A (en) * | 1966-02-24 | 1969-02-04 | Curtiss Wright Corp | Gas turbine rotor blade shroud |
| US3728039A (en) * | 1966-11-02 | 1973-04-17 | Gen Electric | Fluid cooled porous stator structure |
| US3423070A (en) * | 1966-11-23 | 1969-01-21 | Gen Electric | Sealing means for turbomachinery |
| GB2095749B (en) * | 1981-03-25 | 1984-12-12 | Rolls Royce | Gas turbine engine having improved resistance for foreign object ingestion damage |
| US4867639A (en) * | 1987-09-22 | 1989-09-19 | Allied-Signal Inc. | Abradable shroud coating |
| US5228195A (en) * | 1990-09-25 | 1993-07-20 | United Technologies Corporation | Apparatus and method for a stator assembly of a rotary machine |
| US5332358A (en) | 1993-03-01 | 1994-07-26 | General Electric Company | Uncoupled seal support assembly |
| US5380150A (en) | 1993-11-08 | 1995-01-10 | United Technologies Corporation | Turbine shroud segment |
| US5456576A (en) | 1994-08-31 | 1995-10-10 | United Technologies Corporation | Dynamic control of tip clearance |
| 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 DE DE2001504737 patent/DE50104737D1/en not_active Expired - Lifetime
- 2001-04-26 EP EP01110386A patent/EP1149985B1/en not_active Expired - Lifetime
- 2001-04-26 AT AT01110386T patent/ATE284480T1/en not_active IP Right Cessation
- 2001-04-27 US US09/844,012 patent/US6537020B2/en not_active Expired - Fee Related
- 2001-04-27 JP JP2001131882A patent/JP4572042B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| EP1149985A2 (en) | 2001-10-31 |
| JP2002004806A (en) | 2002-01-09 |
| EP1149985A3 (en) | 2003-09-17 |
| DE10020673C2 (en) | 2002-06-27 |
| US20010048876A1 (en) | 2001-12-06 |
| JP4572042B2 (en) | 2010-10-27 |
| ATE284480T1 (en) | 2004-12-15 |
| US6537020B2 (en) | 2003-03-25 |
| DE50104737D1 (en) | 2005-01-13 |
| DE10020673A1 (en) | 2001-10-31 |
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