EP1711689B1 - Sealing arrangement - Google Patents

Sealing arrangement Download PDF

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Publication number
EP1711689B1
EP1711689B1 EP05706719A EP05706719A EP1711689B1 EP 1711689 B1 EP1711689 B1 EP 1711689B1 EP 05706719 A EP05706719 A EP 05706719A EP 05706719 A EP05706719 A EP 05706719A EP 1711689 B1 EP1711689 B1 EP 1711689B1
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EP
European Patent Office
Prior art keywords
rotor
walls
honeycomb
sealing
rotation
Prior art date
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Not-in-force
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EP05706719A
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German (de)
French (fr)
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EP1711689A1 (en
Inventor
Reinhold Meier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of EP1711689A1 publication Critical patent/EP1711689A1/en
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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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • 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
    • F01D11/127—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 a deformable or crushable structure, e.g. honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the invention relates to a sealing arrangement, in particular for a gas turbine or an aircraft engine, according to the preamble of patent claim 1.
  • Gas turbines consist of several components, such as, inter alia, a fan (fan), a combustion chamber, preferably a plurality of compressors and a plurality of turbines.
  • the preferably several turbines are, in particular, a high-pressure turbine and a low-pressure turbine, with the plurality of compressors in particular a high-pressure compressor and a low-pressure compressor.
  • a plurality of guide vane rings are positioned behind one another in the axial direction or in the direction of flow of the gas turbine, each guide vane ring having a plurality of guide vanes distributed over the circumference.
  • each a rotor blade ring is positioned, which has a plurality of blades. The blades are associated with a rotor and rotate together with the rotor relative to a fixed housing and the also stationary formed vanes of the vane rings.
  • the walls, which separate the honeycomb cells of the honeycomb seal run exactly in the radial direction, so that, for example, the sealing fins are oriented perpendicular to walls of the honeycomb cells extending transversely to the direction of rotation of the sealing fins.
  • the rotor rubs against the stator-side honeycomb seal
  • the rotor accordingly strikes the walls of the honeycomb sealing cells running transversely to the direction of rotation of the rotor in the axial direction of view, as a result of which a rotation or rotation of the rotor is opposed by a resisting force.
  • walls of the honeycomb cells extending in this way are relatively stiff, as a result of which the walls of the honeycomb sealing cells do not deform as much as possible.
  • the rotor, in particular the sealing fins runs into the honeycomb seal, according to the prior art, the walls of the honeycomb sealing cells are at least partially removed. In this case, therefore, the honeycomb seal is damaged and the gap to be sealed increases, which is disadvantageous overall.
  • the document GB 793 886 A relates to a seal assembly for a rotor / stator seal, in which the stator is associated with a honeycomb seal with a plurality of honeycomb seal cells.
  • the walls of the honeycomb cells can be vertical or radial (FIG. FIG. 1 ) or inclined ( FIG. 2 ) may be arranged on a support.
  • the honeycomb sealing cells are arranged on the inside of an annular carrier inclined in the circumferential direction, deviating from the radial seal.
  • the open ends of the cells have obliquely in the direction of rotation of the sealed blade tips.
  • the cell walls can deform without being removed immediately, which also protects the blade tips.
  • the disadvantage here is the elaborate production of a honeycomb structure with a defined inclination of each complete honeycomb cell.
  • the document EP-A-0 716 218 relates to a housing structure for the compressor of a gas turbine in the form of a honeycomb configuration, the honeycomb cells are inclined with the open ends opposite to the direction of rotation of the blades.
  • the purpose of the cells is to energize the sluggish blade tip flow and thereby increase the stall margin of the compactor.
  • Such a structure is often referred to as casing treatment.
  • the squeal behavior of such a geometry is very unfavorable, since the cell walls set up radially inwardly on blade contact and penetrate even deeper into the blade path.
  • a honeycomb seal for the production of which sheets are provided with deep nubs (embossed sheet) and applied to a carrier, the still closed nubs protruding from the carrier. Then the studded floors are removed, creating honeycomb cells with curved or arched walls. These are perpendicular to the carrier.
  • the present invention is based on the problem to provide a simplified seal arrangement, in particular for a gas turbine or an aircraft engine, with favorable Anstreif .
  • a sealing arrangement according to claim 1.
  • at least the transverse to the direction of rotation of the rotor walls of the honeycomb sealing cells are set radially obliquely in the direction of rotation of the rotor.
  • a deformability of the walls of the honeycomb sealing cells is provided, so that when rubbing the rotor, in particular the rotor-side sealing fins, in the honeycomb seal a removal or cracking of the walls is avoided.
  • the present sealing arrangement therefore, an effective sealing of a gap between a rotor and a stator is possible.
  • the transverse to the direction of rotation of the rotor walls of the honeycomb sealing cells are set in the direction of rotation of the rotor so inclined that the rotor facing edges of these walls are offset from the rotor facing edges of these walls in the direction of rotation of the rotor.
  • the edges of these walls facing the rotor are curved, the edges of these walls facing away from the rotor extending in a straight line.
  • This geometry makes it possible, for example, to start from a sheet metal structure with square or rectangular honeycomb seal cells and to permanently deform a part of the cell walls. This is much easier than making oblique honeycombs.
  • the walls of the honeycomb sealing cells extending transversely to the direction of rotation of the rotor are inclined as well.
  • FIGS. 5 and 6 Embodiments of the present invention will be explained in more detail below with reference to FIG Fig. 1 to 4 two known from the prior art sealing arrangements will be described.
  • FIG. 1 and 2 highly schematic of a honeycomb seal 10 of a seal assembly according to the prior art between a non-illustrated rotor and a likewise not shown stator of a gas turbine.
  • Fig. 1 shows a schematic side view of the honeycomb seal 10 in the axial direction
  • Fig. 2 shows a schematic plan view the same in the radial direction.
  • the X-coordinate of the represented coordinate systems is the radial direction
  • the Y-coordinate is the circumferential direction
  • the Z-coordinate the axial direction is visualized.
  • the axial direction according to Fig. 1 one sees therefore on the XY-plane, in radial direction according to Fig. 2 you can see the YZ-plane.
  • the honeycomb seal 10 is formed by a plurality of honeycomb seal cells 11, wherein the honeycomb seal cells 11 in FIG Fig. 1 and 2 have a rectangular cross-sectional area. It should be noted at this point that the honeycomb seals can of course also have a hexagonal cross-sectional profile.
  • honeycomb seal cells 11 of the honeycomb seal 10 are bounded by a plurality of walls. For the purposes of the present invention is to be distinguished between such walls which extend transversely or longitudinally to the direction of rotation of a rotor.
  • the direction of rotation of a non-illustrated rotor is in Fig. 1 and 2 illustrated with an arrow 12.
  • Walls of the honeycomb sealing cells 11 extending transversely to the direction of rotation 12 are identified by the reference numeral 13
  • walls of the honeycomb sealing cells 11 running longitudinally or parallel to the direction of rotation 12 are identified by the reference numeral 14.
  • Fig. 1 can be removed, extend according to the prior art, the transverse to the direction of rotation 12 of the rotor walls 13 of the honeycomb sealing cells 11 exactly in the radial direction, so that the same in the axial direction of the Fig. 1 are aligned perpendicular to the direction of rotation 12 of the rotor.
  • the walls 13 running transversely to the direction of rotation of the rotor form a resistance for the rotor 12, since walls 13 formed in this way are relatively stiff and can only slightly deform, if at all. When rubbing the rotor in the same direction transverse to the direction of rotation walls 13, these are therefore removed and thus damaged.
  • the honeycomb seal 15 of 3 and 4 shows a honeycomb seal 15 of a further seal arrangement according to the prior art in different representations or viewing directions, the viewing directions of 3 and 4 the views of the Fig. 1 and 2 correspond.
  • the honeycomb seal 15 of 3 and 4 consists of several honeycomb sealing cells 16, wherein the honeycomb sealing cells 16 have a rectangular contour in cross section.
  • the honeycomb cells 16 are in turn bounded by several walls, which are aligned optimally relative to the direction of rotation (arrow 17) of a rotor.
  • the transverse to the direction of rotation 17 of the rotor walls 18 of the honeycomb sealing cells 16 are set obliquely so that a rotor facing edge 20 is offset from the rotor facing away from the edge 21 in the direction of rotation of the rotor, which means that the edge facing the rotor 20th is positioned in the direction of rotation 17 to the front or downstream of the edge 21 facing away from the rotor.
  • the offset edges 20 and 21 of the transverse to the direction of rotation 17 of the rotor walls 18 are shown as parallel lines. The edges 20, 21 of the walls 18 thus run straight.
  • the production of such precise, obliquely employed honeycomb cells is complex.
  • FIGS. 5 and 6 show two embodiments of inventive honeycomb seals or sealing arrangements.
  • Fig. 5 differs from the known version of the 3 and 4 in that in the honeycomb seal 22 of the Fig. 5 the rotor-facing edges 20 of the transverse to the direction of rotation 17 of the rotor walls 18 are not rectilinear, but rather are curved or curved. The curvature runs in the direction of rotation 17 of the rotor. The edges facing away from the rotor 21 of the transverse to the direction of rotation of the rotor walls 18, however, are rectilinear.
  • Fig. 6 shows a further embodiment of a honeycomb seal 23 according to the invention, wherein in the honeycomb seal 23 according to Fig. 6 in addition to the transverse to the direction of rotation 17 of the rotor walls 18 extending in the direction of rotation of the rotor walls 19 of the honeycomb sealing cells 16 are inclined.
  • the edges thereof offset from each other so that a rotor facing edge 24 of the walls 19 is offset from a rotor 25 facing away from the edge, wherein in the embodiment of Fig. 6 the rotor facing edge 24 is curved and facing away from the rotor edge 25 is rectilinear.
  • the flexibility of the honeycomb sealing cells 16 or the walls 18, 19 of the honeycomb sealing cells 16 can be optimized once again.
  • the embodiments shown have in common that at least the transverse to the direction of rotation 17 of the rotor walls 18 of the honeycomb sealing cells 16 are set radially obliquely in the direction of rotation of the rotor.
  • the edges 20, 21 extend on the one hand straight, on the other curved. In this way, a good elastic and plastic deformability of the walls of the honeycomb seal cells is made possible, without damaging or removing the walls of the honeycomb seal cells when the rotor or rotor-side sealing fins are rubbed into the honeycomb seal. The stress of the honeycomb seal can thus be reduced, thereby increasing the life of the same.
  • the sealing arrangement according to the invention serves, in particular, for sealing a radial gap between radially inner ends of guide vanes and a rotor.
  • the honeycomb seals are then assigned to the radially inner ends of the guide vanes or corresponding inner end tapes of the guide vanes, the sealing fins associated with the rotor interacting with the honeycomb seal. It is also possible to seal a gap between the radially outer ends of the rotating blades and a fixed housing with such a sealing arrangement.
  • the use of the sealing arrangement in the compressor area or turbine area of a gas turbine, in particular of an aircraft engine, is preferred.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Description

Die Erfindung betrifft eine Dichtungsanordnung, insbesondere für eine Gasturbine bzw. ein Flugtriebwerk, gemäß dem Oberbegriff des Patentanspruchs 1.The invention relates to a sealing arrangement, in particular for a gas turbine or an aircraft engine, according to the preamble of patent claim 1.

Gasturbinen bestehen aus mehreren Baugruppen, so zum Beispiel unter anderem aus einem Lüfter (Fan), einer Brennkammer, vorzugsweise mehreren Verdichtern sowie mehreren Turbinen. Bei den vorzugsweise mehreren Turbinen handelt es sich insbesondere um eine Hochdruckturbine sowie eine Niederdruckturbine, bei den mehreren Verdichtern insbesondere um einen Hochendruckverdichter sowie einen Niederdruckverdichter. In einer Turbine sowie einem Verdichter einer Gasturbine sind in axialer Richtung bzw. in Durchströmungsrichtung der Gasturbine hintereinander mehrere Leitschaufelkränze positioniert, wobei jeder Leitschaufelkranz mehrere, über den Umfang verteilt angeordnete Leitschaufeln aufweist. Zwischen jeweils zwei benachbarten Leitschaufelkränzen ist jeweils ein Laufschaufelkranz positioniert, der mehrere Laufschaufeln aufweist. Die Laufschaufeln sind einem Rotor zugeordnet und rotieren zusammen mit dem Rotor gegenüber einem feststehenden Gehäuse sowie den ebenfalls feststehend ausgebildeten Leitschaufeln der Leitschaufelkränze.Gas turbines consist of several components, such as, inter alia, a fan (fan), a combustion chamber, preferably a plurality of compressors and a plurality of turbines. The preferably several turbines are, in particular, a high-pressure turbine and a low-pressure turbine, with the plurality of compressors in particular a high-pressure compressor and a low-pressure compressor. In a turbine and a compressor of a gas turbine, a plurality of guide vane rings are positioned behind one another in the axial direction or in the direction of flow of the gas turbine, each guide vane ring having a plurality of guide vanes distributed over the circumference. Between each two adjacent vane rings each a rotor blade ring is positioned, which has a plurality of blades. The blades are associated with a rotor and rotate together with the rotor relative to a fixed housing and the also stationary formed vanes of the vane rings.

Zur Optimierung des Wirkungsgrads einer Gasturbine müssen Leckagen einerseits zwischen den rotierenden Laufschaufeln und dem feststehenden Gehäuse und andererseits zwischen den feststehenden Leitschaufeln und dem Rotor durch effektive Dichtungssysteme vermieden werden. So ist es aus dem Stand der Technik bereits bekannt, zur Abdichtung solcher Spalte dem Stator, also dem feststehenden Gehäuse oder den radial innenliegenden Enden der feststehenden Leitschaufeln, eine mehrere Wabendichtungszellen umfassende Wabendichtung zuzuordnen, wobei die Wabendichtungszellen durch Wände voneinander getrennt sind. Diese Wabendichtungen wirken insbesondere mit dem Rotor oder den rotierenden Laufschaufeln zugeordneten Dichtfins zusammen, wobei ein solcher Dichtfin gegenüber der statorseitigen Wabendichtung rotiert.To optimize the efficiency of a gas turbine, leaks must be avoided on the one hand between the rotating blades and the stationary casing and on the other hand between the fixed vanes and the rotor by effective sealing systems. Thus, it is already known from the prior art, for sealing such gaps the stator, so the fixed housing or the radially inner ends of the fixed vanes, assign a multi-honeycomb cells comprehensive honeycomb seal, wherein the honeycomb sealing cells are separated by walls. These honeycomb seals cooperate in particular with sealing fins associated with the rotor or the rotating blades, such a sealing washer rotating relative to the stator-side honeycomb seal.

Nach dem Stand der Technik verlaufen die Wände, welche die Wabenzellen der Wabendichtung voneinander trennen, exakt in radialer Richtung, sodass zum Beispiel die Dichtfins relativ zu quer zur Drehrichtung der Dichtfins verlaufenden Wände der Wabendichtungszellen senkrecht ausgerichtet sind.According to the prior art, the walls, which separate the honeycomb cells of the honeycomb seal, run exactly in the radial direction, so that, for example, the sealing fins are oriented perpendicular to walls of the honeycomb cells extending transversely to the direction of rotation of the sealing fins.

Bei einem Anstreifen des Rotors, insbesondere der Dichtfins, in die statorseitige Wabendichtung trifft der Rotor demnach in axialer Blickrichtung senkrecht auf die quer zur Drehrichtung des Rotors verlaufenden Wände der Wabendichtungszellen, wodurch der Rotation bzw. Drehung des Rotors eine Widerstandskraft entgegengesetzt wird. Derart verlaufende Wände der Wabendichtungszellen sind nämlich relativ steif ausgebildet, wodurch sich die Wände der Wabendichtungszellen so gut wie nicht verformen. Beim Einlaufen des Rotors, insbesondere der Dichtfins, in die Wabendichtung werden demnach nach dem Stand der Technik die Wände der Wabendichtungszellen zumindest bereichsweise abgetragen. Hierbei wird demnach die Wabendichtung beschädigt sowie der abzudichtende Spalt vergrößert, was insgesamt von Nachteil ist.When the rotor, in particular the sealing fins, rubs against the stator-side honeycomb seal, the rotor accordingly strikes the walls of the honeycomb sealing cells running transversely to the direction of rotation of the rotor in the axial direction of view, as a result of which a rotation or rotation of the rotor is opposed by a resisting force. In fact, walls of the honeycomb cells extending in this way are relatively stiff, as a result of which the walls of the honeycomb sealing cells do not deform as much as possible. When the rotor, in particular the sealing fins, runs into the honeycomb seal, according to the prior art, the walls of the honeycomb sealing cells are at least partially removed. In this case, therefore, the honeycomb seal is damaged and the gap to be sealed increases, which is disadvantageous overall.

Das Dokument GB 793 886 A betrifft eine Dichtungsanordnung für eine Rotor-/Stator-Abdichtung, bei der dem Stator eine Wabendichtung mit mehreren Wabendichtungszellen zugeordnet ist. Die Wände der Wabendichtungszellen können senkrecht bzw. radial (Figur 1) oder geneigt (Figur 2) auf einem Träger angeordnet sein. Gemäß Figur 8 dieses Dokuments sind die Wabendichtungszellen auf der Innenseite eines kreisringförmigen Trägers abweichend von der Radialdichtung in Umfangsrichtung geneigt angeordnet. Die offenen Enden der Zellen weisen dabei schräg in Drehrichtung der abzudichtenden Laufschaufelspitzen. Im Falle eines Anstreifens können sich die Zellenwände verformen, ohne gleich abgetragen zu werden, was auch die Schaufelspitzen schont. Nachteilig dabei ist die aufwändige Fertigung einer Honigwabenstruktur mit definierter Neigung jeder kompletten Wabenzelle.The document GB 793 886 A relates to a seal assembly for a rotor / stator seal, in which the stator is associated with a honeycomb seal with a plurality of honeycomb seal cells. The walls of the honeycomb cells can be vertical or radial (FIG. FIG. 1 ) or inclined ( FIG. 2 ) may be arranged on a support. According to FIG. 8 of this document, the honeycomb sealing cells are arranged on the inside of an annular carrier inclined in the circumferential direction, deviating from the radial seal. The open ends of the cells have obliquely in the direction of rotation of the sealed blade tips. In the case of an abutment, the cell walls can deform without being removed immediately, which also protects the blade tips. The disadvantage here is the elaborate production of a honeycomb structure with a defined inclination of each complete honeycomb cell.

Das Dokument EP-A-0 716 218 betrifft eine Gehäusestruktur für den Verdichter einer Gasturbine in Form einer Wabenstruktur (honeycomb configuration), deren Wabenzellen mit den offenen Enden entgegen der Drehrichtung der Laufschaufeln geneigt sind. Die Zellen haben die Aufgabe, die träge Schaufelspitzenströmung zu energetisieren und dadurch die Pumpgrenze (stall margin) des Verdichters zu erhöhen. Eine solche Struktur wird häufig als Casing Treatment bezeichnet. Das Anstreifverhalten einer solchen Geometrie ist sehr ungünstig, da sich die Zellenwände bei Schaufelberührung radial nach innen aufstellen und noch tiefer in die Schaufelbahn eindringen.The document EP-A-0 716 218 relates to a housing structure for the compressor of a gas turbine in the form of a honeycomb configuration, the honeycomb cells are inclined with the open ends opposite to the direction of rotation of the blades. The purpose of the cells is to energize the sluggish blade tip flow and thereby increase the stall margin of the compactor. Such a structure is often referred to as casing treatment. The squeal behavior of such a geometry is very unfavorable, since the cell walls set up radially inwardly on blade contact and penetrate even deeper into the blade path.

Aus dem Dokument US-A-3 649 033 ist eine Wabendichtung bekannt, zu deren Fertigung Bleche mit tiefen Noppen versehen (embossed sheet) und auf einen Träger aufgebracht werden, wobei die noch geschlossenen Noppen von dem Träger abstehen. Dann werden die Noppenböden spanabhebend entfernt, wodurch Wabenzellen mit gekrümmten bzw. gewölbten Wänden entstehen. Diese stehen senkrecht auf dem Träger.From the document U.S.-A-3,649,033 For example, a honeycomb seal is known, for the production of which sheets are provided with deep nubs (embossed sheet) and applied to a carrier, the still closed nubs protruding from the carrier. Then the studded floors are removed, creating honeycomb cells with curved or arched walls. These are perpendicular to the carrier.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine vereinfachte Dichtungsanordnung, insbesondere für eine Gasturbine bzw. ein Flugtriebwerk, mit günstigem Anstreifverhalten, zu schaffen.On this basis, the present invention is based on the problem to provide a simplified seal arrangement, in particular for a gas turbine or an aircraft engine, with favorable Anstreifverhalten.

Dieses Problem wird durch eine Dichtungsanordnung gemäß Patentanspruch 1 gelöst. In bekannter Weise sind zumindest die quer zur Drehrichtung des Rotors verlaufenden Wände der Wabendichtungszellen in Drehrichtung des Rotors radial schräg angestellt.
Hierdurch wird eine Verformbarkeit der Wände der Wabendichtungszellen bereitgestellt, sodass beim Anstreifen des Rotors, insbesondere der rotorseitigen Dichtfins, in die Wabendichtung ein Abtragen bzw. eine Rissbildung der Wände vermieden wird. Mit der hier vorliegenden Dichtungsanordnung ist demnach eine effektive Abdichtung eines Spalts zwischen einem Rotor und einem Stator möglich. Dabei sind die quer zur Drehrichtung des Rotors verlaufenden Wände der Wabendichtungszellen in Drehrichtung des Rotors derart schräg angestellt, dass dem Rotor zugewandte Kanten dieser Wände gegenüber dem Rotor abgewandten Kanten dieser Wände in Drehrichtung des Rotors versetzt sind.This problem is solved by a sealing arrangement according to claim 1. In a known manner, at least the transverse to the direction of rotation of the rotor walls of the honeycomb sealing cells are set radially obliquely in the direction of rotation of the rotor.
As a result, a deformability of the walls of the honeycomb sealing cells is provided, so that when rubbing the rotor, in particular the rotor-side sealing fins, in the honeycomb seal a removal or cracking of the walls is avoided. With the present sealing arrangement, therefore, an effective sealing of a gap between a rotor and a stator is possible. The transverse to the direction of rotation of the rotor walls of the honeycomb sealing cells are set in the direction of rotation of the rotor so inclined that the rotor facing edges of these walls are offset from the rotor facing edges of these walls in the direction of rotation of the rotor.

Erfindungsgemäß sind die dem Rotor zugewandten Kanten dieser Wände gewölbt, die von dem Rotor abgewandten Kanten dieser Wände verlaufen geradlinig.
Diese Geometrie macht es möglich, z.B. von einer Blechstruktur mit quadratischen oder rechteckigen Wabendichtungszellen auszugehen und einen Teil der Zellwände bleibend zu verformen. Die ist wesentlich einfacher, als die Fertigung schräger Honigwaben.According to the invention, the edges of these walls facing the rotor are curved, the edges of these walls facing away from the rotor extending in a straight line.
This geometry makes it possible, for example, to start from a sheet metal structure with square or rectangular honeycomb seal cells and to permanently deform a part of the cell walls. This is much easier than making oblique honeycombs.

Nach einer vorteilhaften Weiterbildung der Erfindung sind zusätzlich zu den quer zur Drehrichtung des Rotors verlaufenden Wänden der Wabendichtungszellen auch die in Drehrichtung des Rotors verlaufenden Wände der Wabendichtungszellen schräg angestellt.According to an advantageous development of the invention, in addition to the walls of the honeycomb sealing cells extending transversely to the direction of rotation of the rotor, the walls of the honeycomb sealing cells extending in the direction of rotation of the rotor are inclined as well.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1
eine stark schematisierte Seitenansicht in axialer Blickrichtung auf eine mehrere Wabendichtungszellen umfassende Wabendichtung einer Dichtungsanordnung nach dem Stand der Technik;
Fig. 2
eine stark schematisierte Draufsicht in radialer Blickrichtung auf die mehrere Wabendichtungszellen umfassende Wabendichtung nach Fig. 1;
Fig. 3
eine stark schematisierte Seitenansicht in axialer Blickrichtung auf eine mehrere Wabendichtungszellen umfassende Wabendichtung einer weiteren Dichtungsanordnung nach dem Stand der Technik;
Fig. 4
eine stark schematisierte Draufsicht in radialer Blickrichtung auf die mehrere Wabendichtungszellen umfassende Wabendichtung nach Fig. 3;
Fig. 5
eine stark schematisierte Draufsicht in radialer Blickrichtung auf eine mehrere Wabendichtungszellen umfassende Wabendichtung einer Dichtungsanordnung nach einem ersten Ausführungsbeispiel der hier vorliegenden Erfindung; und
Fig. 6
eine stark schematisierte Draufsicht in radialer Blickrichtung auf eine mehrere Wabendichtungszellen umfassende Wabendichtung einer Dichtungsanordnung nach einem zweiten Ausführungsbeispiel der hier vorliegenden Erfindung.
Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a highly schematic side view in the axial direction of a multi-honeycomb cells comprehensive honeycomb seal of a seal assembly according to the prior art;
Fig. 2
a highly schematic top view in the radial direction of the multi-honeycomb cells comprehensive honeycomb seal after Fig. 1 ;
Fig. 3
a highly schematic side view in the axial direction of a wadding sealing cells comprehensive honeycomb seal another seal assembly according to the prior art;
Fig. 4
a highly schematic top view in the radial direction of the multi-honeycomb cells comprehensive honeycomb seal after Fig. 3 ;
Fig. 5
a highly schematic plan view in the radial direction of view on a plurality of honeycomb sealing comprehensive honeycomb seal a seal assembly according to a first embodiment of the present invention; and
Fig. 6
a highly schematic plan view in the radial direction of view on a plurality of honeycomb sealing comprehensive honeycomb seal a seal assembly according to a second embodiment of the present invention.

Bevor nachfolgend unter Bezugnahme auf Fig. 5 und 6 Ausführungsbeispiele der hier vorliegenden Erfindung in größerem Detail erläutert werden, sollen nachfolgend unter Bezugnahme auf Fig. 1 bis 4 zwei aus dem Stand der Technik bekannte Dichtungsanordnungen beschrieben werden.Before referring to below FIGS. 5 and 6 Embodiments of the present invention will be explained in more detail below with reference to FIG Fig. 1 to 4 two known from the prior art sealing arrangements will be described.

So zeigen Fig. 1 und 2 stark schematisiert eine Wabendichtung 10 einer Dichtungsanordnung nach dem Stand der Technik zwischen einem nicht-dargestellten Rotor und einem ebenfalls nicht-dargestellten Stator einer Gasturbine. Fig. 1 zeigt eine schematisierte Seitenansicht der Wabendichtung 10 in axialer Blickrichtung, Fig. 2 zeigt eine schematisierte Draufsicht derselben in radialer Blickrichtung. Mit der X-Koordinate der dargestellten Koordinatensysteme ist die radiale Richtung, mit der Y-Koordinate ist die Umfangsrichtung und mit der Z-Koordinate ist die axiale Richtung visualisiert. In axialer Blickrichtung gemäß Fig. 1 sieht man demnach auf die X-Y-Ebene, in radialer Blickrichtung gemäß Fig. 2 sieht man die Y-Z-Ebene.To show Fig. 1 and 2 highly schematic of a honeycomb seal 10 of a seal assembly according to the prior art between a non-illustrated rotor and a likewise not shown stator of a gas turbine. Fig. 1 shows a schematic side view of the honeycomb seal 10 in the axial direction, Fig. 2 shows a schematic plan view the same in the radial direction. With the X-coordinate of the represented coordinate systems is the radial direction, with the Y-coordinate is the circumferential direction and with the Z-coordinate the axial direction is visualized. In the axial direction according to Fig. 1 one sees therefore on the XY-plane, in radial direction according to Fig. 2 you can see the YZ-plane.

Die Wabendichtung 10 wird von mehreren Wabendichtungszellen 11 gebildet, wobei die Wabendichtungszellen 11 in Fig. 1 und 2 eine rechteckige Querschnittsfläche aufweisen. Es sei an dieser Stelle darauf hingewiesen, dass die Wabendichtungen selbstverständlich auch ein sechseckiges Querschnittsprofil aufweisen können.The honeycomb seal 10 is formed by a plurality of honeycomb seal cells 11, wherein the honeycomb seal cells 11 in FIG Fig. 1 and 2 have a rectangular cross-sectional area. It should be noted at this point that the honeycomb seals can of course also have a hexagonal cross-sectional profile.

Die Wabendichtungszellen 11 der Wabendichtung 10 werden von mehreren Wänden begrenzt. Im Sinne der hier vorliegenden Erfindung soll zwischen solchen Wänden unterschieden werden, die quer oder längs zur Drehrichtung eines Rotors verlaufen. Die Drehrichtung eines nicht-dargestellten Rotors ist in Fig. 1 und 2 mit einem Pfeil 12 verdeutlicht. Quer zur Drehrichtung 12 verlaufende Wände der Wabendichtungszellen 11 sind mit der Bezugsziffer 13 gekennzeichnet, längs bzw. parallel zur Drehrichtung 12 verlaufende Wände der Wabendichtungszellen 11 sind mit der Bezugsziffer 14 gekennzeichnet.The honeycomb seal cells 11 of the honeycomb seal 10 are bounded by a plurality of walls. For the purposes of the present invention is to be distinguished between such walls which extend transversely or longitudinally to the direction of rotation of a rotor. The direction of rotation of a non-illustrated rotor is in Fig. 1 and 2 illustrated with an arrow 12. Walls of the honeycomb sealing cells 11 extending transversely to the direction of rotation 12 are identified by the reference numeral 13, and walls of the honeycomb sealing cells 11 running longitudinally or parallel to the direction of rotation 12 are identified by the reference numeral 14.

Wie Fig. 1 entnommen werden kann, verlaufen nach dem Stand der Technik die quer zur Drehrichtung 12 des Rotors verlaufenden Wände 13 der Wabendichtungszellen 11 exakt in radialer Richtung, sodass dieselben in axialer Blickrichtung der Fig. 1 senkrecht zur Drehrichtung 12 des Rotors ausgerichtet sind. Nach dem Stand der Technik bilden demnach die quer zur Drehrichtung des Rotors verlaufenden Wände 13 einen Widerstand für den Rotor 12, da derart ausgebildete Wände 13 relativ steif sind und sich, wenn überhaupt, nur geringfügig verformen können. Beim Anstreifen des Rotors in die quer zur Drehrichtung desselben verlaufenden Wände 13 werden diese demnach abgetragen und damit beschädigt.As Fig. 1 can be removed, extend according to the prior art, the transverse to the direction of rotation 12 of the rotor walls 13 of the honeycomb sealing cells 11 exactly in the radial direction, so that the same in the axial direction of the Fig. 1 are aligned perpendicular to the direction of rotation 12 of the rotor. According to the state of the art, therefore, the walls 13 running transversely to the direction of rotation of the rotor form a resistance for the rotor 12, since walls 13 formed in this way are relatively stiff and can only slightly deform, if at all. When rubbing the rotor in the same direction transverse to the direction of rotation walls 13, these are therefore removed and thus damaged.

Fig. 3 und 4 zeigen eine Wabendichtung 15 einer weiteren Dichtungsanordnung nach dem Stand der Technik in unterschiedlichen Darstellungen bzw. Blickrichtungen, wobei die Blickrichtungen der Fig. 3 und 4 den Blickrichtungen der Fig. 1 und 2 entsprechen. Auch die Wabendichtung 15 der Fig. 3 und 4 besteht aus mehreren Wabendichtungszellen 16, wobei die Wabendichtungszellen 16 im Querschnitt eine rechteckige Kontur aufweisen. Die Wabendichtungszellen 16 werden wiederum von mehreren Wänden begrenzt, die relativ zur Drehrichtung (Pfeil 17) eines Rotors optimiert ausgerichtet sind. 3 and 4 show a honeycomb seal 15 of a further seal arrangement according to the prior art in different representations or viewing directions, the viewing directions of 3 and 4 the views of the Fig. 1 and 2 correspond. Also, the honeycomb seal 15 of 3 and 4 consists of several honeycomb sealing cells 16, wherein the honeycomb sealing cells 16 have a rectangular contour in cross section. The honeycomb cells 16 are in turn bounded by several walls, which are aligned optimally relative to the direction of rotation (arrow 17) of a rotor.

Im Ausführungsbeispiel der Fig. 3 und 4 sind die quer zur Drehrichtung des Rotors verlaufenden Wände 18 der Wabendichtungszellen 17 in Drehrichtung des Rotors radial schräg angestellt. Dies kann am besten Fig. 3 (entspricht der axialen Blickrichtung) entnommen werden, aus welcher die radiale Schrägstellung der Wände 18 ersichtlich ist. Die längs bzw. parallel zur Drehrichtung 17 des Rotors verlaufenden Wände 19 hingegen verlaufen radial ohne derartige Schrägstellung.In the embodiment of 3 and 4 are the transverse to the direction of rotation of the rotor walls 18 of the honeycomb sealing cells 17 set radially obliquely in the direction of rotation of the rotor. This is best Fig. 3 (corresponds to the axial direction of view) are taken, from which the radial inclination of the walls 18 can be seen. The longitudinally or parallel to the direction of rotation 17 of the rotor extending walls 19, however, extend radially without such skewing.

Die quer zur Drehrichtung 17 des Rotors verlaufenden Wände 18 der Wabendichtungszellen 16 sind dabei derart schräg angestellt, dass eine dem Rotor zugewandte Kante 20 gegenüber einer dem Rotor abgewandten Kante 21 in Drehrichtung des Rotors versetzt ist, was bedeutet, dass die dem Rotor zugewandte Kante 20 in Drehrichtung 17 nach vorne bzw. stromabwärts der vom Rotor abgewandten Kante 21 positioniert ist. In der Draufsicht auf die Wabendichtung 10 gemäß Fig. 4 (entspricht der radialen Blickrichtung) sind die derart versetzten Kanten 20 und 21 der quer zur Drehrichtung 17 des Rotors verlaufenden Wände 18 als parallel zueinander verlaufende Linien dargestellt. Die Kanten 20, 21 der Wände 18 verlaufen demnach geradlinig. Die Fertigung solch präziser, schräg angestellter Wabendichtungszellen ist aufwändig.The transverse to the direction of rotation 17 of the rotor walls 18 of the honeycomb sealing cells 16 are set obliquely so that a rotor facing edge 20 is offset from the rotor facing away from the edge 21 in the direction of rotation of the rotor, which means that the edge facing the rotor 20th is positioned in the direction of rotation 17 to the front or downstream of the edge 21 facing away from the rotor. In the plan view of the honeycomb seal 10 according to Fig. 4 (Corresponds to the radial viewing direction), the offset edges 20 and 21 of the transverse to the direction of rotation 17 of the rotor walls 18 are shown as parallel lines. The edges 20, 21 of the walls 18 thus run straight. The production of such precise, obliquely employed honeycomb cells is complex.

Fig. 5 und 6 zeigen zwei Ausführungsbeispiele erfindungsgemäßer Wabendichtungen bzw. Dichtungsanordnungen. FIGS. 5 and 6 show two embodiments of inventive honeycomb seals or sealing arrangements.

Das Ausführungsbeispiel der Fig. 5 unterscheidet sich von der bekannten Ausführung der Fig. 3 und 4 dadurch, dass bei der Wabendichtung 22 der Fig. 5 die dem Rotor zugewandten Kanten 20 der quer zur Drehrichtung 17 des Rotors verlaufenden Wände 18 nicht geradlinig verlaufen, sondern vielmehr gekrümmt bzw. gewölbt sind. Die Wölbung verläuft dabei in Drehrichtung 17 des Rotors. Die vom Rotor abgewandten Kanten 21 der quer zur Drehrichtung des Rotors verlaufenden Wände 18 verlaufen hingegen geradlinig.The embodiment of Fig. 5 differs from the known version of the 3 and 4 in that in the honeycomb seal 22 of the Fig. 5 the rotor-facing edges 20 of the transverse to the direction of rotation 17 of the rotor walls 18 are not rectilinear, but rather are curved or curved. The curvature runs in the direction of rotation 17 of the rotor. The edges facing away from the rotor 21 of the transverse to the direction of rotation of the rotor walls 18, however, are rectilinear.

Fig. 6 zeigt ein weiteres Ausführungsbeispiel einer erfindungsgemäßen Wabendichtung 23, wobei bei der Wabendichtung 23 gemäß Fig. 6 zusätzlich zu den quer zur Drehrichtung 17 des Rotors verlaufenden Wänden 18 auch die in Drehrichtung des Rotors verlaufenden Wände 19 der Wabendichtungszellen 16 schräg angestellt sind. So sind im Ausführungsbeispiel der Fig. 6 auch im Bereich der längs bzw. parallel zur Drehrichtung 17 verlaufenden Wände 19 die Kanten derselben derart zueinander versetzt, dass eine dem Rotor zugewandte Kante 24 der Wände 19 gegenüber einer dem Rotor abgewandten Kante 25 versetzt ist, wobei im Ausführungsbeispiel der Fig. 6 die dem Rotor zugewandte Kante 24 gewölbt ist und die dem Rotor abgewandte Kante 25 geradlinig verläuft. Hierdurch kann die Flexibilität der Wabendichtungszellen 16 bzw. der Wände 18, 19 der Wabendichtungszellen 16 nochmals optimiert werden. Fig. 6 shows a further embodiment of a honeycomb seal 23 according to the invention, wherein in the honeycomb seal 23 according to Fig. 6 in addition to the transverse to the direction of rotation 17 of the rotor walls 18 extending in the direction of rotation of the rotor walls 19 of the honeycomb sealing cells 16 are inclined. Thus, in the embodiment of the Fig. 6 also in the region of the longitudinally or parallel to the direction of rotation 17 extending walls 19, the edges thereof offset from each other so that a rotor facing edge 24 of the walls 19 is offset from a rotor 25 facing away from the edge, wherein in the embodiment of Fig. 6 the rotor facing edge 24 is curved and facing away from the rotor edge 25 is rectilinear. As a result, the flexibility of the honeycomb sealing cells 16 or the walls 18, 19 of the honeycomb sealing cells 16 can be optimized once again.

Den gezeigten Ausführungsbeispielen ist gemeinsam, dass zumindest die quer zur Drehrichtung 17 des Rotors verlaufenden Wände 18 der Wabendichtungszellen 16 in Drehrichtung des Rotors radial schräg angestellt sind. Hierzu sind die Kanten 20, 21, welche die quer zur Drehrichtung des Rotors verlaufenden Wände 18 begrenzen, zueinander versetzt. Die Kanten 20, 21 verlaufen zum einen geradlinig, zum anderen gekrümmt. Hierdurch wird eine gute elastische sowie plastische Verformbarkeit der Wände der Wabendichtungszellen ermöglicht, ohne dass beim Anstreifen des Rotors bzw. von rotorseitigen Dichtfins in die Wabendichtung die Wände der Wabendichtungszellen beschädigt oder abgetragen werden. Die Beanspruchung der Wabendichtung kann demnach reduziert werden, wodurch sich die Lebensdauer derselben erhöht. Es tritt keine unerwünschte Vergrößerung des abzudichtenden Spalts ein, weshalb eine höhere Dichtwirkung erzielt werden kann. Die erfindungsgemäße Dichtungsanordnung dient insbesondere der Abdichtung eines radialen Spalts zwischen radial innenliegenden Enden von Leitschaufeln und einem Rotor. Die Wabendichtungen sind dann den radial innenliegenden Enden der Leitschaufeln bzw. entsprechenden Innendeckbändern der Leitschaufeln zugeordnet, wobei dem Rotor zugeordnete Dichtfins mit der Wabendichtung zusammenwirken. Es ist auch möglich, mit einer derartigen Dichtungsanordnung einen Spalt zwischen den radial außenliegenden Enden der rotierenden Laufschaufeln und einem feststehenden Gehäuse abzudichten. Bevorzugt ist die Verwendung der Dichtungsanordnung im Verdichterbereich bzw. Turbinenbereich einer Gasturbine, insbesondere eines Flugtriebwerks. The embodiments shown have in common that at least the transverse to the direction of rotation 17 of the rotor walls 18 of the honeycomb sealing cells 16 are set radially obliquely in the direction of rotation of the rotor. For this purpose, the edges 20, 21, which limit the transverse to the direction of rotation of the rotor walls 18, offset from one another. The edges 20, 21 extend on the one hand straight, on the other curved. In this way, a good elastic and plastic deformability of the walls of the honeycomb seal cells is made possible, without damaging or removing the walls of the honeycomb seal cells when the rotor or rotor-side sealing fins are rubbed into the honeycomb seal. The stress of the honeycomb seal can thus be reduced, thereby increasing the life of the same. There is no unwanted increase in the gap to be sealed, which is why a higher sealing effect can be achieved. The sealing arrangement according to the invention serves, in particular, for sealing a radial gap between radially inner ends of guide vanes and a rotor. The honeycomb seals are then assigned to the radially inner ends of the guide vanes or corresponding inner end tapes of the guide vanes, the sealing fins associated with the rotor interacting with the honeycomb seal. It is also possible to seal a gap between the radially outer ends of the rotating blades and a fixed housing with such a sealing arrangement. The use of the sealing arrangement in the compressor area or turbine area of a gas turbine, in particular of an aircraft engine, is preferred.

Claims (5)

  1. Sealing arrangement, in particular for a gas turbine such as an aircraft engine, for sealing a gap between a rotor and a stator, in particular for sealing a gap between radially inner ends of fixed guide vanes and a rotor and/or a gap between radially outer ends of rotating blades and a fixed housing, a honeycomb seal (15) comprising a plurality of honeycomb sealing cells (16) being assigned to the stator, the honeycomb sealing cells (16) being separated from one another by walls (18, 19) and at least the walls (18) of the honeycomb sealing cells (16) which run at right angles to the direction of rotation (17) of the rotor being angled in the direction of rotation (17) of the rotor in such a manner that edges (20) of these walls (18) which face towards the rotor are offset in the direction of rotation (17) of the rotor in relation to edges (21) of these walls (18) which face away from the rotor,
    characterised in that
    the edges (21) of these walls (18) which face away from the rotor run in a straight line and the edges (20) of these walls (18) which face towards the rotor are bent or curved, the curve of these walls (18) running in the direction of rotation (17) of the rotor.
  2. Sealing arrangement in accordance with claim 1,
    characterised in that
    in addition to the walls (18) of the honeycomb sealing cells (16) which run at right angles to the direction of rotation (17) of the rotor, the walls (19) of the honeycomb sealing cells (16) which run in the direction of rotation (17) of the rotor are also angled.
  3. Sealing arrangement in accordance with claim 2,
    characterised in that
    edges (24) of these walls (19) which face towards the rotor are offset in relation to edges (25) of these walls (19) which face away from the rotor.
  4. Sealing arrangement in accordance with claim 3,
    characterised in that
    the edges (25) of these walls (19) which face away from the rotor run in a straight line.
  5. Sealing arrangement in accordance with claim 4,
    characterised in that
    the edges (24) of these walls (19) which face towards the rotor are bent or curved.
EP05706719A 2004-01-31 2005-01-28 Sealing arrangement Not-in-force EP1711689B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004004915A DE102004004915A1 (en) 2004-01-31 2004-01-31 sealing arrangement
PCT/DE2005/000131 WO2005073518A1 (en) 2004-01-31 2005-01-28 Sealing arrangement

Publications (2)

Publication Number Publication Date
EP1711689A1 EP1711689A1 (en) 2006-10-18
EP1711689B1 true EP1711689B1 (en) 2009-04-22

Family

ID=34801375

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05706719A Not-in-force EP1711689B1 (en) 2004-01-31 2005-01-28 Sealing arrangement

Country Status (4)

Country Link
US (1) US20070273103A1 (en)
EP (1) EP1711689B1 (en)
DE (2) DE102004004915A1 (en)
WO (1) WO2005073518A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010062087A1 (en) * 2010-11-29 2012-05-31 Siemens Aktiengesellschaft Turbomachine with sealing structure between rotating and stationary parts and method for producing this sealing structure
DE102012200883B4 (en) * 2012-01-23 2015-12-03 MTU Aero Engines AG Dynamic-seal assembly
US10794489B2 (en) 2015-12-01 2020-10-06 Saint-Gobain Performance Plastics Corporation Annular seals
CN108412556A (en) * 2018-03-15 2018-08-17 哈尔滨工业大学 A kind of prismatic cavity leaf top for controlling the flowing of turbine rotor blade tip leakage

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB793886A (en) * 1955-01-24 1958-04-23 Solar Aircraft Co Improvements in or relating to sealing means between relatively movable parts
US3649033A (en) * 1969-12-24 1972-03-14 Nippon Denso Co Honeycomb rotor-sealing device and method of manufacture
US4218066A (en) * 1976-03-23 1980-08-19 United Technologies Corporation Rotary seal
US4477089A (en) * 1982-07-26 1984-10-16 Avco Corporation Honeycomb seal for turbine engines
US5520508A (en) * 1994-12-05 1996-05-28 United Technologies Corporation Compressor endwall treatment

Also Published As

Publication number Publication date
DE102004004915A1 (en) 2005-08-18
DE502005007136D1 (en) 2009-06-04
US20070273103A1 (en) 2007-11-29
EP1711689A1 (en) 2006-10-18
WO2005073518A1 (en) 2005-08-11

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